WO2005108798A1 - Method and apparatus of forming the tridimensional vortex, and the tridimensional vortex aircraft - Google Patents

Abstract

The invention series belong to the field of aviation and electromagnetics. The invention is related to the creation and application of a novel vortex, which can be applied to the take-off and landing aircraft using the aerodynamic force as the lift within the atmosphere. Said vortex is formed by the fluid (air or plasma) passing through the specific adjusting passage with the assistance of a helical circular vortex accumulator. The air runs along the helix passage and accumulates at the ends to form an annulus vortex, which has the rotated vector on the horizontal plane and the vertical plane. The accumulator produces a novel vortex with high self-stability by forming a substantially circular (or conic) surface as the lift surface, or produces an annulus plasma flow as the Tokamak Device. It provides the main lift for the aircraft. It is a new type of aerodynamic force, and it makes all kinds of aircraft be helicopter.

Description

 Manufacturing method, manufacturing equipment of three-dimensional eddy current and three-dimensional eddy current aircraft

Technical field to which the present invention belongs

 The invention belongs to the fields of aeronautics and electromagnetics, and in particular relates to a method for manufacturing a three-dimensional vortex fluid, a manufacturing device and an application thereof. The series of the invention belongs to the fields of aeronautics and electromagnetics, and is a creation and application of a new type of vortex fluid, which is suitable for aerospace helicopters that generate lift by aerodynamic force in the atmosphere. It also involves acceleration and magnetic confinement of charged ions, and magnetic fluid power systems. Combining multiple mechanical and electrical industries such as automotive, aerospace and even aerospace and nuclear energy.

Prior art prior to the present invention

 One hundred years since the invention of the airplane, the aerodynamic technology used by humans is mainly one. When the air moves rapidly relative to the wing, the air will cause the airflow velocity of the upper wing surface to be faster than the lower wing surface due to the action of the wing, creating a pressure difference. To get lift, this requires the wing to have an airfoil. With the passage of time, new aerodynamic lifts have also been or will be tried. For example, detachable vortexes have been used more. They are mainly used on fixed-wing aircraft to improve high angle of attack performance, delay airflow separation and increase lift; Miniature aircrafts that mimic insects use lift-off vortices to generate lift and thrust by fluttering wings; "Lift Body" i inspection machine and future superb ¾¾ already have or plan to use "bullet body technology" and "wave ride flight technology"; or directly in the It is sufficient to blow air on the lifting surface. The above example is to obtain the lifting force by using the air pressure difference between the upper and lower surfaces, which all belong to the aerodynamic category.

 For current helicopters, in addition to directly using the engine jet or the pulling (thrusting) force of the propeller (fan) to generate lift to achieve helicopter or hover, most helicopters use rotors to generate lift. Its aerodynamic principle As with fixed wings, the rotor must have an airfoil (or elevation) and the speed of movement relative to the air.

 The construction and maintenance of airports and aircraft carriers are costly, the runway area is large, but the takeoff and landing aircraft frequency is limited, and the emergency capacity is low. Whether economically or in use, people increasingly want to get rid of the large airports and aircraft carriers. Constraints. However, due to various defects in current helicopters, the number of fixed-wing aircraft still accounts for the majority. With the development of the times, people are increasingly yearning for the family of aircraft. However, it turns out that light and small fixed-wing aircraft have inherent defects in safety, seaworthiness and convenience, so more and better helicopters are needed instead of Fixed-wing aircraft.

 Over the past 100 years, light and small fixed-wing aircraft have already proven that safety and comfort cannot meet the requirements in difficult flights, such as failure to adapt to the shear wind climate cake, engine safety when it fails, oversized airframes, and flight stability. Poor and so on, coupled with the need for a dedicated take-off and landing runway, so far it is still only a few "flight home toys".

However, both existing and under development helicopters have major drawbacks. Existing old helicopters, such as the majority of rotor helicopters, have large resistance, limited speed, high fuel consumption, and large rotor size. For example, the British "鹞" military jet helicopter has complicated technology and high temperature and high speed. The ground environment has a large impact and a low safety factor. New helicopters under development, such as mimicking the U-shaped manned flapping wing aircraft, have limited success in theory or practice because of the limited weight, size, and power ratios. Hope; for example, micro-aircraft that imitates insects, the scope of its vortex vortex is small, and only appears in the field of low Reynolds number;

The Osprey V-22 tilt-rotor helicopter has poor reliability and inherent defects. Especially during rapid descent, the dangerous "vortex ring state" is prone to accidents caused by retrograde circulation and severe vortices.

 Another problem that has existed for more than a century is that since the invention of airplanes, people naturally wanted to combine cars with airplanes. The contemporary car industry has stagnated in developed countries, the number of cars is close to saturation, and road traffic is easily blocked inside and outside the city. Regardless of the reasons for the transportation facilities or the car itself, it is necessary to further increase the speed and circulation of vehicles. It is very difficult, coupled with the limitations of cars compared to aircraft, such as restrictions on the range of movement, circulation, and speed, so that people always look naturally at air traffic. However, airplanes and automobiles have their own advantages and disadvantages, and their uses and environments are different. They still cannot completely replace each other. At present, people can only have both. At the same time, if cars and airplanes can be perfectly combined in the future, people ’s lives and even the industrial structure will be bound to change. There have been great changes and improvements. However, this attempt has not been successful. Even the barely combined "Four Dislikes" is neither a good aircraft nor a good car, and the safety cannot be guaranteed. In addition to light and small fixed-wing aircraft and known forms The insurmountable shortcomings of helicopters have gradually weakened this idea in society.

 The development history of automobiles is longer than that of airplanes, but for a long time, the application of aerodynamic results has mostly focused on the aerospace and meteorological fields. With the continuous increase of vehicle speed, the aero-aerodynamic achievements have begun to be incorporated into automobile design. . The continuous evolution of the shape of the car from the original reduction of the windward area of the box car (1915) to the beetle type (1934), ship type (1949), fish type (1952), and wedge type (1963), is reflecting the continuous evolution The actual results in the development of automotive aerodynamics are presented. However, in general, the aerodynamics of automobiles are fundamentally different from those of aviation. Automotive aerodynamics has developed into an independent branch of aerodynamics. .

 The "UF0" boom that has fluctuated around the world in the past fifty years. One of the more common is a saucer-shaped flying object, that is, a "flying saucer", which is characterized by being capable of drumming and hovering, and rotating during flight. The whole body often emits strong light. It can suddenly hide or show up for radar detection. It often has strong magnetism. It can accelerate and fly at very high speeds, but rarely emit sounds. In addition, the incidental effect is that when the flying saucer lands or lifts off At times, many windstorms are accompanied. When the flying saucer lands in the desert, it will cause a violent sandstorm. When the flying saucer flies over the snow-covered snowy field, a strong snow cyclone appears under the flying saucer. When the flying saucer hovered in the sea When it is above, the sea surface will be entangled with huge waves and water columns, and the waves will be sucked towards the flying saucer. When it passes over the vehicle (box) at low altitude, it will be lifted (towed). Since the principle of flight cannot be explained with the existing technology, if people admit that this is an unknown aircraft, a new aerodynamic theory is required. This is also an eternal mystery to be solved.

Eddy currents or vortices occupy a very important proportion in natural fluids, but people's understanding and utilization of them are obviously insufficient. Although their significance in new aerodynamic applications has been recognized, and people have long explored the use of eddy currents as Helicopters provide the main lift but have not been successful so far. The following is the content of the prior art known to the applicant:

 ^ If the high-speed vortex or vortex generates lift, the patented technologies are: Chi Yuguang's 92109827. 8 flying saucer, Zhang Yibai's 97205608. 4 jet vortex aircraft, Ren Junchao's 97110404. 2 flying object liftoff method, Xiao Lifeng's 03113561. 7 swirl jet aircraft;

 The patented technology of the aircraft that uses the blades to rotate the compressed air to generate high-speed swirl and the "gyro effect" is: Lin Kang's

99124654. 3 an air and land cyclone gyro helicopter;

 Patented technologies that use magnetically constrained high-temperature plasma Coanda jets to generate lift, thrust, and drag reduction are: Marion's 85105602 drag-reducing jet aircraft;

 The patented technologies for generating lift using frictional pressurization on the lower surface are: Wu Yunlong's 03122707.4 new aircraft; the patented technologies for aircraft using the vacuum layer on the upper surface to generate lift are: He Huiping's 98112980. 3 shell rotating aviation flying saucer aircraft;

 The patented technologies applicable to the ion accelerator in the aerospace field are: 99809994. 5 plasma accelerator device of Germany Thomson Tube Electronics Co., Ltd., Liang Tewei's 97110156. 6 electric potential energy generator and electric potential energy vehicle; using natural " The patented aerodynamic principles of the shape of the "Dune" are: Gao Ge's 85100305. 2 Dune-Standing Vortex Flame Stabilizer;

 According to Higher Education Press, July 1995, 1st edition, Zhao Kaihua and Luo Weiyin's new conceptual physics course "Mechanics", page 235, Chapter V Continuum Mechanics, Section 3.7. Conservation of Ideal Fluid Loop Quantities, writes: : "The axis around the vortex is called the vortex. There is a good experiment to demonstrate the vortex's movement with the fluid. As shown in Figure 5-33, a circular hole is opened in the center of the bottom of an oblate box, like The drum is covered with a tight rubber film on the surface, and it is placed on the table. Spray some smoke into the drum in advance. If you pat the drum surface with your hands, you will see a ring of smoke emerging from the hole in the bottom. Here, one side moves forward and the other side expands. The smoke ring is a closed vortex. The air revolves around it like a solenoid. If a candle is placed a certain distance away, it will blow it after the smoke ring passes. Off. "

According to the Internet website: China Science Popularization Expo / Earth Story / Atmospheric Science Museum / Where does the wind come from / Wonderful wind / Tornado (http: 〃 www.kepu.net.cn/gb/earth/weather/wind), "Tornado is a The violently rotating circular air column, the tornado's temper is extremely rough. Wherever it goes, the roar is thunderous, as strong as an aircraft fleet passing by at low altitude. This may be due to the wind speed of some parts of the vortex exceeding the speed of sound. As a result, a small-amplitude shock wave is generated. How big is the wind speed in a tornado? People can't determine yet, because any anemometer cannot withstand its destruction. Generally, the wind speed may be 50-150 meters per second. In extreme cases, It even reached a supersonic speed of 300 ^ ¾ per second. But the wind speed in the center of the tornado is very small or even no wind, which is very similar to the situation in typhoons. Especially terrible is the low air pressure inside the tornado. This low air pressure can be low Up to 400 Mbar, even 200 mbar, and a standard atmospheric pressure is 1013 mbar. Therefore, in the place where the tornado swept, like a temple suction pump, it often sucked up the water, sand, dust, and trees it touched to form a tall column. When the tornado swept over the top of the building or When a vehicle is in use, its internal air pressure is extremely low, causing a strong air pressure difference between the inside and outside of the building or the vehicle, which will instantly cause the building or transportation vehicle to "explode".

 According to the People ’s Publishing House, Huang Xiangdong ’s “Automotive Aerodynamics and Body Modeling”, Chapter 3, Aerodynamic Forces on Cars and Their Impact on Car Performance, states: "The emergence of aerodynamic lift is not good for cars. There are two basic reasons: It will reduce the adhesion of the car to the road, and it will also induce induced resistance. By the way, the idea of trying to reduce rolling resistance by aerodynamic lift is completely wrong. Aside from the adhesion performance, it is normal Cars traveling at cruising speed will experience much higher induced drag than rolling resistance under the condition that the lift generated remains the same. "Chapter 5 Aerodynamic considerations for vehicle stability, writes:" Aerodynamics for cars The effects of the steady state and transient stability of the vehicle are mainly manifested in two aspects: If the lift of a high-speed car is sufficiently large, it will appear a "fat" feeling, and the ability to maintain the scheduled route and the manoeuvrability are significantly reduced; when the airflow is relatively When the car has a lateral velocity component (such as a side gust or a steering), if the wind pressure center of the car is at the front of the car body, The tendency of the wind to deviate from the original driving route (that is, cross-wind instability). The combined effect of increased lifting force when driving at high speeds becomes very dangerous. To reduce the lift, the appearance of the car should be similar to the typical wing profile and have A certain negative angle. In this sense, wedge-type cars are the best, followed by ship types, and fish-type (hatchback) and beetle-type are worse. Of course, wedge-type tail vortex resistance is generally large, which is to improve the high-speed of the car A cost of safety and stability ... The shape of the longitudinal section of the car determines the cooperative force center of the crosswind, that is, the position of the wind pressure center. The relative position of the wind pressure center and the center of gravity of the vehicle body causes crosswind stability problems. Some machinery Layout measures, such as front-wheel drive or a design that moves the center of gravity of the vehicle as far as possible, can solve this problem to a certain extent. Some high-speed sports cars and test prototypes, in order to obtain a smaller Cx value It adopts the shape of a spindle-shaped streamline body. However, in order to improve the cross wind instability caused by it, an aircraft-like Straight tail, so that the pressure center after the shift, has a certain effect. ,,

According to National Defense Industry Press, "Principles of Aviation Gas Turbines (Vol. 1)" by Peng Zehuan and Liu Gang, Chapter VIII Basics of Combustion Theory, Section IV Flame Stabilization in High-Speed Airflow, Writes: "Know from Fluid Mechanics, Viscous Gas Bypasses Defective streamlined objects will inevitably cause the phenomenon of detachment around the flow. A stable vortex region is formed behind it. In combustion technology, it is called a recirculation zone. The formation of the recirculation zone and its size and fine stable flame play a decisive role. The air flow flows through the V-shaped groove, and the turbulent pulsation is very intense. According to the time-averaged flow velocity, two symmetrical cross-sections are oval-shaped vortices, with a core in the middle, and the speed of the core midpoint is zero. ", Tenth The third chapter of the afterburner second chapter of the dune stabilizer, wrote: "In theoretical and experimental research, it has been proved that the crescent-shaped dune (BD) vortex generator has strong anti-interference performance. The dune stabilizer is mainly used Good natural airflow structure, which not only ensures good heat and mass exchange, but also weakens the periodicity of the V-shaped stabilizer trailing edge vortex. Falling off enhances the vitality of the stable flame, prolongs the residence time of the combustible micelles, and prevents to a certain extent the excitation factors of oscillating combustion caused by the periodic shedding of vortices. "

 According to the Northwestern Polytechnical University Press, Yang Huabao's "Principles and Structures of Airplanes," Chapter 2 Low-Speed Aerodynamics Basics, Section 2-3, Wing Shape Parameters, writes: "Figure (f) is an S-shaped wing profile. The midline of this wing profile is S-shaped, and its characteristic is that the tail is slightly upturned, so that the pressure center does not move forward and backward. Figure (h) is the so-called "laminar wing profile", which is characterized by the lowest pressure distribution The pressure point (that is, the maximum negative pressure) is located at the rear part of the wing section, which can reduce the resistance. This wing section is often used on aircraft with high speed. "

 According to the National Defense Industry Press, "100 Years of World Aircraft" by Cheng Zhaowu, Shen Meizhen, and Meng Xingming, page 172, wrote: "At the end of the 1950s, North American airlines in the United States were developing the XB-70 Duck Super Bomber. During the process, it was found that when the aircraft was flying at a speed of Mach 3, the fibers from the bow of the front end of the air intake duct increased the air pressure on the lower surface of the wing, and the total lift of the aircraft was increased by 30%. Added additional resistance. This phenomenon was then called "compressive lift" or "shock lift". "Page 176," wrote: "An air-space program proposed by the Winsler Institute of Technology in New York, USA It is the real "flying saucer." In order to reduce the resistance, an elongated plasma cone is extended from the center of the "flying saucer" to excite the plasma and generate oblique shock waves. "

 According to Tsinghua University Press, Hui's "University Physics-Electromagnetism (Second Edition)", p. 240, Today's Physics Fun B Plasma, writes: "In order to further produce the conditions for controlled thermonuclear reactions, Combining the above-mentioned ring-shaped magnetic bottle device with the ring-shaped pinch device, that is, winding a coil on the outside of the ring-shaped reaction chamber in the ring-shaped pinch device, and passing an electric current. Thus, there will be two kinds of magnetic fields in the reactor. : One is Bl in the axial direction, which is generated by the current in the coil outside the reaction chamber; the other is B2 in the circular direction, which is generated by the induced current in the plasma. The superposition of these two magnetic fields forms a spiral shape. The total magnetic field Bo theory and practice have proved that the plasma confined in this magnetic field has better stability. In this reactor, particles can be almost endless except for the loss across the magnetic induction lines caused by collisions. The ground rotates around the magnetic induction line in the annular chamber. Because the magnetic induction line is helical or twisted, it does not close by itself after one round of the loop tube, so the particles rotate around the magnetic induction line for a while The child ran to the inside of the ring tube, and later ran to the outside of the ring tube, always hovering in the magnetic field, and would not separate the charges due to the uneven magnetic field. In this device, the axial direction can also be adjusted separately The magnetic field B1 and the circle stele field B2, so as to find a relatively stable working condition of the plasma. This experimental device is called the Tokamak device, which is currently a relatively large number of controlled thermonuclear reaction experimental devices.

