CN1718504A - High speed remote voyage natural gas airship - Google Patents

Abstract

The high-speed and long-range natural gas blue sky spacecraft is equipped with at least two groups of buoyancy gas containers—soft balloons or soft and hard balloons. Different balloon groups are connected by pipelines. Pressure pumps and inflation and deflation valves are connected in series on the pipelines, relying on inflatable balloons. Generate buoyancy; the lower part of the buoyancy device is connected to the manned or manned and loaded container; the balloons of the aircraft include fuel balloons and buoyancy balloons; the aircraft uses the fuel gas in the fuel balloon as the energy to generate power to propel the aircraft and support the operation of the aircraft; The gas in the buoyancy balloon generates upward lift; the fuel and the gas in the buoyancy balloon are natural gas, etc., and a fire barrier is set between the "fuel balloon and the combustible gas buoyancy balloon" and the rest; when the equipment burns, the combustible balloon will automatically break away from the protection of the aircraft device. It has an inflation mechanism that can generate buoyancy when the combustible balloon leaves the aircraft. The invention is particularly suitable for use as a fast personal flying tool, and a high-speed, long-distance civil aviation vehicle.

Description

High-speed long-range natural gas blue sky spacecraft

1. Technical field

The present invention is a high-speed long-range natural gas blue sky spacecraft (hereinafter referred to as the present invention), which belongs to the balloon aircraft technology in the field of aviation technology—airship technology.

2. Background technology

In the era of the rise of aircraft aviation and the complete occupation of the aviation industry, from the 1970s, the inflatable aircraft—airship aviation began to recover again. On the one hand, this is because new material technology and control technology can improve the defects of airships in history, so that airships have the ability to compete with aircraft aviation in terms of load capacity, shipping cost, and safety; the more important deep-seated reasons are: The shortage of energy and oil in the world is becoming more and more serious, and the aircraft and aviation industry, which consumes huge amounts of oil, is also facing a serious crisis. Once the oil is exhausted, all existing aircraft will become a pile of waste.

The recovering inflatable airship has not developed fast for decades, and it is far from entering civil aviation and other practical aviation fields in large numbers, because there are still some shortcomings in safety and practicality, especially the flexibility to control the movement in all directions in the air It is not yet perfect, and the energy consumed is still basically petroleum products. Inflatable blue sky spacecraft using solar energy is difficult to obtain high speed and long cruising range due to low energy density and energy supply affected by weather and day and night. Carrying fuel as an energy source, because the fuel occupies the payload of the aircraft, it is impossible to reserve enough energy for high-speed and long-distance voyages. The inflatable blue sky spacecraft using hydrogen energy fuel, although the hydrogen will not occupy the effective load of the aircraft, and can generate buoyancy due to the hydrogen; but because the fuel consumption has too much influence on the buoyancy change, it is difficult to achieve effective regulation of the buoyancy, which greatly The amount of hydrogen energy carried is limited, which greatly limits the speed and endurance of the aircraft.

3. Contents of the invention

Purpose of the present invention will design and manufacture high-speed long-distance natural gas blue sky spacecraft exactly. And it is based on the existing technologies including the invention of "solar controllable buoyancy, self-controlled and stable helium blue sky spacecraft" and the invention of "safe hydrogen buoyancy, hydrogen fuel blue sky spacecraft".

In the present invention, the inflatable blue sky spacecraft carries and uses natural gas and similar gases, including natural gas, petroleum gas, catalytic cracking or relatively pure methane, butane, acetylene, ethylene, propylene, butene, ethane, propane, butane, etc. Using non-hydrogen combustible gas as fuel can successfully solve the problem of carrying a large amount of fuel in the inflatable blue sky spacecraft, thereby realizing high-speed and long-range endurance of the inflatable blue sky spacecraft. This is because the density of non-hydrogen combustible gases such as natural gas is generally lower than that of air, but much higher than that of hydrogen and helium commonly used as buoyancy gases, which allows buoyant aircraft to carry a large amount of fuel without increasing the load of the aircraft burden without causing too much disturbance to the buoyancy of the buoyancy balloon.

Under the situation of shortage of petroleum energy, the use of natural gas and other transitional energy is an effective strategy. The present invention uses natural gas and other non-hydrogen gas fuels for the inflatable buoyancy aircraft, which can greatly increase the quantity of fuel carried per unit flight load, and realize high-speed and long-distance flight of the inflatable buoyancy aircraft. The main purpose of the present invention is just here.