Among them, such as Zhang Yibai's 97205608. 4 jet vortex aircraft, which generates a plane vortex in a basin container, but the edge of the basin expands, and the centrifugal force of the plane vortex itself causes the fluid to squeeze toward the edge and upward. Overflow not only loses energy, but also has the effect of upward exhaust and is subject to reverse thrust, which weakens lift. Such as Lin Kang's 99124654. 3-two kinds of air and land With a cyclone gyro helicopter vehicle, the cyclone gyro is composed of paddles on the vertical plane and paddles on the horizontal plane. The rotation of the paddles on the vertical plane presses the surrounding air into the horizontal cyclone. In the shape of a straight plate, the swirling flow is squeezed upward or downward from the inner surface of the vertical blade by the centrifugal force and overflows, and it may be destroyed by the blade on the horizontal surface before the horizontal swirling flow is formed, so its cyclone is impossible Generates major lift. Such as Wu Yunlong's 03122707. 4 new aircraft, which makes the lower surface of the wing into uneven friction areas, it is believed that the lift caused by the friction and collision of gas molecules, of course, it is accurate to say that the kinetic energy of the gas is converted into pressure energy. Small fluid dynamic pressure increases its static pressure. Although it is not necessarily possible to obtain positive pressure, it can at least make its surface pressure as close to the external atmospheric pressure as possible. For example, how is Huiping's 98112980. 3 shell rotary aviation flying saucer aircraft, which forms a vacuum layer on the upper surface and wants to obtain lift, but this is not the case. The vacuum layer on the upper surface repels charged heavy ions upwards. Therefore, according to the principle of working force and reaction force, the upper surface is still subject to the static pressure of heavy ions due to the reaction force of charged heavy ions. The high-speed rotation of the shell causes the heavy ions to have a velocity and dynamic pressure relative to the shell, thereby reducing the static pressure. It is also basically the same as the case of neutral gas on the lower surface of the body, so the static pressure on the upper and lower surfaces is basically the same, so how much lift the aircraft can get is questionable.

 At present, the eddy currents appearing on the manned aircraft are mainly beneficial to the detached vortex (plane eddy current) on the upper surface of the wing of the fixed-wing aircraft. However, the disadvantage of the detached vortex is that the loss is large, and the residual kinetic energy of the eddy current cannot be fully used. Can be generated and utilized under specific conditions (such as high angles of attack) and cannot be controlled. In airplanes with airfoil wings, the detachment vortex is also a harmful vortex that needs to be avoided and eliminated, that is, the presence of wingtip vortices creates induced resistance. In addition, the wake formed in the back of the object in the fluid contains a large number of vortices, which causes the pressure (shape) resistance of the object.

 Therefore, how to make full use of the residual kinetic energy of the vortex and make the vortex be artificially generated and controlled is a historical problem. Object of the invention

 In order to solve the above problems, it can be conceived that when the eddy current can be positioned in a region on the lifting surface, it can be a fixed-point eddy current instead of a disengaged eddy current, and the diffusion of the eddy current is limited, and the lost fluid is continuously replenished, so that the powerful The eddy current continues to generate enough negative pressure on the lift surface, then the lift problem of the aircraft can be transformed into the problem of the generation and restraint of fixed-point vortices', and this limited fixed-point can also occur when taking off, landing or hovering to a standstill. Vortex, the aircraft will become a helicopter, and there will be no induced resistance, which can make the fluid more artificially controlled.

The "smog ring" of human beings and the "tornado" phenomenon and principle of nature provide ideas, which can organically combine the two. When the fluid runs along the solenoid trajectory, it is closed and surrounded at both ends of the solenoid. The toroidal vortex makes it have both vertical and horizontal rotation components, and it becomes a "spiral spiral vortex" (three-dimensional vortex). From the image, it can be said to be an artificial "smoke ring tornado". Like the spiral plasma circulation in the "Tokamak device", from a certain point of view, it is nothing more than taking it out of the thermonuclear fusion container and turning it into a vortex, which is achieved by mechanical, electrical and electrical methods, respectively. The physical forms of fluids are gaseous and plasma. This vortex has a very strong negative pressure like a "tornado", and also has the self-restraining ability like a "smoke ring", with small losses, no induced resistance, small footprint, high fluid utilization, and can be artificially manufactured and replenished. Become the only choice for the new aerodynamics of a helicopter. And this kind of three-dimensional vortex has the special effect of self-compensation for the vertical shear wind, that is, when the vertical shear wind flares from the top to the bottom, the vortex at the top is strengthened, but the lift is increased, so the aircraft will not only descend Instead there is an upward trend.

 The current eddy current manufacturing equipment is generally called a "vortex generator", and the eddy currents generated are usually "plane eddy currents", that is, only the rotation on the plane, and none of them can condense, retain, and restrain the eddy currents. The invention is a "stereoscopic eddy current", that is, a new type of eddy current like a toroidal solenoid. This new type of eddy current has self-restraining properties, which is caused by the special structure of the eddy current generating device or its own magnetic field. Unlike any existing vortex generator, the applicant proposed a new term for "vortex condenser".

Technical solution of the present invention

 The present invention contains two types of eddy current condensers, mechanical and electrical, including three types of aircraft that use this new type of vortex fluid to generate lift, namely automobile aircraft, jet helicopters, dish-shaped aircraft, and three types of vortex condensers on the shed. And proposed a variety of new parts on the aircraft.

 It should be particularly pointed out that: the mechanical eddy current condensate in the present invention not only generates spiral eddy currents (three-dimensional eddy currents), but at the same time, the gas overflowing from the upper part of the eddy current condensate squeezes each other to form a planar vortex. Therefore, two kinds of vortices are formed, that is, there is a plane vortex on top of the three-dimensional vortex. In addition, the condensator can be used to generate ordinary plane vortices after a slight modification. The aircraft can also use the plane vortex to generate the main lift; The characteristic superior to planar vortex is that the surface layer formed by the three-dimensional eddy current on the surface of the rectifying channel is activated due to the rotation of the vortex in the vertical plane, which improves the efficiency, instead of the surface layer below the planar vortex flowing in a circular ring shape. And gradually accumulate and thicken, the energy consumption is greater.

 The two common types of eddy current condensers have the following common features: Fluids (gases or plasmas) are rectified and rectified, and both form solid eddy currents. Multi-level nesting of rectifying channels and three-dimensional eddy currents can be realized on the lifting surface.

 The difference between the two types of eddy current condensers is: The rectifier channel of the mechanical condensator is composed of mechanical components, including three components: the bottom vortex orbit, the side gas pressure panel, and the top torsion surface. Constraints, shaping, etc .; The rectifier channel of the electrical condensing device is a vortex-shaped magnetic field, and the condensing, constraining, and shaping of the plasma flow is achieved by the electromagnetic force effect. Among them, the working medium of the eddy current is also divided into two types: gas and plasma. Big class.

The outer edge of the bottom vortex track of the mechanical condenser is equipped with a side pressure panel, and the middle and upper part of the side pressure panel is equipped with a top torsion surface. The side pressure panel and the top torsion surface have three states, which can be rotated. It is either fixed or naturally extended. When the side air pressure panel and the top torsion surface can be rotated or fixed at an angle, the air is generally pushed in from the surroundings by the condensate itself. When the side air pressure panel and the top torsion surface are naturally extended, it is generally formed by The external gas generating device injects gas.

 The cross-sectional shape of the inner surface of the rectifying channel of the mechanical condenser is a smooth convex curve, which can make a practical choice between fluid loss and torsional efficiency, but the mechanically processed curved surface can never reach the strict physical meaning. To the absolute smooth, it can only be approximate polygon; the preferred plan of the cross-sectional shape of the inner surface of both the bottom vortex track and the side gas pressure panel is a circular arc segment, which can have minimal fluid loss, and the inner surface of the top torsion surface The preferred cross-sectional shape of the surface is an involute (spiral) segment, which can twist the fluid at the highest efficiency.

 The flow ¾ is susceptible to interference during the twisting process and causes chaos. Therefore, the vertical and horizontal cross-sectional plane shapes of the air flow torsion section and the air pressure blades of the condenser of the automobile aircraft can become a thick meniscus in the middle Or individuals, can reduce the resistance and prevent the airflow from being disturbed and obstructed by the mechanical parts when rotating from the bottom up.

 The inner surface of the rectifying channel of the mechanical condenser can be arranged with airflow rotary rifling or vortex generators on fixed-wing aircraft. Both can enhance the rotation of the airflow in the vertical plane, but the emphasis is different. It is the side part of the swirling airflow on the vertical plane, and the inner part of the vortex generating sheet is strengthened.

 The condensing device of the automobile and airplane is to compress the surrounding air inward to obtain the airflow, and gradually accelerate the airflow to the required speed. The airflow source of the condensing device of the jet helicopter is the jet from the engine, and the jet from the engine has reached high speed or even exceeded The speed of sound must be reduced by the drainage orbit (involute groove) to obtain the required sub-Weiwei airflow; while the plasma vortex of the condenser of a saucer aircraft can exceed the speed of sound under the constraint of a strong magnetic field, but Shock waves do not form inside and outside the boundary layer of the fluid, but are usually subsonic.

 The involute grooves on the jet helicopter's condensers allow the airflow to be reduced and rotated, similar to the function of a spiral airflow generator. P 贲 gas flat tube or a spiral airflow generating device dedicated to the combustion chamber of the engine can be directly installed at the air inlet of the annular groove. At this time, the involute groove can be eliminated, but the speed of the jet injection into the annular groove must be sub- Wei, otherwise it can only be installed at the air inlet of the involute groove.

The surface of a saucer-shaped aircraft is a unique new type of ion accelerator. The magnetic field lines from the inner and outer openings at the center of the circle and the peripheral edge form a unique "vortex-shaped magnetic field". The magnetic field lines have a vertical component pointing to the center of the circle and The parallel direction component along the circumferential tangent line. When the positive ion flows, the vertical direction component is subjected to the ^ Lnz force to obtain the centripetal force. The parallel direction component can also constrain the plasma. Finally, the fluid flows in a circular orbit along the conical surface and becomes a vortex. This unique magnetic field also acts as a "container" for the retention and restraint of eddy currents, but the electrons are subjected to centrifugal force and the positive and negative charges are separated and unstable. In order to make the charge distribution of the fluid uniform and stable, it must also be Like a plasma stream in a "Tokamak device", it rotates like a solenoid. The central induction coil generates an induced current in a loop formed by a plasma jet. A circle-shaped magnetic field is formed and is superimposed with the parallel components of the "vortex-shaped magnetic field" to form a helical total magnetic field, so that the plasma twists and spins along the magnetic field lines, that is, it also rotates with the magnetic field like a solenoid. Finally, a three-dimensional eddy current is obtained. This kind of ion accelerator, as a component of vortex condensers, is also the main component of the plasma jet equipment, and also the propulsion engine of the dish-shaped aircraft. It has multiple roles and multiple functions.

 A booster cover plate is attached above the lower agglomerator of the automobile aircraft in the present invention. If only a smooth flat plate is added to the upper part of the eddy current condensate as a cover, then this vortex cannot generate lift, because the fluid also generates a negative pressure on the surface of the cover plate and offsets the lift force. It can only try to increase the pressure on the surface of the cover plate. Big. Therefore, the applicant has added a pressurized cover plate with a friction area similar to the rough surface above the lower condenser of the automobile aircraft.

 A "dune-shaped fairing" in the front of a "dune" shape similar to that of nature was proposed in a car airplane, which can reduce drag, retain eddy currents formed by the condenser, increase lift, and reduce losses. The applicant gives a personal explanation of the structural principle of the "sand dunes" in nature: it is through a slightly flat waterdrop-shaped streamline body by another larger cylinder (or sphere or waterdrop-shaped streamline body) from the front or The remaining body after cutting at the middle section is obtained by taking half of it and making a slight correction (can be sharpened), and its top projection surface is like the same "meniscus". Because of its good natural airflow structure, it has tenacious anti-interference performance. A stable vortex can be retained in the inner space, and it can have a good mass exchange with external fluids. It can neither grow nor weaken. The periodic vortex shedding of the trailing edge of the V-shaped body prolongs the dwell time of the vortex, and to some extent prevents the body's excitation and lift center from moving backward due to the vortex shedding or the formation of a detached vortex. It completely shields the front of the top condenser, avoiding the unbalanced moment on both sides caused by the impact of the high-speed air flow in the front on the inlet of the condenser.

In a car airplane, its movable windshield mainly protrudes downward when driving on the ground to become a wedge-shaped car, reducing the lift of the car; its telescopic tail is extended during flight to become an "S" shaped airfoil plane, reducing Flying resistance, improving heading and longitudinal stability, resisting vertical shear wind; its stator rotating motor (or rotary-cylinder star piston engine) has a rotating stator (or cylinder) fixedly connected to the bottom plate of the condenser, and can be hung together The huge moment of inertia improves flight stability and safety. A centripetal heat-dissipating gas turbine is fixed above or below it, which can provide the compressed air required in all aspects to achieve flight control. In addition, as a car, it uses a front-wheel drive and moves the center of gravity of the vehicle slightly forward to use a double vertical tail design, which greatly improves the crosswind stability when driving on the ground. The characteristics of the new eddy current and the automatic sensor control system are not affected by vertical shear wind. Due to the use of new aerodynamics, this automotive aircraft has become a helicopter. Compared to existing helicopters or fixed-wing aircraft, its energy consumption has been greatly saved. The stability meets the needs in three dimensions. The effect of changing wind is small, and the shape and size meet the two contradictory requirements of automobiles and airplanes. The transmission system is simple and efficient, the control system is flexible and reliable, and the safety reaches unprecedented high standards. Although its overall structure is more complex than that of cars and airplanes, for the first time, it has completely eliminated the contradictions and problems of the combination of the two, and can become the most important personal transport in the future. In the jet helicopter, a frontal "meniscus fairing" similar to the shape of a "sand dune" in nature is also proposed, which uses a so-called "return zone" similar to the combustion technology of an aviation gas turbine, which is different from a single vortex reserved in a car airplane Yes, it can protect and retain the two symmetrical vortices formed by the two condensers, but it can also increase the lift, reduce the loss, and prevent the body vibration caused by the vortex shedding or the formation of the detached vortex to a certain extent And the center of lift is moved back too far. A “meniscus winglet winglet” composed of the “top view” of the “sand dunes” is also proposed, which can reduce or eliminate the induced resistance caused by wingtip vortices, while the wingtip winglets have good natural airflow structure and its upper and lower sides. The wings are tilted towards the Xibu respectively, so that their shape resistance and interference resistance are very small. Because the source of the vortex gas is a jet engine, the inlet nozzle of the vortex condensator is flat tube or flat flared, the nozzle is close to the surface of the rectification channel, and the shape of its cross-sectional curve is consistent with the surface of the rectification flat. Reduces harmful interference to existing vortices and makes air intake more uniform. In addition to the main stream of jets from the main engine in the main scheme as the source of vortex, in addition, a small dedicated auxiliary jet engine can be used to provide vortex air sources during vertical ascent and descent, making this helicopter structure simple and economical. , Safety, and reliability have been greatly improved. Furthermore, the main engine can be replaced by a turboprop engine, etc., which greatly expands the range of aircraft models that use eddy current condensers. Compared with the current mainstream rotorcraft helicopters, this type of helicopter has greatly improved speed and efficiency. Compared with other types of helicopters, its reliability, safety, controllability and flight performance have great advantages, such as comparison Existing military jet helicopters greatly reduce the downward high-temperature exhaust, and the noise is greatly reduced. A single engine can still achieve vertical feed and fall, and low-speed gliding can be achieved without power. The structure of the fuselage is simple, and there is almost no "death". "Heavier", compared with the current majority of rotorcraft helicopters, its flight speed is increased several times, the fuel consumption rate when hovering is also much lower, the tonnage and load capacity of the fuselage are theoretically almost unlimited, and in general, its The cost in terms of cost, complexity, maintenance performance and structural weight is very small. It can replace all aircraft in the mid to high subsonic range in the future.

The "plasma generator, laser horn, shock tube, and strong magnetic tube" was proposed in the dish-shaped aircraft, which can actively generate the front plasma shock manually during flight, and its shape can be controlled by electromagnetic force, which can be weakened. The intensity of the shock wave further softens the shock wave, reduces the shock resistance, reduces the leading edge heating, and improves super-flying performance. The new ion-accelerated disk-shaped aircraft has multiple roles. It constitutes two large accelerator groups, one is the main body of the eddy current condensate in the upper cabin, which can generate a unique "vortex magnetic field" and eddy current, and the other is the middle. The main body of the flight thruster in the cabin can generate the "pie-shaped magnetic field" in the outer layer of the flow field of the aircraft and the thrust required in various directions. It can also be used temporarily to generate eddy currents when hovering. The ion accelerator of the two accelerator groups All of them are long spiral tubes, and all of them are arranged in a multi-involute (vortex) shape. The "pie-shaped magnetic field" in the outer layer of the aircraft's flow field uses the "magnetic mirror effect" to reduce the longitudinal velocity of the shock wave transmission, while increasing the lateral velocity. Further, the "rotating magnetic field" on the upper and lower surfaces of the inner layer of the flow field The "Lorentz force" attracts and pulls the shock surface and approaches the entire surface of the body. On the surface of the upper cabin, the vortex is used to isolate the shock surface, so it receives the negative pressure generated by the vortex, while the lower cabin is completely The high pressure of the shock surface is used to obtain the lift, and the lower surface is positively charged. There is a "low-density isolation layer" between the charge and the shock surface, but this does not affect the transmission of high pressure at all. However, the stagnation of the lower shock surface of the dish-shaped aircraft relative to the airframe in the present invention allows the pressure to be transmitted to the surface of the airframe through the "low-density isolation layer", so as to obtain the lower lift, which is an important proportion during supersonic flight, that is, the lower surface The wavefront provides the so-called "compressive lift" or "shock lift", and the "low-density isolation layer" only serves to insulate and reduce friction. The supersonic flight of the entire aircraft is like a rotating stone on the water. Drift or skateboard. Due to the "Lorentz force" of the "rotating magnetic field" and the "magnetic mirror effect" of the "pie-shaped magnetic field", the shock surface is close to the entire body surface and finally diffuses in the horizontal direction, plus the pinch state of the tail jet, so The sonic boom is basically eliminated. Because the whole body is wrapped in plasma and the body is in the shape of a flat dish, it has ideal radar stealth performance in all directions. The huge moment of inertia obtained by the upper and lower parts of the body rotating at high speed during flight makes it have sufficient flight stability. Under the action of the strong magnetic field, the plasma around the body emits strong light due to the velocity of the mouth. The overflow of the vortex fluid will form a real "tornado" in the lower part. Because the entire flight flow field is controlled manually, the theoretically lowest shape (differential pressure) resistance and shock resistance can be obtained, so its flight efficiency is extremely high; due to its strong power, it has excellent acceleration, plus it has space The potential of flight can be said to be an all-round future aircraft.

 As a result, the perfect unification of cars and airplanes was truly achieved. The extensive heavy-duty jet carrier became a helicopter, and it has initially unveiled the "UF0 mystery" since ancient times. It has also been found for the practice of micro-aircraft and human helicopters. The guiding lighthouse will trigger a revolution in flying technology and open the door to the future of the mechatronics industry.

 The principle, structure, and function of the agglomerator and aircraft are explained in detail in the detailed description in conjunction with the accompanying drawings-BRIEF DESCRIPTION OF THE DRAWINGS

Figure 1-1 is a top view of a rotary blade compressed-air spiral-wound annular vortex condenser

Figure 1-2 is a cross-sectional view of the diameter of a rotary blade compressed air spirally wound annular vortex condenser.

Figure 1-3 is a front view of the inner surface of a compressed air blade of a rotary blade compressed air spirally wound annular vortex condenser.

Figure 1-4 is the forward view of the air pressure blades of the rotary blade air-compressed spiral-wound annular vortex condenser.

Figure 2-1 is a top view of an involute channel bow I-flow spiral wound annular vortex condenser

Figure 2-2 is a cross-sectional view of the diameter of the involute channel drainage spiral spiral vortex condenser

Figure 2-3 is a lateral cross-sectional view of the compressed air side rail of the involute channel drainage spiral spiral annular vortex condenser.

Figure 3-1 is a cross-sectional view of the bottom plate of a vortex magnetic field confined plasma spiral spiral annular eddy current condenser.

Figure 3-2 is a top perspective view of a vortex magnetic field confined plasma spiral toroidal eddy current condenser

Figure 4-1 is a longitudinal sectional view of a magnetically constrained electrostatic field ion accelerator that ejects plasma

Figure 4-2 is a cross-sectional view of a magnetically constrained electrostatic field ion accelerator that ejects plasma

Figure 5-1 is a longitudinal sectional view of a car airplane Figure 5-2 is a top view of the air flight status of a car airplane

 Figure 5-3 is a side view of the ground state of a car airplane

 Figure 6-1 is a side view of a jet helicopter

 Figure 6-2 is the top right 45-degree angle top view of the jet helicopter

 Figure 7-1 is a longitudinal sectional view of a saucer

 Figure 7-2 shows the laser, shock, front jet, tail jet, charge distribution and magnetic field of the saucer.

 Figure 7-3 is a bottom view of the cone-shaped rotating magnetic field generator and cone magnetic field of the lower part of the saucer

 Examples

 ―The present invention contains two major types of eddy current condensers, namely, one-to-one rotary vane compressed spiral spiral annular vortex condenser, involute channel-drain spiral spiral annular vortex condenser, vortex magnetic field confined plasma spiral spiral Eddy current condenser

 1. A rotary blade compressed-air spiral-wound annular eddy current condensate, used in automobile and aircraft, as shown in Fig. 1, Fig. 1-2, Fig. 3, and Fig. 1-4, comprising: a bottom plate Al, an annular groove A21, compressed air blade A31, blade rotating shaft A311, air flow torsion section A41, air flow rotary rifling A5, central rotating shaft A6, and blade torque adjusting mechanism A7;

It is characterized in that-the bottom plate A1 is the bottom surface of the eddy current condensate, which is approximately a disk surface, and the upper surface is provided with a vortex track composed of two annular grooves A21; The groove is arranged in a ring shape, that is, the airflow flows along a circular orbit on the surface of the groove, and the surface of the groove is engraved with airflow rotating rifling A5; the outer edge of the annular groove A21 is provided with multiple air-compressing blades A31, which can rotate around its own rotation axis The blade rotation axis A311 rotates within a range of plus or minus ninety degrees, and can be used for both positive and negative propellers, and can also be fixed at an angle; the blade torque adjustment mechanism A7 is located in the internal cavity of the base plate M, and the main control part is The center of the bottom plate A1 can control the action and rotation angle of the compression blade A31; the blade rotation axis A311 is controlled by the paddle torque adjustment mechanism A7; the bottom plate A1 can rotate about the central rotation axis A6; the inner surface of the compression blade A31 is also engraved with airflow rotary rifling A5; The airflow rotary rifling A5 is similar to the rotary rifling on the inner bore of the barrel. The surface of the annular groove A21 is scored obliquely from the inner edge of the groove to the outer edge along the direction of airflow, and the surface of the compressor blade A31 is along the air. The direction of flow is obliquely scored from the lower edge to the upper edge; the cross-sectional curve shape of the inner surface of the compressor blade A31 is also a circular arc segment; the airflow torsion section A41 is a fixed component separated from the upper and middle parts of the compressor blade A31 When the inner surface of the compressor blade A31 naturally extends upwards according to the shape of the original cross-sectional curve, and when the tangent of this curve is a vertical line, this is the starting point of the airflow torsion section A41. From this starting point, its inner surface The curvature of the cross-section curve curve starts to change, and the curvature of the front edge surface portion of the airflow (wind) suddenly decreases at the beginning, that is, the curvature of this curve starts to increase negatively, but its curvature will increase when it goes upward. It gradually increases with the inward turning of the surface, and reaches the apex of the torsional pressure section A41 at a certain height. At this time, the tangent of this curve is horizontal, that is, the curve is an involute (spiral). Shape, and the upper part of the entire ¾E air blade A31 from front to back The situation of A41 is all the same, but the curvature at the beginning of this sudden decrease is also gradual, that is, the negative increase of the curvature from the leading edge to the trailing edge of the wind also changes. It seems to be gradually smaller, and the beginning negative increase of the curvature of the trailing edge curve has gradually decreased to zero, that is, the curvature starting from the curvature of the transverse cross-sectional curve of the inner surface of the original compressor blade A31. The other changes are the same as before. The curvature of the curve will gradually increase with the inward turning of the surface when walking upward, and the tangent of this curve will be horizontal at the apex of the torsional section A41. The curvature is also the largest, that is, the curve is an involute (spiral) shape; on the whole, the air flow torsional section A41 is an inclined arc that is formed high front and low back, and surrounds a circular orbit as a whole. The curvature of the inner surface curve of the surface is gradual, whether along its axial direction or along its cross section, and the trajectory of the central axis of the airflow rotation is composed of an arc segment along a circular orbit. So like " Partial curved surface of the "horn-shaped horn" can also make the curvature change of the cross-section curve of the entire inner surface of the ¾ ^ stream torsion section A41 from the windward leading edge to the trailing edge the same, that is, they all show the same involute curve (screw Line) shape, then it looks like a slightly curved involute (spiral) curved panel; the vertical sectional plane shapes of the air pressure blade A31 and the air flow torsion section A41 are meniscus shapes with a thick middle in the tip, It can reduce the resistance and prevent the turbulence from being disturbed when the airflow rotates from the bottom up.

 The eddy current condensate is rotated at a high speed by a disc-shaped lift body, and the air pressure blades at the outer edges are opened at an angle to compress the surrounding air into the annular groove. The airflow moves along the groove and is engraved on the inner surface of the arc. Under the action of the oblique rotating rifling, the fluid rotates from the inside to the outside, and at the same time, under the action of centrifugal force, it is squeezed towards the surface of the side blade and rises along the curved inner surface. It is further squeezed at the top air pressure torsion section Pressing and twisting to produce a stronger rotation, the airflow swirls inward and continues to move forward in the groove. This repetitive cycle process forms a "spiral ring-shaped vortex", which is characterized by the fact that when the flow is rotating at high speed, The centrifugal force will not cause it to squeeze upwards and overflow upwards, resulting in excessive diffusive losses. BeiJi successfully condensed the eddy current on the surface of a disc-shaped lift body like a half-open container; when the blades are completely closed, That is, when the blade's opening angle is zero, the "torque horn" shaped inclined arc of the top of the airflow torsion section at the top shows a high front and a low back, and the ring surrounds the whole structure along the groove. When rotating, the air in the front enters from the highest curved arch segment and is compressed by this "horn-horned" sloping arc surface, and then exits from the lowest curved arch segment at the rear to strengthen and supplement the eddy current. At this time, it is still in the minimum power output state and can still Maintain a strong vortex; In addition, after the twist through the blade's top twisting section, there will still be a partial sloping upward flow, and all the upper overflow airflow will form an upper vortex again, which can further constrain the lower vortex and reduce losses; The complete structure of the blades and vortex and annular grooves can have multiple nesting from the outside to the inside. From the simplified structure, the angle of the blades of the inner layer can be fixed outwards, eliminating the blade torque adjustment mechanism. In addition, the three-dimensional vortex overflows. The gas can form a new planar vortex above.