In order to solve the safety problems of carrying fuel balloons and choosing combustible gas buoyancy balloons, the present invention uses related technologies in "Safe Hydrogen Buoyancy, Hydrogen Fuel Blue Sky Spaceship", that is: not only two kinds of fire barriers-space separation , or fire extinguishing partition wall; and equipped with an automatic protection device that quickly releases the fuel balloon and selects the combustible gas buoyancy balloon to connect with the rest of the aircraft when the high temperature is caused by the leakage of combustible gas. After the fuel balloon and the selected combustible gas buoyancy balloon are separated from the rest of the aircraft due to failure, the rest of the aircraft can rely on other remaining buoyancy-generating inflatable mechanisms (helium balloon or umbrella bag) to continue floating or glide to achieve a safe landing.

The controllable buoyancy, self-control stable balance helium blue sky spacecraft is equipped with a buoyancy device, a power device, a manned or a manned and concurrently loaded device with a lighter-than-air balloon to generate buoyancy. Power device: powered by an electric motor or an internal combustion engine driving a propeller or an airflow pump jet. Buoyancy device and buoyancy control device: There are at least two sets of buoyancy gas containers—soft balloons or soft and hard balloons. Different balloon groups are connected by pipelines, and pressure pumps, namely air pumps and inflation and deflation valves are connected in series on the pipelines. , relying on inflatable balloons to generate buoyancy, the buoyancy gas realizes different pressure and density distributions in different balloon groups under the pressure of the inflator pump, thereby automatically controlling the buoyancy; the lower part of the buoyancy device is connected to a manned or manned and loaded container, which is characterized by: The buoyancy control is realized by using the electronic control system or computer program to control and adjust the different density and pressure distribution of the buoyancy gas between each group of balloons; it is equipped with a "flying air flow control air pump" to realize self-control and stability, and its air outlet is through the air outlet pipe And the branch pipe leads to the air nozzle with adjustable air volume valve distributed around the aircraft, and its air inlet leads to the air inlet opening to the outside through the air inlet pipe; its self-control and balance is achieved by using an electronic control system or a computer The program controls the distribution and intensity of the airflow ejected to the outside world by the "regulating flight airflow air pump".

The balloon cabin space that accommodates all balloons has a flat shape, and a large-area flat roof is arranged. Solar cells are installed on the flat roof, and storage batteries and small internal combustion generators are set as backup power sources.

Buoyancy gas container balloons are all soft balloons made of elastic membranes. These balloons are divided into multiple groups, namely the main balloon group A, the main balloon group B and several auxiliary balloon groups; each group of balloons is composed of several balloons, referred to as unit balloons, The unit balloon is connected to the common trachea using a lung tube trachea similar to the trachea of an animal lung. There are two sets of lung tube trachea and total trachea, one is the inflatable trachea, and the other is the exhaust trachea.

All bronchial ends are connected with balloons by chicken intestine valve cores similar to bicycle and automobile tires. Where the air enters the balloon, the outlet of the valve core is inside the balloon; when the air flows out of the balloon, the outlet of the valve core is outside the balloon. There is also a branch pipe with a controllable air valve at the inlet of the air pump, which is used as a pipe for the intake of external air source.

Each unit balloon and its connected terminal bronchi are characterized in that: each unit balloon is equipped with an air sensor sensitive to a certain concentration of air component gas; Cut-off air valve, the opening and closing of the cut-off air valve is controlled by the aircraft automatic control system and driving instructions.

There are three types of motors in the power unit, namely, the air pump motor (hereinafter referred to as the inflatable motor) that inflates between the main and auxiliary balloons, the motor that drives the propeller propeller (hereinafter referred to as the propulsion motor), and the motor that drives the "control flight airflow". The motor of the air pump (hereinafter referred to as the air motor).

Its structure is composed of a pipe frame and a sheet or film skin, and forms three combined cabins, namely the balloon cabin, the engine room, and the cockpit, and the soft balloon is placed in the balloon cabin. The aircraft shell has an anti-static coating.

It is equipped with a propeller propeller fixed on the "frame shell of the aircraft" or "ancillary structure connected with the frame and shell of the aircraft".