2. An involute channel-draining spiral spiral vortex condensator for a jet helicopter, as shown in Figure 2-1, Figure 2-2, Figure 2-3, including: base plate Al, annular groove A22 , Compressed air side rail A32, Air torsion section A42, Air rotating rifling A5, Involute groove A23, Jet flat tube B5, Rotary vane compressed air vortex condensator B6 (optional); It is characterized in that: the bottom plate A1 is the bottom surface of the eddy current condenser, which is approximately a disc surface, and has two involute grooves A23 on the upper surface, and also two flat flat jets B5; the involute groove A23 is involute; The annular groove A22 is surrounded by the end portion of the involute groove A23 near the center of the inner circle, and has a circular ring shape. The air flow flows along the involute groove on the surface of the involute groove A23. On the surface of the annular groove A22, the airflow flows along the annular orbit; the cross-sectional curve shapes of the inner surfaces of the involute groove A23 and the inner surface of the annular groove A22 are circular arc segments; the airflow rotating rifling A5 is in an involute shape. The grooves A23 and annular grooves A22 and the gas pressure side rails A32 on their outer edges are distributed. The form is similar to the rotary rifling on the inner bore of the barrel. The surface of the involute grooves A23 and the annular groove A22 is along the airflow. The direction of the flow is obliquely scored from the inner edge to the outer edge of the groove, and the surface of the compressor side rail A32 is scored obliquely from the lower edge to the upper edge along the airflow flow direction; the compressor side rail A32 is a fixed form; the airflow torsion section A42 The upper and middle sides of the compressor side rail A32 It is a fixed component that is separated separately. When the inner surface of the side rail A32 naturally extends upwards according to the shape of the original cross-sectional curve, when the tangent of this curve is a vertical line, this is the air torsion section A42. The starting point. From this starting point, the curvature of the cross-section curve of its inner surface begins to change, and the curvature of this curve will gradually increase with the inward curve of its inner surface, and at a certain height Reached the apex of the air torsional section A42. At this time, the tangent of this curve is horizontal, and its curvature is also the largest, that is, the curve is an involute (spiral) shape, and ^ the torsional section A42 from before the wind The curvature of the transverse cross-sectional curve of all the inner surfaces from the edge to the trailing edge is the same, that is, they all have the same involute (spiral) shape, which is like a twisted involute (spiral) shape. Panel; Rotary blade compressed air vortex condensator B6 is located at the involute center of the involute groove A23, and occupies the entire area of the inner circle of the annular groove A22; the flat flat jet pipe B5 is a jet port for the introduction of airflow, and is a flat pipe Or flat trumpet shape; the surface of the involute groove A23 can be made of high temperature resistant materials and coatings, and the composite cooling technology like turbine blades is used by introducing high-pressure cold air from the engine; at this time, the inner rotating blade pressure type vortex condensate B6 No need to rotate, just adjust the angle of the compressor blade to bow the high-speed air flow into the annular groove A22 to form the internal vortex;

This eddy current condensator introduces high-speed airflow through the 3 ± ¾ port. The source air velocity can be Gao Ya, SR ¾ or supersonic. If the source of the vortex gas is a jet engine, the inlet nozzle of the vortex condensator is flat. Tubular or flat flared, the nozzle is close to the surface of the rectification channel, and its cross-sectional curve shape also matches the surface of the rectification channel to reduce the harmful interference to the existing vortex and make the air intake more uniform; The jet flat tube is ejected at a height close to the curved surface of the groove, and an involute groove is introduced. If it is a supersonic fluid, it can form multiple shock surfaces in the groove to decelerate the airflow, while using composite cooling The technology cools the surface and airflow; the rotating rifling on the groove surface and the airflow torsion section on the top of the pressure side rail can cause the airflow to rotate in the vertical plane during the deceleration process, and finally in the annular groove in the center of the involute Reduced to subsonic speed and form a "spiral ring-shaped vortex"; In the inner center area, there can be smaller-sized rotating blade compressed air vortex condensers, which can be drawn from the ring-shaped drainage groove Stream into the gas stream and form an inner vortex. The air-torsion section on the top of the compressed side rail allows all the upper parts to overflow the air flow An upper vortex is formed again, which can further constrain the lower vortex and reduce losses; in addition, the gas overflowing from the three-dimensional vortex can form a new planar vortex above.

 3. A vortex magnetic field confined plasma spiral spiral annular eddy current condensator for a saucer-shaped aircraft, as shown in Figs. 3-1 and 2-3, including: a base plate Al, a superconductor magnetic insulation layer A131, and a heat insulation layer A132, electrostatic layer A133, vortex magnetic field A23, ion force eloquence set C2, inner edge opening C31, outer edge opening C41, central induction coil C51, plasma eddy current C6;

 Its characteristics are as follows: the bottom plate A1 is the bottom surface of the eddy current condensate, which is approximately a conical disk surface, the lower surface is a superconducting magnetic insulation layer A131, the internal cavity in the middle has an ion accelerator set C2, and the upper surface is a heat insulation layer A132 and an electrostatic layer A133. And the electrostatic layer A133 is on the outermost side; the ion acceleration combination C2 is a spiral shape with a plurality of spiral-shaped tubular objects distributed along a circular ring in the form of multiple involutes (spirals). The magnetically constrained electrostatic field ion accelerator is a solenoid-shaped wire and acts as a magnetic confinement and transmission channel for charged ions. The inner edge opening C31 and the outer edge opening C41 are on the surface of the electrostatic layer A133 through the winding. Extend and obliquely. Relatively, the inner edge opening is inclined outward at an angle along the circumferential tangent, and the rim opening is inclined inward at an angle along the circumferential tangent. The smooth connection between the inner and outer edge openings is involute. Vortex shape, when the solenoid-shaped wire is energized with current, the magnetic lines of force concentrated on the openings of the inner and outer edges constitute the vortex magnetic field A23, which is opposite to the direction of the involute of the solenoid winding; Port C41 is a plasma nozzle. The design must ensure that the direction of motion of the plasma vortex C6 and the direction of the magnetic field lines of the vortex magnetic field A23 have an appropriate angle. In addition, a negative ion nozzle is led from the side of the plasma nozzle; the central induction coil C51 surrounds The center of the eddy fluid is arranged inside the trajectory of the vortex as a whole; the electrostatic layer A133 can generally carry a negative charge;

This eddy current condensator is a new type of ion accelerator that accelerates, constrains, and transports charged ion current. After the positive and negative ions are mixed at the nozzle, the formed plasma stream is obliquely ejected from the outer edge opening into the circle; from the plasma nozzle The negative ions (electrons) ejected from the side are opposite to the direction of the plasma vortex, forming a reverse vortex of negative ions, which continuously collides with neutral molecules to form the plasma state of the entire vortex. The electrostatic layer can generally be negatively charged, while attracting and constraining positive ions, it can collide with positive ions ¾ = generate "secondary electrons" to stimulate the ionization process; the smooth lines connecting the openings of the inner and outer edges are multi-graded. Vortex-shaped, when the solenoid-shaped wire is energized with current, the magnetic field lines concentrated on the inner and outer edge openings constitute a vortex-shaped magnetic field; because the direction of the vortex of the plasma vortex is designed to match the direction of the magnetic field lines of the involute vortex field When the plasma eddy current is compressed by the "Lorentz force" toward the floor surface due to the vertical component of the magnetic field line, it is also constrained by the parallel component of the magnetic field line. When cutting the vertical component of the magnetic field lines of this vortex-shaped magnetic field, the positive and negative ions receive the opposite direction of the force, the positive ions are attracted to the surface of the body by centripetal force, and the negative ions are repelled by the centrifugal force away from the surface of the body. Stable body flow and uniform internal charge distribution, the fluid must be macroscopically like a "tokamak device" for thermonuclear fusion Plasma beam It is also necessary for the solenoid to rotate and allow part of the negative ion current to be sprayed and rotated in a direction opposite to the direction of rotation of the plasma vortex. Because the plasma current is a good conductor, the plasma can be caused by the changing current in the central induction coil. Induced potential is generated by the flow, and an induced current is generated in the loop formed by the interconnection of the plasma jets, and then a circle magnetic field is formed, so that the axial magnetic field and the circle magnetic field in the plasma eddy current are superimposed into a circular axis. In the spiral magnetic field, the eddy current of the IJ plasma also spirals as the magnetic induction line twists, and eventually becomes a "spiral annular eddy current", in which the ion current swirls along the spiral magnetic induction line, so that the plasma is stable. The working negative, and the negative anion (electron) nozzle that is drawn from the plasma nozzle, ejects an electron flow opposite to the direction of the plasma vortex rotation, so that the plasma state can be maintained at all times. This vortex is very similar in shape, structure and properties to the spiral plasma circulation in the "Tokamak device", except that it is taken out of the thermonuclear fusion vessel, and the circulation is turned into an eddy current; in a vortex magnetic field The speed of the ion current under the constraint can be super ¾¾, but it will not cause shock waves inside the vortex itself and the outer boundary airflow. It can also mix and decompose the shock waves generated in front of the supersonic flight, and make the external shock surface close to The entire surface of the vortex; the gradually decreasing part of this three-dimensional vortex will become the planar vortex of the inner ring, and gradually migrate to the top of the cone and further decelerate, and then be sucked in or overflowed; otherwise, the neutrality of this three-dimensional vortex overflow is neutral The gas can form a new plane vortex in the lower part of the body, becoming a "tornado".

2. The eddy current condensers and flight thrusters used in the present invention are almost entirely composed of a new type of ion accelerator, that is, a magnetic confinement electrostatic field ion accelerator that ejects plasma.

 A magnetically constrained electrostatic field ion accelerator for spraying plasma is used in a saucer-shaped aircraft, as shown in Figure 4-1 and Figure 4-2, and includes: a solenoid conductor D1, an external electrode charging wire D2, and a static electricity The field electrode D3, the positive ion channel D4, the internal electrostatic field electrode D5, the internal electrode charging wire D6, the circular tube-shaped conductor D7, and the negative ion channel D8; in addition, the supporting structure as the internal circular tube assembly is omitted here, and now Some descriptions are just a small segment in the middle of the entire long solenoid-shaped accelerator;

Its characteristics are: the solenoid conductor D1 is in the outermost layer of the accelerator, and the turns are tightly connected, which can be a superconductor; the electrode charging wire D2 is connected to each external electrostatic field electrode D3 and is distributed at a uniform interval in the space; The electrostatic field electrode D3 and the internal electrostatic field electrode D5 are respectively located on the inner side wall and the inner side wall of the positive ion channel D4. The inner field electrode is a circular tube structure, and its gradient voltage is discharged from the front entrance to the rear nozzle. The distribution sequence is: The highest voltage is on the outer electrode tube at the entrance. After the entire length of the electrode tube, the second voltage is added to the inner electrode tube. After the entire length of the electrode tube, the third voltage is applied. The voltage is applied to the external electrode tube and so on; the positive ion channel D4 is a tube-shaped channel in the electric field space formed by the external electrostatic field electrode D3 and the internal electrostatic field electrode D5; the internal electrode charging wire D6 is separately connected to each internal electrostatic field electrode D5 is connected and is distributed at even intervals in space; the circular tube-shaped conductor D7 is a circular tube structure at the center of the solenoid, and the center is a negative ion channel D8; The ion accelerator uses the stepped voltage of the external electrostatic field electrode and the internal electrostatic field electrode to decrease from the high voltage at the inlet to the low voltage at the outlet in the longitudinal direction. The internal and external electrodes are staggered at the front and rear edges, and the voltage gradients are staggered. In the tube-shaped positive ion flat, a unique and relatively uniform longitudinal "slant-gate-arranged gradient electrostatic field" is formed, and the positive ions can be accelerated from zero to extremely high speed. The solenoid conductor is passed current to form an axial magnetic field in the positive ion channel, which restricts the positive ion current in motion. When positive and negative ions are mixed at the nozzle to form a plasma, an induced current is formed in the fluid. The components of the parallel magnetic field that generates the current and the "vortex-shaped magnetic field" on the outer surface are superimposed into a spiral magnetic field, so that the plasma stream is twisted into a spiral shape, forming a "spiral spiral plasma vortex"; The conductor itself can isolate the external electric field, but it will not isolate the magnetic field. When it is energized, a circular magnetic field is formed outside the tube. The magnetic field lines of force are perpendicular to the direction of the positive ion movement, which causes the positive ion current to be compressed and increased. The positive ion flow is focused and the positive ion flow is focused; the center of the solenoid conductor becomes a negative ion channel. The negative ion is constrained by the magnetic force, but it is not affected by the external electric field and does not affect the external ions. The negative ions at the entrance may have an initial velocity equal to the velocity of the positive ions at the exit, that is, the negative ions are not subject to longitudinal acceleration in the accelerator; The plasma nozzle is at the tail of the accelerator, and a negative ion nozzle can be drawn on the side of the nozzle. The negative ions (electrons) ejected are opposite to the direction of the plasma flow, and constantly collide with the molecules that have become neutral in the vortex to form a "burst". In order to maintain the eddy current plasma state and avoid positive and negative charge separation; all adjacent parts are insulated by insulators; this ion accelerator is also used as a propeller of a saucer-shaped aircraft, which uses a high-speed plasma to eject The obtained recoil force, and its ion distribution nozzles in the circumferential direction can inject ions into the annular solenoid container on the edge of the aircraft, which can adjust the attitude of the aircraft at any angle, and the magnetic field lines of the ion distribution nozzles in the circumferential distribution are formed together. An outer "pie-shaped magnetic field"; that is, the ion accelerator has multiple roles on a saucer, and has a variety of important functions. It is generally not used alone. Usually, multiple solenoid-shaped accelerators are used to gradually open. Line (vortex) forms are used in groups, and there are two such large accelerations on a saucer. Groups, although in theory be used in place of other ion accelerator, but only becomes more discrete components and equipment, ineffective.

3. The present invention contains three types of helicopters, namely, a car airplane, a jet helicopter, and a saucer.

1. An automotive aircraft, as shown in Figure 5-1, Figure 5-2, and Figure 5-3, including: eddy current condensate H1, eddy current condensate H2, coaxial counter-rotating double-blade double propeller H3, and retractable wheels H4, Electronic and electrical system assembly H5, Front main battery fuel (oil) tank H6, Front mechanical system H7, Rear mechanical system and battery H8, Rear main battery fuel (oil) tank H9, Double vertical tail Η10 , Flat tail Hll, telescopic tail frame H12, movable windshield H13, dune fairing H14, middle trunk H15, horizontal drive shaft H16, vertical drive shaft H17, auxiliary wing H18, aileron H19, vertical tail rudder H20 , Flat tail elevator H21, integrated vehicle (machine) frame H22, bevel gear group rendezvous H23, movable windshield track pulley H24, movable windshield telescopic arm H25, wing end jets H26, telescopic tail end jets H27, wing chamber H28, telescopic tail can be overlapped Cloth H29, Stator Rotary Motor (or Rotary Cylinder Star Piston Engine) H301, Stator Rotary Motor (or Rotary Cylinder Star Piston Engine) H302, Ring (Circular) Disc-shaped Booster Cover H31, Centripetal Radiator and pressure turbine H32, back-to-back seat H33, spare battery fuel (oil) tank H34, top side parallel air outlet H35, telescopic tail storage room H36, reverse opening and lift-up dual-purpose door H37; front air outlet H38 ;

 It is characterized in that: the eddy current condensator HI is installed on the top of the body, and is driven to rotate by a stator rotary motor (or rotary-cylinder star piston engine) H301; the eddy current condensator H2 is installed at the bottom of the body, and is driven by the stator rotary motor (or rotating Cylinder-type star piston engine) H302 is driven to rotate, and the upper surface of the motor (engine) is equipped with a centrifugal heat-dissipating gas turbine H32; the lower surface of the top eddy current condenser HI can also be equipped with a booster cover, and the bottom vortex Condenser H2 is equipped with a booster cover H31. The booster cover H31 is connected to the heat-dissipating gas turbine as an integral disc. The upper cover of the bottom vortex condensate H2 is also optional. The lower surface of the bottom vortex condensate H2 is also optional. Pressurized cover plate; the top vortex condensator HI and the bottom vortex condensator H2 have opposite rotation directions and equal inertia moments; the coaxial counter-rotating double-blade double propeller H3 is at the front of the body, and the diameter of the blade rotation surface is not greater than the body width. Variable pitch and reverse propellers can be constant speed propellers, which are locked at the horizontal position when driving on the ground; retractable wheels H4 is the four-wheel layout of the car When driving on the ground, it is driven by the front two wheels, but it is fully incorporated into the fuselage during flight. The electronic and electrical system assembly H5 is located at the front bridge in the cabin, and is composed of electronic automatic control and communication systems and electrical implementation systems. The main battery fuel (oil) tank H6 is below the front of the body. The liquid level is controllable and there is an anti-sloshing and flame retardant mechanism. The front mechanical system H7 is located at the middle of the two cymbals below the front and is driven by wheels (paddles). And adjustment mechanisms such as clutch, reducer, transmission, differential, universal joint, drive shaft, brake, wheel retractor, paddle lock, pitch changer, etc .; rear mechanical system and battery H8 under the rear The middle of the two front wheels of the square is mainly composed of brakes, wheel retractors, steering gear, batteries, etc. The rear main battery fuel (oil) tank H9 is at the rear of the fuselage. The liquid level is controllable and there is an anti-shake and flame retardant mechanism; The double vertical tail H10 and flat tail H11 are in the shape of "Π" above the tail of the fuselage. They have a vertical tail rudder H20 and a flat tail elevator H21. The telescopic tail frame H12 is a pneumatic telescopic frame beam structure. At the tail end of the telescopic tail frame, there is a telescopic tail end air outlet H27, and the B 贲 gas port has multi-directional turning ability. The entire telescopic tail frame is covered by a telescopic tail stackable cloth H29. Parcel

The movable windshield H13 is directly above the front of the body, in front of the outer surface of the fixed windshield, and is similar in size and shape to the fixed windshield. There are movable windshield track pulleys H24 and movable windshield on both sides. Arm H25, in order to reduce lift and resistance during ground travel, the movable windshield protrudes to the front and lower of the nose, and the fixed windshield is used to construct the body forward and backward. When flying, the movable windshield is retracted at Before the windshield is fixed; the dune-shaped fairing H14 is directly in front of the top eddy current condensator HI. It is a thin-wall curved panel structure similar to the natural "sand dune" shape that can reduce resistance and retain vortices and increase lift. On the left and right and above, the vortex condenser is used to block the impact of the forward flow; the middle trunk H15 00451 In the middle of the body, back to back ^ seat Η 33, the luggage is usually in the middle and the seat is back-to-back during flight. When driving on the ground, the luggage can be removed from the middle and installed at the rear, and the rear seats can be adjusted to The usual front-facing form of a car; the horizontal drive shaft H16 and the vertical drive shaft H17 are linked to the front mechanical system Η7 and the top eddy current condensator HI, but both meet the bevel gear set reciprocator H23 below the middle of the body, and the bevel gear set The lower part of the rendezvous is linked to the bottom vortex condensate H2; the auxiliary wing H18 airfoil profile adopts an asymmetric biconvex shape, and the wing under the trunk H15 in the middle of the body when traveling on the ground! In the room H28, when flying It can be extended. There are organic aileron H19 and wing end air outlet H26. The air outlet has multi-directional turning ability. The aileron movement and wing expansion and contraction can be operated by compressed air. The auxiliary wing can be rotated around its own axis to become positive. Angle of attack or negative angle of attack; integrated vehicle (machine) frame H22 is the load-bearing frame of the fuselage, the outer side of the lower frame is a rectangle with four sides, the middle is an "X" shape, and the upper frame is the upper wing along the wing airfoil Arched shape was "X" shape, the upper and lower frames "X" cross-shaped central upper and lower bearings has a vertical drive shaft of H17;

Stator rotating electric motor (or rotary-cylinder star piston engine) H301 and H302 are located in the center of the eddy current condenser. The rotating stator (or cylinder) is fixedly connected to the bottom plate of the eddy current condenser, and rotates together with the eddy current condenser. The motor (engine The rotating part should account for most of its total mass. At least the mass of the rotating part is greater than the mass of the fixed part. When a stator rotary motor is preferred, a transmission method is: the fixed shaft of the fixed rotor in the center is fixed at On the body, it is coaxial with the rotating shaft of the rotating stator. The fixed shaft of the fixed rotor is the external shaft, while the rotating shaft of the rotating stator is the internal shaft and extends to the bevel gear group intersection H23. Another transmission method is: the stator Both the rotor and the rotor rotate positively and negatively. The rotating stator indirectly meshes with the rotating rotor through the gears and rotates in opposite directions in conjunction with each other, and extends from the rotating shaft of the rotating rotor to the bevel gear group intersection H23. The rotating shaft bearing of this rotating rotor is fixed to the body If the rotary-cylinder radial piston engine is selected, the transmission system is best compared with the latter method. However, no matter which method is used, its oil supply system is more complicated than electric drive; the stator rotary motor (or rotary-cylinder star piston engine) at the center of the eddy current condenser is centripetal on the upper (lower) side of H30 The type of heat-dissipating and compressed-air turbine H32, the turbine blades are involute (spiral), the whole of the turbine is a flat box structure with an edge slit, a compressed air exhaust channel in the middle, and compressed air at the bottom is mainly for the aerodynamic parts of the body. Compressed gas, and the top compressed gas is mainly provided to the top parallel jet H35; the backup battery fuel (oil) tank H34 is below the tail of the fuselage; the top parallel jet H35 is located in the lower part of the top vortex condensator and is arranged in parallel with multiple jets The upper side of the rear fuselage jets in parallel and backward; the telescopic tail cage chamber H36 is at the rear end of the locomotive with shear wind transmission ¾ _{; the} reverse-opening and up-lifting dual-purpose door H37 can be opened sideways and upwards respectively; front The air outlet H38 is on the left and right corners of the front of the fuselage;

This automotive aircraft uses a new type of aerodynamic power to become a helicopter. Compared to existing helicopters or fixed-wing aircraft, its energy consumption is much saved, and the stability meets the needs in three dimensions. Affected by the shear wind and cross wind, the shape and size meet the two contradictory requirements of automobiles and airplanes. The transmission system is simple and efficient, and the control system is flexible. Reliability and safety reach unprecedented high standards; a eddy current condensator is installed on the top and bottom, respectively, to rotate opposite to each other to balance the rotating torque, and a stator rotary motor (or rotary-cylinder star piston engine) is installed in the center of the bottom plate ), Increase the moment of inertia, so that if the entire engine fails during flight, you can also rely on the energy stored in the great moment of inertia to maintain the lift and slowly decrease, because the energy used to compensate for the eddy current loss is very small, the energy stored in the moment of inertia It also consumes very little, so it can achieve unpowered and safe landing from a very high degree of inertia; the "gyro inertial effect" caused by the great moment of inertia makes the body no matter during take-off and landing, hovering, flying, and vertical cut Sufficient horizontal stability can be maintained in variable winds; the top vortex condensers and the bottom vortex condensers have similar weights, and their moments of inertia are basically equal, and the unbalance of torque can be adjusted by the variable pitch of the pressure impeller. The frame (also pneumatic or electric parts) extends the telescopic tail and tilts it upward slightly. Block shape, and the longitudinal curvature of the upper and lower surfaces of the fuselage is appropriately selected, so that the longitudinal section of the combination of the fuselage and the telescopic tail is an "S" shape airfoil structure of the aircraft wing, that is, the airfoil curve is "S" shape, It can resist vertical shear wind. At the same time, the upward curvature of the front bottom panel should be appropriately selected to achieve the best airfoil curvature and airfoil leading edge radius in the longitudinal section of the fuselage. The best lift-to-drag ratio is obtained when cruising, and the locomotive is at The bottom airflow is improved when driving on the ground, and the telescopic tail can not only make the structure of the body more streamlined, but also reduce the pressure (shape) resistance. The larger projection area can also shift the focus of the aircraft backwards. Improve the longitudinal stability during flight, and at the same time, its lateral projection area also improves the lateral stability during flight. The telescopic tail retracts to the telescopic tail collection room when it is traveling on the ground or encounters shear wind during flight. Need, the shape of the airframe is more like a car than an airplane, and it is convenient to use the shape of the car. The "s" shaped airfoil body also generates lift in flight. The pitch moves the center of lift; when it encounters vertical shear wind from top to bottom, the vortex at the top is strengthened, and instead the lift is increased, so the aircraft will not rise but will have an upward trend, that is, it will have a sense of vertical shear wind. The special effect of compensation; because the tail and tail are not effective when hovering, the aircraft can be turned, pitched, advanced, reversed, and traversed by the front and rear nozzles;

The auxiliary wing can be extended during hovering to exhaust with wing tip nozzles to adjust the body balance, and to extend the flight lift when the body is too heavy or the various torques cannot be balanced, and it can usually be retracted to reduce the mutual in the workshop. The probability of rubbing, in which the wing tip nozzle is mainly used to adjust and compensate for the lateral stability problem that may arise from the center of gravity of the condenser deviating from the center axis of the lift of the condenser when hovering, because the rotational inertia of the two lift bodies of the locomotive is equal and The direction of rotation is opposite, so there will be no "drift effect of the gyro precession", and the wing tip nozzles will also maintain the balance of the torques with respect to the center of gravity together with the front and rear nozzles; and because this new type of vortex is used completely as the lift of the helicopter Its lift distribution is very uniform and the structure of many dense compressor blades makes it inherently not vibrate, while the coaxial counter-rotating propeller generates very little vibration. Therefore, with the cooperation of many adjustment mechanisms, whether it is in flight or The body will not sway and vibrate when hovering; the induced resistance caused by the lift of the airfoil body is very small, and the coagulator generates vortices. The flow has no induced resistance, so the total resistance of the body is small, which increases the speed and reduces the energy consumption; the top fairing is A thin-walled curved panel structure similar to the "sand dune" shape in nature, which is passed from a front or middle through a slightly flat waterdrop-shaped streamline body by another larger cylinder (or sphere or waterdrop-shaped streamline body). Half of the remaining carcass after cutting is obtained by trimming it slightly (can be sharpened). Its top projection surface is like the same round of "meniscus". Because of its good natural airflow structure, it has strong anti-interference performance. A stable vortex can be retained in the inner space, which can have a good mass exchange with the external fluid, can neither grow nor weaken, and prevents the vortex of the trailing edge of the cylinder or V-shaped body from falling off periodically, which prolongs the vortex. The residence time, and to some extent, prevents the body vibration and lift center from moving backwards due to the vortex shedding or the formation of a detached vortex. At the same time, it can reduce drag, increase lift, reduce energy consumption, and condense the top The device is completely shielded, thereby avoiding the rotation or vibration of the body that may be caused by the imbalance torque on both sides caused by the impact of the high-speed airflow in the front on the air intake of the condenser; The upper surface of the upper part of the body jets backwards in parallel, blowing out the turbulence at the rear, delaying the separation of the surface airflow, which can increase the lift and reduce the pressure (shape) resistance, while the retractable tail jets weaken the tail vortex when traveling on the ground. The movable windshield retracts during flight and forms a double-layer form with the fixed windshield, which improves forward collision resistance during flight, and extends forward and downward when the ground is required to reduce lift due to high-speed driving. The airfoil of the airfoil body acts as an anti-collision plate and also protects the propeller. At the same time, it acts as a nose fairing to reduce the resistance caused by the head propeller and other parts, because the shape of the airframe is mainly constructed to generate lift during flight. Therefore, when driving on the ground at high speed, it is necessary to make the body into a wedge shape, forming the so-called "negative impact angle" before and after the airfoil camber line, in order to reduce lift and induced drag, and improve the wheel's adhesion to the ground, and At this time, the retractable tail was retracted into the rear cabin, and the body became a "wedge-shaped (sloping) back" car, which meets the needs of the exterior structure of high-speed driving on the ground. However, the length of the fuselage is still only equivalent to that of a normal car. The width of the fuselage is subject to the diameter of the eddy current condensate. If the diameter of the vortex condensator is made as small as possible, the width of the entire body is equivalent to that of a normal car; The body height may be slightly higher than that of a normal car;

The locomotive uses front-wheel drive, and the center of gravity can be adjusted to a slightly forward position through the movement of the fuel. In addition, the wide double-tail structure allows the cross-wind stability to be satisfied when driving on the ground. When the winglet winglets and wingtip end plates hinder the formation of two large three-dimensional wake vortices at the rear of the fuselage, they can reduce the induced resistance and pressure (shape) resistance at the same time; the front propeller blade surface when driving on the ground The rear flat tail elevator can be deflected to increase the local pressure and improve the adhesion of the wheels to the ground. The upper cover of the bottom vortex condenser is equipped with a centrifugal heat-dissipating gas turbine, which provides compression for the aerodynamic components while the engine is cooling Air source, each jet port can adjust the attitude of the aircraft at any time; The pressure impeller of the vortex condensator is in the state of reverse propeller when traveling on the ground, and the rotation of the condensator does not generate lift, while still allowing the engine to dissipate heat; The lower surface of the bottom plate can also be equipped with a thinner booster cover plate to avoid the negative pressure that may be generated on the lower surface of the condensator due to high speed rotation. Generally, two engines are used. When a fuel cell motor is used, if necessary, an additional motor can be installed at the front to increase the speed or increase the safety factor. That is, if the shaft of the eddy current condenser is stuck, the front motor Still make the plane level 1 row and safe landing; Co-rotating double-blade twin propellers increase power output and efficiency, and at the same time, balance the rotating torque on the vertical axis; The center of the lift of the body i is slightly behind and does not change with the angle of attack However, the gas that overflows from the upper three-dimensional vortex can form a planar vortex. It may move backward and become a disengaged vortex as the speed increases during flight, which will have a certain impact on the rear upper surface and the tail. May move slightly backwards as the speed increases, the center of gravity of the aircraft can be adjusted, it is above the central axis line of the upper and lower vortex condensers when hovering, and it can move slightly when flying forward, but always before the lift center or focus of the whole aircraft , Making the aircraft a "quiet and stable" aircraft during flight; the inherent aerodynamic conditions and inner structure of the locomotive make it not afraid of light rear-end collision or collision of the body and wings during flight, and can accept small foreign objects or The bird's frontal impact can still use the huge moment of inertia to maintain the eddy current required for lift, so that it can land slowly, smoothly and safely without being affected by other aircraft or locomotives. The effect of the wake of the turbulence is particularly beneficial to adapt to the busy air traffic in the future and become the most versatile future air-ground two-zone manned transportation vehicle; because the safety of the locomotive has reached the peak that the aircraft can theoretically reach, so the machine There is no parachute inside, but for the purpose of forced landing on the water, an emergency inflatable airbag can be added. In addition, due to its strong lift, large load capacity, sufficient internal space and reasonable body structure, it is convenient to fully use existing mature cars and Anti-crash and anti-crash technology equipment for helicopters, such as head anti-collision airbags, four-wheel anti-crash oil shock absorbers, anti-fall seats, elastic energy-absorbing material cabins, energy-absorbing straps, anti-fall soft fuel tanks, etc., but mainly It is used to deal with a possible crash caused by a serious impact in the air. The failure of the locomotive itself generally does not cause safety problems. The locomotive can take off and land at any time anywhere outside the urban area. It can also fly over traffic jams at low altitudes in the urban area. At this time, the propeller does not move, and the wings and telescopic tail do not need to be extended. Only the tail nozzle is used to achieve the propulsion and steering, and the front nozzle is used to achieve the And back brake, and to achieve common traverse, will not have a strong influence downwash air flow and push the surrounding environment, will not result in dangerous external rotary member to each other;

In order to decelerate efficiently when flying in the air, the double tail can be designed as a split-type high-resistance rudder to double as a speed reducer. At the same time, the front propeller can realize the reverse propeller operation state. Of course, if necessary, the aircraft can also use the reverse propeller for reverse flight. ; Due to the use of new high-efficiency and low-consumption aerodynamics, its fuel consumption rate is not only much lower than the existing general-purpose rotor helicopters, or even lower than the existing general-purpose fixed-wing aircraft. The shortcomings of the rotor helicopter are inefficient, but they retain and develop the advantages of the two, and combine all the characteristics of the car; the locomotive can be fully automatic (especially when flying), or it can be converted into a semi-automatic form, and When driving on the ground, it can be changed to full manual driving. The locomotive motion control system can use the aircraft ’s redundant telex or light transmission control mode, and can include a set of emergency simple machinery ^, especially when it is used for manual driving on the ground. «Vertical; locomotive has a variety of sensors and communication equipment, can automatically sense attitude and environment ^ 牛, accept the host Voice commands and the command of the traffic network control agency; The economic speed of locomotive ground running can be 100 ~ 200 km / h, the air flight cruising speed can be 300 ~ 600 km / h, the number of ¾A can be 4 ~ 6 people, and the main flight route can be It is the air on both sides of the highway on the ground between cities. At this time, the ground lightning control and satellite system navigation and robot driving, the flight altitude is It generally does not exceed 1 kilometer, does not disturb the traffic lines of large passenger aircraft, and can be subject to application for approval to open the beach into the scenic area. Sightseeing within the allowed height and area, and flying and parking at will. Thus truly achieving the perfect integration of cars and aircraft

2. A jet helicopter, as shown in Figure 6-1 and Figure 6-2, includes: eddy current condensator II, air inlet 12, turbojet engine 13, auxiliary wing 14, meniscus fairing 15, aircraft Airframe 16, engine vector nozzle 17, "T" tail fin 18, vortex surface 19 of plate structure, meniscus winglet 110;

 It is characterized by: The eddy current condensate II is arranged on the back of the fuselage. It is an involute channel drainage type eddy current condensator. It has two left and right side by side to become the main lift body of the aircraft. The form of the drainage channel on it is single. In the involute shape, the involutes of the left and right lifting bodies rotate in opposite directions, and the air inlets are parallel to each other at the center of the top of the aircraft, and share an air inlet 12 for the natural incoming flow in front; the air inlet 12 is similar to The air inlet of today's supersonic aircraft has a beveled lip. The internal upper surface has a compression swash plate for compressed air. Its tilt angle is adjustable. There is a shroud at the rear of the interior. It can be used to divide the air flow into two streams. There is an engine air intake port, which is connected to the tail nozzles of the two engines at the same time, and the two streams are mixed and divided into two again, which are respectively provided to the air inlets of the two vortex condensers. There are two turbojet engines 13, Hanging below the eddy current condensers on both sides of the body, and at a certain distance from the body, there is a drainage tube in the middle and rear to mix the engine and the gas along the hanger The pipeline is fed to the eddy current condensate. The tail is the engine vector nozzle 17, which can be turned down from the horizontal direction by more than ninety degrees, and can be slightly rotated to both sides. The auxiliary wing 14 is installed on the outside of the eddy current condensate and slightly back. The auxiliary lift center provided is behind the center of gravity, and there is also an aileron for adjustment; the meniscus fairing 15 is on the top of the leading edge of the vortex condenser, and is combined with the top of the air inlet 12 as a front shield for the two vortices. The shape of the fairing is a "dune" shape in nature; the aircraft body 16 is the type of a high-aircraft aircraft, and the front and rear ends and the two wing tips have attitude adjustment jets, respectively, and use the high-pressure air-conditioning of the engine; "T" tail 18 away from the jet flow of the engine; the vortex-retaining surface 19 of the plate structure is a slightly downward curved plate structure, which is generally not adjustable, is located at the trailing edge of the vortex condensator, and the width is similar to it, and the length is optional; the meniscus wing tip winglet 110 at the mid-rear end of the wing tip;

This jet helicopter is a ship with one left, one right, two bow I-flow eddy current condensers on the back of the fuselage. The left and right two involute drainage channels merge at the front to form an air inlet, and the air inlet is from the bottom. The jet flow of the engine is introduced to form the vortex and provide the main lift, so it becomes a helicopter; the bottom surface of the vortex condensator can be the shape of the bottom surface of the "laminar airfoil" of the aircraft wing, and the vortex-retaining surface of the plate structure is slightly curved downward. The final combination of the upwardly curved bottom surface to form a "supercritical airfoil" is the organic combination of the bottom surfaces of the two airfoils, which will generate a certain lift and reduce drag, which is also beneficial to the wing Structural strength and spatial arrangement; the auxiliary lift center provided by the auxiliary wing is behind the center of gravity, and there is also an aileron for adjustment; when normal flight is stopped, the air extraction from the engine can be stopped, and the front of the vortex condensator will naturally forward the air The incoming stream is compressed and supplied The concentrator generates eddy current and lift, and can maintain eddy current and lift to achieve glide when all engines fail, that is, it has excellent unpowered gliding ability; the vector nozzle of the engine and the attitude adjustment jet of the front and rear ends of the body and the tips of the two wings Coordinated together, it provides part of the nine rise and realizes the functions of forward and retreat, yaw, braking, steering and attitude adjustment during aircraft take-off and landing, hovering and low-speed movement; "T" tail can keep it away from the effects of jet flow and vortex Area; the top of the fuselage has a natural "sand dune" shaped front "meniscus fairing", using the so-called "return zone" similar to the combustion technology of aviation gas turbines, which is different from retaining a single vortex on a car airplane, It can protect and retain the two symmetrical vortices formed by the two condensers, but it can also increase the lift force, reduce the loss, and prevent the body's vibration and lift caused by the vortex shedding or the formation of a decoupled vortex to a certain extent. The center is shifted back too far; the plane vortex formed by the gas overflowing from the three-dimensional eddy current when flying at high speed will move backward and eventually disassociate to form a dissociation After withdrawal of the vortex may move after leaving the vortex action surface area, so as to obtain extra lift, the lift and flight center or center of gravity is in focus, a "static stability" of the aircraft;

The "meniscus winglet winglet" can be obtained from the overhead projection surface of the "sand dune" in nature, which is formed by the connection of two upper and lower half-shaped meniscus winglets of different sizes, which can reduce the wing tip. The induced resistance of vortex formation is also small due to its good natural air flow structure. Generally, the upper winglet is larger than the lower winglet in terms of degree and length, and both the upper and lower winglets can be inclined outward at an angle. Can reduce the interference resistance between it and the airfoil surface; the turbojet engine has a certain distance from the airframe, and will not adversely affect the surface skin of the airframe and the flow field at the rear of the airframe; The mixed gas is sent to the natural air compression body along the pipe in the hanger, and the two (or multiple) gases are mixed and expanded by the ultrasonic tube diffuser from the engine air intake port below, and the air flow is divided into two The strand is provided to two vortex condensers. Since it is likely that the airflow at the vortex gas inlet is supersonic and has multiple different sources and velocities, the inlet nozzle of the vortex condensator combines a centrifugal type A variant of the ultrasonic tube diffuser in the compressor to reduce the loss of expansion and mixing, and whether the source air intake is critical to the formation of the vortex fluid; and when any engine fails, it can still be Balance the body and have enough lift to continue to fly. If the engine's jet volume is adequate and the distribution is reasonable, plus the cooperation of the vector nozzle, the vertical landing of a single engine can also be achieved. In addition, the airflow of the engine can be compressed in the natural airflow. A small dedicated auxiliary jet engine is installed at the front to provide a vortex air source during vertical lift, which simplifies the structure of this helicopter, greatly improving economics, safety and reliability. Furthermore, the main engine can be replaced by Turboprop engines, etc. This greatly expands the range of aircraft models that use eddy current condensers; where high temperature gas passes or where gas shock waves are formed, such as mixed gas bows! Flow tubes and involute shapes of vortex condensers The surface of the drainage channel can be made of high-temperature resistant materials and coatings, and the composite of turbine blades can be used by introducing high-pressure cold air from the engine. But technology; aircraft flying subsonic speed usually Gao. As a result, the widely-used subsonic heavy-duty jet transport aircraft has become a helicopter. 3. A saucer-shaped aircraft, as shown in Figure 7-1, Figure 7-2, and Figure 7-3, includes: a top three-dimensional stabilization capsule Jl, an upper rotating capsule J2, and a central plasma thruster and bilayer magnetic field generation. Device J3, lower rotating chamber J4, central stable shaft tube J5, plasma generator and laser fiber device, beach tube and strong magnetic tube J6, upper casing and vortex magnetic field confined plasma eddy current condensator J7, lower inner surface of the outer shell Rotating magnetic field generator J8, head cone fibrillation and negative ion beam J9, head plasma jet J10, head rotating strong magnetic field Jll, head plasma wave cone J12, upper vortex magnetic field J13, pie-shaped outer magnetic field J14, Lower conical inner rotating magnetic field J15, tail plasma jet J16, lower multi-layer densely wound (involute) current-carrying coil J17, lower outer double-hook magnetic head J18, lower star-shaped rod-shaped current-carrying solenoid J19 , Double hook magnetic head J20 at the lower inner edge;

 Its characteristics are: The projection plane of each part of the fuselage is round when viewed from the top or bottom, and the overall side view is the shape of the "flying saucer" in the "UF0", with the two discs snapped together; the top three-dimensional stabilization tank J1 is on the top of the fuselage. Is a spherical body with a low center of gravity and a mass distribution in the form of a "tumbler." It has three dimensions of autonomous rotation and balance capabilities. It can always maintain horizontal stability during flight. It contains a control system and a life support system. The outer wall can be made of "ferromagnetic" material with high magnetic permeability; the upper rotating cabin J2 forms the upper body with the lower part of the top three-dimensional stability cabin J1, and can rotate at high speed by itself, with the central stable shaft J5 as the rotating shaft. For the electromechanical equipment and energy sources, the surface of the body is an upper shell and vortex magnetic field confined plasma eddy current condensator J7, which has a vortex magnetic field confined plasma eddy current condensator and a magnetic confinement electrostatic field ion accelerator that ejects plasma; the central plasma The thruster and pie-shaped outer magnetic field generator J3 is located in the middle of the body, which can stabilize the central axis J5. The structure can be divided into upper and lower layers. There are multiple involute arc-shaped magnetically constrained electrostatic field ion accelerators in the plasma as the flight thrusters. The involute shapes of the upper and lower ion accelerators have opposite rotation directions. On the outer circumference, there are two upper and lower current-carrying conductors and inductive power sources similar to the toroidal solenoid in the "Tokamak device", which can contain and constrain the high-speed ion current generated by the upper and lower accelerators. Ion jet nozzles; the lower rotating cabin J4 is the bottom of the body, which can rotate at high speed, with the central stable shaft tube J5 as the rotating shaft, the internal electromechanical equipment and the engine, etc., the surface of the body is the lower shell »shaped inner rotating magnetic field generator J8, Inside there are multiple layers of densely wound (involute) shaped current-carrying coils J17 and star-shaped rod-shaped current-carrying solenoids J19;

The central stable shaft tube J5 is the rotating shaft of each rotating cabin. Generally, it does not rotate at the position of the central axis of the fuselage. It is in the shape of a hollow circular tube. There are multiple magnetic suspension bearings isolated and connected to each cabin. The hollow interior can be A channel for communication control and maintenance activities, there are a variety of photoelectric interfaces, rattan, control systems and movable cabin doors, etc., the outer wall of the tube side can have "ferromagnetic" materials with high magnetic permeability; plasma generators and lasers; And shock tube and ferromagnetic tube J6 in the front part of the middle fiber, which is composed of multiple layers of densely wound current-carrying solenoid and "ferromagnetic" material core to form a strong magnetic tube to generate a strong magnetic field, and a laser Emitters, ion jets, etc .; there may be multiple suction ports distributed in a ring around the top of the upper rotating cabin and the central stable shaft tube, which are provided for Generate the gas required for lift and propulsion; the cone laser and anion beam J9 at the head of the flight flow field. The laser and anion beams emitted by the plasma generator and laser emitter and shock tube and strong magnet tube J6 are both In a conical shape, a small beam of head plasma jet J10 is emitted immediately from its central axis, and the head plasma # ^ wave cone J12 is excited, and the magnetic field lines of the head rotating strong magnetic field J11 formed by the ferromagnetic tube J6 Cut the plasma sickle cone; the pierin layer magnetic field J14 is in the layer of the medullary field, and the magnetic field lines are sent by the central plasma thruster and pie-shaped outer layer magnetic field generator J3 to reach the top and bottom of the body respectively; the upper vortex magnetic field J13 is closely attached The surface of the upper rotating ship J2; the lower conical inner rotating magnetic field J15 is close to the surface of the lower rotating cabin J4; the tail plasma jet J16 appears in the middle plasma reactor and the outer outer magnetic field generator J3 has a rear edge After a plurality of nozzles arranged in a wide range; the lower multi-layer densely wound (involute) current-carrying coil J17 and the lower star-shaped current-carrying solenoid J19 jointly generate the lower conical inner rotating magnetic field J15, magnetic An outer edge line by a lower hook-shaped head reaches the starting edge of the hook-shaped head J20 J18 at the lower part;

This disk-shaped aircraft uses the magnetic force of the sprayed plasma in the upper rotating capsule shell to constrain the electrostatic field ion accelerator to generate a vortex magnetic field on the upper surface, and also accelerates and ejects the plasma stream. The vertical component of the vortex magnetic field and the ion current Intersecting cutting produces a "Lendz force", plus a solenoid-shaped magnetic field formed by the superposition of the parallel component and the coil-shaped magnetic field of the induced current in the plasma flow circuit, which collectively adsorb, constrain and twist the plasma flow to form There is an "ion spiral vortex" in the central plasma fiber. There is an ion accelerator in the central plasma fiber. During the flight, the high-speed ions are ejected backwards to generate thrust. At the same time, the magnetic field lines of the solenoid are at the edge of the central ring. Dense, the other end is guided by the outer wall made of "ferromagnetic" material in the central stable shaft tube and the top three-dimensional stability capsule, and then appears concentrated on the top and bottom of the body. The closed magnetic lines form a pie-shaped outer magnetic field, which produces The "magnetic mirror effect" constrains and absorbs the plasma shock wave; the surface of the lower rotating cabin has a cone-shaped inner rotating magnetic field generator. The lower rotating cabin rotates the conical inner magnetic field during rotation, and its magnetic field lines cut the plasma at high speed to subject it to "Lorentz force", so as to absorb and restrain the plasma shock wave; the plasma generator, the shock fiber device, and the shock wave The tube and ferromagnetic tube are in the front of the middle ¾a device. During super-flying, a cone laser, even a high-energy X-ray laser and a gamma ray, heat and excite the air in front, and then eject a large number of high-speed negative ions (electrons ) Stream, which ionizes the excited hot air into a plasma, and can mix and emit a small amount of positive ion current in the negative ion stream, which excites the air in front to form a cone-shaped plasma shock cone, so that the tube itself is behind this shock cone and thus It will not be overheated and generate a strong magnetic field as a strong magnetic tube, which will distort the plasma shock surface due to the "magneto mirror effect" constraint, and reduce the longitudinal velocity and increase the lateral velocity. Ideally, this shock surface and its The subsequent decelerated air is in a plasma state, and the magnetic field of this strong magnetic tube can also be rotated at a high speed, and the rotating magnetic lines of force cut the front plasma. The shock cone makes it subject to the "Lorentz force" and further shrinks and twists inward, thereby changing the shape of the shock surface. In general, the front plasma shock can be artificially generated actively during the flight of the spinal cord and can be passed through The electromagnetic force controls its shape, which can reduce the intensity of the shock wave, further "soften" the shock wave, and reduce the shock resistance. Force, reducing leading edge heating, and improving super-flying performance. It must be particularly required that the magnetic field formed by the strong magnetic tube and the forward shock cone intersect, and the direction of the magnetic field lines is approximately parallel to the cone surface, that is, the intersection angle is small. At the time, the shock cone will be contracted inwardly (or expanded by the Lorentz force); during flight, the central device only rotates when turning, generally ejecting the plasma backwards, and the upper part The lower rotating cabin and the lower rotating cabin each rotate in opposite directions. The vortex magnetic field of the upper rotating cabin itself rotates at a high speed to become a rotating magnetic field, and the conical magnetic field of the lower rotating cabin also becomes a rotating magnetic field due to the rotation of the cabin body;

During hovering, both the upper and lower spin chambers stopped rotating. The upper spin chamber did not accelerate ions, but was still used to generate a vortex magnetic field. The ion thruster ejected a stream of ions in the ring direction, generating a "spiral spiral plasma." Vortex "to obtain the hovering lift force, and the central thruster is rotated by the reaction force. If you want to hover at a low air pressure, you can make the small jets on the peripheral edge of the central thruster spray the ion stream downward to generate a reaction force. The small nozzle is also an attitude adjustment system for the entire flight range; the center of gravity of the aircraft is at the center of the central thruster, and the mass distribution of the aircraft is in the form of "not falling ^", that is, the weight of the upper and lower parts of the aircraft is equal, and the rotational directions are opposite, and the moment of inertia It is also equal. Because of the huge moment of inertia generated by the high-speed rotation of the upper and lower stern carcasses, its stability during high-speed flight is guaranteed; all conductors can be superconductors; each cabin is separated and connected by magnetic suspension bearings. ; The inner walls of all cabins have a superconducting magnetic insulation layer, and the shells of all cabins have a heat insulation layer and an electrostatic layer. The electrostatic layer of the shell is negatively charged to attract and withstand the impact of positive ions, the electrostatic layer of the lower shell is positively charged to repel positive ions, and the front edge of the central thruster is negatively charged to attract positive ions to change the shape of the front shock surface. The trailing edge is positively charged to repel positive ions, prevent the positive ions from jetting back, and the body is electrically neutral. The plasma and magnetic field are subject to "Lorentz force" when they rotate relative to each other and have centripetal acceleration. Ions will radiate electromagnetic waves, so-called "cyclotron radiation", which can produce a luminous phenomenon, and because of being surrounded by the plasma, the smart radar detects stealth; when the flying angle exceeds ¾, the front-end shock tube first generates a shock cone, which is strongly magnetic. The tube generates a rotating strong magnetic field. This plasma shock is constrained by the front-end rotating strong magnetic field and the pie-shaped outer magnetic field surrounding the entire body. The "Lendz force" and "magnet mirror effect" gradually reduce the velocity component of the charged ions in the parallel direction, and gradually increase the velocity component in the lateral direction. Under the attraction of the negative charge on the leading edge of the central thruster, the positive ions When the front edge of the body is squeezed inward, the original wave cone is distorted and deformed, so that the shock surface is propagated backwards and spreads close to the front edge surface of the body. The plasma vortex speed under the constraint of the rotating vortex magnetic field on the upper surface of the body can be It is super ¾¾ ', but it will not cause shock waves within the vortex itself and the outer boundary layer. Because of the cutting by the rotating vortex magnetic field, the front plasma shock surface will be closer to the body surface due to the "Lorentz force". However, the distortion and deformation, the entire externally formed plasma shock surface finally forms close to the surface of the eddy current, or the surface of the eddy current is surrounded by the surface of the shock, and the surface of the shock also strengthens and constrains the eddy current, reducing the diffusion and loss of the eddy current. And the shock wave will be gradually decomposed and mixed by the plasma eddy current, and eventually become a component of the eddy current; On the lower surface of the body, the plasma shock surface is cut by the rotating conical magnetic field, and is brought into close contact with the lower surface of the body due to the "Lorentz force". The lower compartment can be positively charged to repel positive ions, and the body The original surface layer between the surface and the shock surface is formed as a thin "low-density isolation layer", which can insulate and reduce friction and increase the Reynolds number, and because of the positive charge on the lower surface and the negative charge on the upper surface On the contrary, it helps to balance the charge on the surface of the body, but the lower surface is not affected by the shock surface because of the "low-density isolation layer", but is constrained by the "magnetic mirror effect" of the pie-shaped outer magnetic field and the cone The "Lorentz force" of the rotating magnetic field causes the shock surface to be twisted into a flat cone close to its lower surface, so the pressure on the lower surface is more uniform, and they are still affected by the high pressure of the shock surface, that is, The so-called "shock compression lift" is obtained by using the lower shock surface. In addition, the upper shell of the body is separated by the plasma eddy current. The upper body is not affected by the high pressure of the shock surface but is high. The negative pressure generated by the eddy current, so as to obtain all the lift required for supersonic flight; this lower shock surface was finally twisted and constrained by the common outer magnetic field of the pie-shaped magnetic field and the rotating magnetic field of the conical inner layer, and finally propelled from the middle The rear edge of the device conducts and diffuses outward (backward) in a horizontal direction, so the shock waves formed in the front will not cause a sound explosion due to downward conduction; the "magnetic mirror effect" of the pie-shaped outer magnetic field is mainly reflected in The longitudinal component of the velocity of the plasma shock wave in the conduction of the first half of the body is reduced and the transverse component is increased, that is, the shock wave is brought closer to the surface of the body, causing distortion, passing through the half-line of the body or passing another magnetic pole ( After the cone apex), the longitudinal component of the shock velocity increases and the transverse component decreases, and finally conducts and diffuses horizontally along the rear edge. This situation is the same for the lower or upper shock, and the lower part The "Lorentz force" of the conical rotating magnetic field also firmly grasped the shock surface of the lower part, making it closer to the surface of the body and becoming a complete "attached wave"; relatively speaking, superb ^时 压 压 plasm ## The front of the body is permanently stagnant, so the rotation of the upper and lower rotating magnetic fields causes the plasma to cut the magnetic field lines at a constant speed. When the magnetic field polarity is constant, the direction of rotation of the rotating magnetic field determines whether the heavy ions in the plasma are attracted by the bow or Is excluded

When the ions of the central thruster accelerate the backward jet of the plasma, a strong magnetic field can be formed in the jet at the same time. The magnetic field lines are parallel to the direction of the ion velocity, pinching the tail jet, and using the mechanism of the "Tokamak device" in the plasma. The induced potential is formed in the body, and the strong positive charge area near the tail jet slows down the negative charge (electrons) and eventually forms a "space charge region" at the end of the tail jet, which helps the induced potential to form a sense in the plasma. The current is generated, so that the tail jet is further pinched, and the velocity of some of the injected electrons is much higher than that of the positive ions. The small size of the electrons and the ability to escape easily make it able to catch up with the jets far behind. Molecules that have become neutral are "ionized" by high-speed electron impact and re-ionized. They can still maintain the plasma state, thereby maintaining a high pinch state, until the tail jet velocity is reduced to subsonic speed, and it can also be at the nozzle. A high-speed rotating strong magnetic field generated by the strong magnetic tube in front is added, and a ring-shaped ion nozzle is formed on the circumference of the magnetic head, so that the magnetic field lines rotate to cut the plasma, so that Shrinked by the "Lendz force", and has a focus point farther away from the tail, which further prevents the jet from expanding laterally. With so many methods and measures, it greatly reduces the jet shock and weakens the sound. Burst 1 Silent supersonic flight is finally achieved; changes in direction and attitude during flight can be achieved by numerous small nozzles on the outer edge of the central thruster; due to the view, all surfaces of the front, back, left, right, and up and down are covered by a layer of shock surface Therefore, the pressure on the upper and lower surfaces of the body is more uniform and close, which means that the pressure difference between the front and rear parts of the body is not large, so the pressure difference during flight

(Shape) The resistance is very small, and the total resistance is mainly small friction resistance, so its acceleration performance is particularly good. From the perspective of 3¾, the upper surface of the body isolates the shock surface with eddy currents, and because the upper surface is an upward convex Conical surface instead of flat surface, the centrifugal tendency of the eddy current to diffuse outward makes the surface layer on the upper surface of the body very thin and low density, while the lower surface of the body isolates the shock surface with a "low density isolation layer", so the entire body surface The frictional resistance is small and the heat insulation effect is good; the supersonic flight of the entire aircraft is like a stone rotating on the water surface when it floats on the water or the surfboard glides; except that charged ions are accelerated in a strong magnetic field due to "cyclotron radiation" In addition to radiating electromagnetic waves, which produces a strong light phenomenon, when the plasma eddy current eventually loses the constraint of the magnetic field because it changes back to neutral gas, and thus overflows at the edge of the aircraft, a true "tornado" will form in the lower part of the aircraft. When it is lifted off, it will be accompanied by a strong wind. When it flies over or hovering over the desert, snow field, or sea, it will cause sandstorms and snow cyclones. , Giant waves and water columns, coupled with the strong and rotating non-rotating magnetic fields inside and outside, when it passes over a vehicle (box) at a low altitude, it will lift (traction) and affect all "ferromagnetic" substances, these The phenomenon will be exactly the same as the characteristics of the legendary "flying saucer"; the speed of the aircraft can be super high ¾, the energy can be nuclear energy, and the air can be liquefied and stored as an ionizing propellant to achieve single-stage orbit, moon roundtrip, and interplanetary travel When it re-enters the atmosphere, the lower dish-shaped surface with a large area of cone-shaped protrusions is particularly conducive to deceleration. The surface's rapidly rotating cone-shaped magnetic field and positively-charged electrostatic field make it repel plasma. The characteristics of the body are also more conducive to resisting aerodynamic heating. The huge moment of inertia obtained by rotating the upper and lower parts of the body also ensures the attitude and direction stability during re-entry; due to the unique principle and structure of its new vortex fluid and new ion accelerator And functions, so that the upper, middle and lower parts can be transformed into separate dish or circular aircraft after modification, and make the ball and circle The shaped part can also fly alone after being similarly modified, then a large aircraft can be composed of multiple small aircraft, and it can achieve stable separation and combination in the air; this type of aircraft has initially revealed the historical principles "The Mystery of UF0".

Claims

Rights request  1. A method for manufacturing a three-dimensional eddy current, characterized in that, under the action of a spirally wound eddy current condensator, a fluid (gas or plasma) is rectified through a rectifying channel to form a three-dimensional eddy current.  2. A spirally annular eddy current condensator according to claim 1, wherein the rectifying channel comprises a bottom plate (Al), a bottom vortex track (A2), a side gas pressure panel (A3), and a top torsion surface (A4). It is characterized in that: the bottom plate (A1) is a circular (conical) disk surface, the upper surface has one or more bottom vortex orbits (A2), and the bottom vortex orbits (A2) form a circular ring around the center of the bottom plate (A1) Arrangement; the outer edge of the bottom vortex track (A2) is equipped with a side air pressure panel (A3), which can be rotated or fixed or naturally extended from the bottom vortex track (A2) to the outside; side A top torsion surface (A4) is installed in the middle and upper part of the gas compression panel (A3), and the top torsion surface (A4) can be rotated or fixed or naturally extends upward from the side gas compression panel (A3).  3. A spirally annular eddy current condensate according to claim 2, characterized in that: the bottom vortex orbit (A2), the side gas pressure panel (A3), and the top torsion surface (A4) The inner surface of the vortex is composed of air swirling rifling (A5) or vortex generator. The preferred solution is air swirling rifling (A5). The inner surface of the bottom vortex orbit (A2) is inclined from the inner edge to the outer edge along the airflow The air swirling rifling (A5) is drawn, and the inner surfaces of the side air pressure panel (A3) and the top twisting surface (A4) are scoring the air swirling rifling (A5) obliquely upward from the lower direction along the air flow direction.  4. A spirally annular eddy current condensator according to claim 3, characterized in that the shape of the airflow rotating rifling (A5) is the same as the rotating rifling on the inner bore of the gun or barrel; and the vortex generating sheet is The eddy current generating sheet on the existing fixed-wing aircraft has a sheet structure, and the eddy current generating sheet is arranged on the inner surface of the rectifying channel in the same manner as the airflow rotating rifling (A5), and can be used in the same position in the front and rear direction in the same manner. Arrange multiple pieces of the same vortex, but in the cross section, only one vortex can occur on the inner surface of the bottom vortex track (A2), the side pressure panel (A3), and the top torsion surface (A4). Sheet; wherein the airflow rotating rifling and the vortex generating sheet are separately or both installed on the inner surface of the rectifying channel.  5. A spirally annular eddy current condensator according to any one of claims 2 to 4, characterized in that: the bottom vortex track (A2), the side gas pressure panel (A3), and the top torsion surface (A4) The cross-sectional shape of the inner surface of the three is a smooth convex curve; the preferred plan of the cross-sectional shape of the inner surface of the bottom vortex track (A2) and the side pressure panel (A3) is a circular arc segment, and the top A preferred solution of the cross-sectional shape of the inner surface of the torsion surface (A4) is an involute (spiral) segment. 6. A spirally annular eddy current condensator according to claim 5, characterized in that the bottom vortex orbit (A2) of the house ¾ is composed of an annular groove (A21), and the side pressure panel (A3) is made of compressed air. The blade (A31) is composed, and the top torsion surface (A4) is composed of the airflow torsion section (A41); the whole of the annular vortex condensate is rotated around the central rotation axis (A6). 7. A spirally annular eddy current condensator according to claim 5, characterized in that: the bottom vortex orbit (A2) is composed of an annular groove (A22), and the side pressure panel (A3) is made of compressed air. The side rail (A32) is composed, and the top torsion surface (A4) is composed of the airflow torsion section (A42); the whole of the spiral annular vortex condenser is a fixed form.  8. A spirally wound eddy current condensing device as claimed in claim 1, wherein the rectifying channel comprises a bottom plate (Al), characterized in that: the bottom plate (A1) is a circular (conical) disk surface, and there is one or one on the upper surface. The above bottom vortex orbit (A2) is arranged in a circular ring shape around the center of the bottom plate (M; a plurality of inner edge ions and The magnetic field line nozzle (C3); a plurality of outer ion and magnetic field line nozzles (C4) are distributed in a circular ring shape on the edge of the vortex track (A2) at the bottom; an induction coil (C5) is arranged around the center of the bottom plate (A1).  9. A spirally annular eddy current condensator according to claim 8, characterized in that the bottom eddy current orbit (A2) of the household is composed of a vortex magnetic field (A23), and the inner edge ion and magnetic field line nozzle (C3) is formed by the inner The edge opening (C31) is composed, the edge edge ion and magnetic field line nozzle (C4) is composed of the edge edge opening (C41), and the induction coil (C5) is composed of the center induction coil (C51); in the inner chamber of the bottom plate (A1) An ion accelerator set (C2) is arranged.  10. A spirally annular eddy current condensator according to claim 9, characterized in that the ion accelerator set (C2) is a plurality of spiral-shaped tubular objects with multiple involutes (spirals) The form is distributed along a circular ring; the internal nozzle of the ion accelerator set (C2) near the center of the base plate (A1) is used as the inner edge opening (C31); the ion accelerator set (C2) is located near the outer edge of the base plate (A13). As the outer edge opening (C41); the inner edge opening (C31) and the outer edge opening (C41) respectively protrude from the surface of the base plate (A13) through the ion accelerator set (C2) and are diagonally opposite, and the inner edge opening (C31) The oblique points along the circumferential tangent point outwards, and the outer edge opening (C41) obliquely points inward along the circumferential tangent line; the smooth connecting lines between the inner edge opening (C31) and the outer edge opening (C41) are in a spiral shape with multiple involutes distributed in a ring shape The magnetic field formed between the inner edge opening (C31) and the Xib edge opening (C41) becomes the vortex magnetic field (A23). The vortex magnetic field (A23) is a vortex distributed in a circular shape in the form of a multi-involute (spiral). Shape; the central induction coil (C51) is arranged around the center of the vortex fluid.  The spiral annular eddy current condensate according to claim 10, wherein the inner edge opening (C31) and the rim opening (C41) both have reverse negative ion nozzles, and the reverse The negative ion ejected from the negative ion nozzle is opposite to the positive ion ejection direction. 12. A spirally annular eddy current condensate according to claim 6, characterized in that the shape of the cross-sectional curve of the inner surface of the annular groove (A21) is a circular arc segment; the compressor blade (A31) The shape of the cross-section of the inner surface is a circular arc segment; the compressor blade (A31) can rotate around its own rotation axis (A311), and the range is a plus or minus 90 degree angle; the airflow torsion section (A41) is located on the compressor blade (A31) The upper part of the compressor blade (A31) naturally extends from the middle and upper part of the compressor blade (A31) and is functionally separated. The starting point of the tangent line of the cross-section curve of the inner surface of the compressor blade (A31) is the vertical line. Compressor blade (A31) The tangent of the cross-section curve of the inner surface is at the end of the horizontal line, and the entire curve is involute (spiral); the curve begins with the curvature of the cross-section curve of the inner surface of the original compressor blade (A31). The tangent of this curve is horizontal at the apex of the torsional pressure section (A41), and the curvature of this curve is also the largest, that is, the curve is involute (spiral). 13. A spirally annular eddy current condensator according to claim 6, characterized in that the cross-sectional plane of the air flow torsion section (A41) and the air pressure blade (A31) in the vertical direction ¾ j square upward The shape is a meniscus with a thick middle in the middle of the two tips; or the vertical cross-sectional plane shape of the air pressure blade (A31) and the air torsion section (A41) is a meniscus with a thick middle in the two tips, 7j <The cross-sectional plane shape in the flat direction is also a meniscus-shaped individual with a thick middle between the tips.  14. A spirally annular eddy current condensator according to claim 6, characterized in that: the inner chamber of the bottom plate (A1) has a pitch moment adjusting mechanism (A7), and the main control part is on the bottom plate The center of (A1) controls the action and rotation angle of the compressor blade (A31), and the blade shaft (A311) is controlled by the paddle torque adjustment mechanism (A7).  15. A spirally annular eddy current condensate according to claim 7, characterized in that the shape of the cross-sectional curve of the inner surface of the annular groove (A22) is a circular arc segment; the compressed side rail (A32) The horizontal cross-sectional curve shape of the inner surface is a circular arc segment; the compression side rail (A32) is a fixed form; the air flow torsion segment (A42) is located above the compression side rail (A32), and the middle of the compression side rail (A32) The upper part naturally extends and is separated separately in function. The starting point is the tangent to the horizontal cross-section of the inner surface of the compressed air rail (A32) as a starting point, and the inner surface of the compressed air rail (A32) is transversely cut. The tangent of the curve is at the end of the horizontal line, and the entire curve is involute (spiral); the curvature of the transverse 咅 観 curve of all the inner surfaces of the flow torsion section (A42) from the leading edge to the trailing edge of the wind changes. Similarly, they are all involute (spiral); the air flow section (A42) and the air pressure side rail (A32) are curved involute (spiral) curved panels as a whole. 16. A spirally annular eddy current condensator according to claim 7, characterized in that: an involute groove (A23) is provided on the periphery of the annular groove (A22), and the air inlet and the The air outlet of the open-line groove (A23) is smoothly connected; the structure of the involute-shaped groove (A23) is similar to the structure of the annular groove (A22), and also has a compressed air side rail (A32) at the outer edge and an air flow torsion at the upper portion. Paragraph (A42).  17. A spirally annular eddy current condensate according to claim 7, characterized in that: the air inlet of the annular groove (A22) is provided with a jet flat tube (B5) or a spiral dedicated to the combustion chamber of the engine. The shape of the airflow generating device, the flat gas pipe (B5) or the spiral airflow generating device, the velocity of the gas is subsonic. 18. A spirally annular eddy current condensate according to claim 16, characterized in that: an air inlet flat of the involute groove (A23) is provided with a jet flat tube (B5) or dedicated for the combustion chamber of the engine The speed of the gas ejected from the involute groove (A23) of the spiral airflow generating device is subsonic. 19. The application of a spiral ring eddy current condensate according to claim 6, characterized in that: a vortex condensate (HI) is installed on the top of the car, and a vortex condensate (H2) is installed on the bottom of the car; (HI) Rotation is driven by a stator rotary electric motor (or rotary-cylinder radial piston engine) (H301) at its center; eddy current condenser (H2) is driven by a stator rotary electric motor (or rotary-cylinder radial star) at its center Piston engine) (H302) is driven to rotate; a booster cover plate (H31) is installed above the bottom vortex condensate (H2); the top vortex condensate (HI) and the bottom vortex condensate (H2) rotate in opposite directions. 20. The application of a spiral-wound annular vortex condensator according to claim 7, characterized in that: the back or bottom of the aircraft casing (The preferred solution is the back) Two eddy current condensers (11) are installed side by side, and the curve form of the involute grooves on them is involute (spiral), and the left and right vortex condensers have involute concaves. The involute (spiral) shapes of the grooves rotate in opposite directions, and the vortices inside them also rotate in opposite directions, and the air inlets are juxtaposed with each other in front of the center of the back or bottom (preferably the back) of the aircraft casing.  21. The application of a spiral ring-shaped vortex condensator according to claim 9, characterized in that: a rotary cabin (J2) is provided on the body of the dish-shaped aircraft, and the surface of the rotary cabin (J2) is negatively charged. The upper casing of the spin chamber (J2) is equipped with a vortex magnetic field confined plasma eddy current condensator (J7).  22. A spirally wound eddy current condensator according to claim 9, characterized in that: said ion accelerator set (C2) is formed into a plurality of solenoid-shaped tubular objects with multiple involutes (spirals) ) Form a vortex shape distributed along a circular ring, a single tube is a magnetically constrained electrostatic field ion accelerator that ejects plasma; its outer layer is a solenoid-shaped wire; its solenoid conductor (D1) is on the accelerator The outermost layer, the turns are tightly connected; the outer electrode charging wire (D2) is connected to each external electrostatic field electrode (D3), and is distributed at uniform intervals in the space; the electrostatic field electrode (D3) and the internal electrostatic field The electrode (D5) is on the outer and inner side walls of the positive ion channel (D4), respectively; the positive ion channel (D4) is in the electric field space formed by the external electrostatic field electrode (D3) and the internal electrostatic field electrode (D5), and is a tube Shaped channel structure; the inner electrode charging wire (D6) is connected to each inner electrostatic field electrode (D5), and is distributed at uniform intervals in space; the round pipe-shaped conductor (D7) is a round pipe structure at the center of the solenoid , The center is the negative ion channel (D8); The electrode (D3) and the internal electrostatic field electrode (D5) are gradually distributed from the high voltage at the inlet to the low voltage at the outlet in the form of a step voltage. The inner and outer electrodes are staggered at the front and back edges, and the voltage gradients are staggered with each other, forming a unique "Oblique door-to-door gradient gradient electrostatic field", the internal and external electrostatic field electrodes are circular tube structures, and the distribution order of the gradient voltage from the front entrance to the rear nozzle is: the highest voltage is on the outer electrode tube at the entrance, passing through the entire electrode After the length of the tube, add the second-stage voltage to the inner electrode tube, and after the entire length of the electrode tube, add the third-stage voltage to the outer electrode tube, and so on. 23. The application of a spirally annular eddy current condensate according to claim 19, characterized in that: a movable windshield is installed above the body of the automobile in front of the outer surface of the fixed windshield of the automobile (H13); movable windshield (H13) and The size and shape of the fixed windshield are similar, and there are movable windshield rail pulleys (H24) and movable windshield telescopic arms (H25) on both sides; during ground driving, the movable windshield protrudes to the front and lower of the nose, Models in which the body is constructed as a "wedge" in tandem with the fixed windshield; when flying, the movable windshield is retracted before the fixed windshield.  24. The application of a spiral-wound annular eddy current condensate according to claim 19, characterized in that: the upper and lower sides of the rotating stators of the stator rotating motors (H301) and (H302) of the automobile are fixed Centripetal heat-dissipating gas turbine (H32), which is also fixedly connected to the bottom plate of the eddy current condenser; the turbine blades are involute (spiral), with compressed gas exhaust channels in the middle, and the entire turbine is oblate with open edges Box structure; the mass of the rotating part of the motor is greater than that of the fixed part.  25. The application of a spiral-wound annular eddy current condenser according to claim 19, characterized in that: the automobile has a telescopic tail frame (H12), and the telescopic tail frame (H12) is a pneumatic or electric telescopic type Frame beam structure; telescoping tail frame has telescoping tail air vents (H27) at the tip of the telescoping, the air jets have multi-directional rotation ability, ¾ the telescoping tail frame is covered by telescoping stackable cloth (Η29); during flight The telescopic tail frame (H12) is extended and slightly tilted upwards. The telescopic tail is a wedge shape as a whole; the longitudinal section of the combination of the entire body and the telescopic tail is an "S" shaped airfoil structure of the aircraft wing. When driving on the ground, the retractable tail retracts into the retractable tail storage room (Η36). 26. The application of a spirally annular eddy current condensate according to claim 19, characterized in that: the car has a dune-shaped fairing (H14); the fairing is a thin-wall curved panel in the shape of a "sand". Xi structure, Xi Bu form "sand dune" shape, its top projection surface is like "meniscus" shape.  27. The application of a spirally annular eddy current condensator according to claim 20, characterized in that: the aircraft has an air inlet (12) which is a natural incoming flow in front, and the air inlet (12) is similar In the air inlets of today's supersonic aircraft, the lips are beveled, and the internal upper surface is provided with a compression swash plate for compressed air. The tilt angle is adjustable. There is an airflow shroud at the rear of the interior. There is an engine airflow inlet below. The tail nozzle of the main engine is connected. At this time, the main engine is a turbojet engine; a small dedicated auxiliary jet engine can be additionally installed in the front of the engine air intake port in the natural air inlet (12) to provide the jet to the vortex condensate. At this time, the main engine may still be a turbojet engine, or a turboprop engine may be used instead. 28. The application of a spirally annular eddy current condensate according to claim 20, characterized in that: the aircraft has a meniscus fairing (15); the fairing is a thin-walled bend in the shape of a "sand dune" The panel structure is located at the top of the leading edge of the vortex condensate and is combined with the top of the air inlet (12). As a front shield for the two vortices, the shape of the fairing is a natural "sand dune" shape. A slightly flat, hollow, drop-shaped streamline is replaced by another larger cylinder (or sphere Body or waterdrop-shaped streamline body) cut from the front or middle part of the remaining body and take half of it, and its top projection surface is like the same round of "meniscus".  29. The application of a spirally annular eddy current condensator according to claim 20, characterized in that: the aircraft has a vortex retention surface (19) with a plate structure, the vortex retention surface is curved downward and is in two vortex currents The width of the trailing edge of the condenser is similar to that of the vortex condenser.  30. The application of a spirally annular eddy current condensator according to claim 20, characterized in that: the rear end of the wing tip of the aircraft has a meniscus-shaped winglet (110), Half "meniscus" shaped winglets are joined.  31. The application of a spiral annular vortex condensate according to claim 30, wherein the upper winglet of the aircraft is larger than the lower winglet in height and length, and both the upper and lower winglets are inclined outward. 32. The application of a spirally annular eddy current condensator according to claim 21, characterized in that: a central part of the dish-shaped aircraft has a plasma thruster and a pie-shaped outer magnetic field generator (J3), Rotate around the central stabilization shaft tube (J5).  33. The application of a spiral-wound eddy current condensator according to claim 32, characterized in that: the magnetic field generator (J3) has two upper and lower layers in structure, and a plurality of involute spray plasmas are arranged therein The body's magnetically constrained electrostatic field ion accelerator acts as a flying thruster. The involute shape of the ion accelerator on the upper and lower layers has opposite rotation directions, and there are energized conductors and induced power sources of the upper and lower annular solenoids at the outer circumference.  34. The application of a spirally annular eddy current condensator according to claim 21, characterized in that: the bottom of the body of the dish-shaped aircraft has a rotating capsule (J4), the surface of which is positively charged, and its direction of rotation and The opposite of the upper rotating cabin (J2), the moment of inertia is the same as that of the upper rotating cabin (J2); a rotating magnetic field generator (J8) is installed in the lower part of the body shell, and a lower multilayer densely wound ring (involute) is located inside the rotating magnetic field generator. ) -Shaped current-carrying coil (J17), the rotating magnetic field generator (J8) has a lower star-shaped current-carrying solenoid (J19).  35. The application of a spiral-wound annular vortex condensator according to claim 21, characterized in that: a plasma generator, a laser inch device, and a laser Wave tube and strong magnetic tube (J6), the shape is round tube, or flat tube with wide mouth.