The bottom bronchus (terminal bronchus) is connected to the unit balloon, and the bottom bronchus is provided with a cut-off valve that can be opened and closed automatically. The opening and closing of the cut-off valve is controlled by the aircraft automatic control system and driving instructions. Each unit balloon is equipped with an air sensor sensitive to a certain concentration of air component gas. The principle of controlling the opening and closing of the cut-off valve is: the air pressure of each balloon inflated and deflated by the same group of balloons should be even; The terminal bronchus cut-off air valve is closed to stop the inflation and deflation flow of the balloon.

The invention relates to an aircraft that uses gas lighter than air to fill balloons to generate buoyancy, and is characterized in that: the balloons of the aircraft include fuel balloons and buoyancy balloons. The aircraft uses the fuel gas in the fuel balloon as the energy to generate power to propel the aircraft and support the operation of the aircraft; it relies on the gas in the buoyancy balloon to generate upward lift. The gas in the fuel balloon can be natural gas, or methane, acetylene, ethylene in natural gas, or other non-hydrogen combustible gases lighter than air; the gas in the buoyancy balloon can be helium, hydrogen, natural gas, or methane, acetylene , ethylene, or other combustible gases that are lighter than or similar in density to air. Its "fuel balloon and combustible gas buoyancy balloon" and "the rest of the aircraft" are provided with a fire barrier that isolates combustion and high temperature; and it is equipped with a "fuel balloon or combustible gas buoyancy balloon" that causes high temperature when the combustion causes a "burning balloon" An automatic belay that disengages itself from "the rest of the aircraft". When the buoyancy balloon does not adopt the helium balloon, it also has an inflation mechanism that can generate buoyancy when the fuel balloon or the combustible gas buoyancy balloon is separated from the aircraft.

The buoyancy-generating balloon of the aircraft of the present invention is characterized in that the buoyancy of the balloon can be regulated; the buoyancy regulation is to use an electronic control system or a computer program to control an air pump and a controllable air valve to adjust the buoyancy gas between different buoyancy balloons Different densities and pressure distributions are achieved. The air pump of the present invention allocates gas between two groups of main balloons for regulating and descending, and allocates gas between the main balloons and secondary balloons for regulating the volume of buoyant gas adapted to the flight altitude.

The aircraft of the present invention is characterized in that: the automatic control of flight motion stability is realized by using an electronic control system or a computer program to control the distribution and intensity of the airflow ejected from the jet engine or the airflow pump to the outside.

The fuel balloon of the aircraft of the present invention is characterized in that: it can be suspended on the top of the rest of the aircraft and is composed of several fuel balloons; into connected gas tanks.

The combustible gas buoyancy balloon of the aircraft of the present invention is characterized in that: it can be suspended on the top of "the rest of the aircraft except the fuel balloon" and is composed of several buoyancy gas balloons; The remaining part of the aircraft other than the fuel balloon" is an adjacent buoyancy chamber composed of a number of buoyancy gas balloons,

The inflating mechanism that can produce buoyancy when the fuel balloon and the combustible gas buoyancy balloon are separated from the aircraft situation of the aircraft of the present invention is characterized in that it can be naturally inflated by the relatively rising air flow when the fuel balloon and the combustible gas buoyancy balloon are separated from the aircraft situation The spare inflatable umbrella-shaped bag, the umbrella-shaped bag is made up of the upper cover of the spherical crown and the lower bottom surface of the ball belt, the lower bottom surface of the umbrella-shaped bag is fixed on the circumferential frame of the aircraft, and there is a large gap between the inner circle of the lower bottom surface of the spherical belt. The area is used as a hole in the umbrella-shaped bag to communicate with the outside air, and the top cover of the umbrella-shaped bag is usually folded on the lower bottom surface and is in a non-inflated state. The aircraft circumferential frame that fixes the bottom surface of the umbrella-shaped balloon band is connected with the aircraft cabin and the cockpit frame as a whole.

The fire barrier for isolated combustion and high temperature provided between the fuel balloon of the aircraft and other parts of the aircraft of the present invention is characterized in that: when the fuel balloon is suspended on the top of the rest of the aircraft to form a barrier composed of several fuel balloons, its The feature is: when the fuel balloon is an independent gas cabin composed of a number of fuel balloons suspended above the rest of the aircraft, the space between the gas cabin and other parts of the aircraft is used as a fire barrier to isolate combustion and high temperature; When a fuel balloon is a connected gas cabin formed by a number of fuel balloons surrounding other parts of the aircraft, the partition wall formed with fire-resistant and fire-extinguishing materials between the gas cabin and other parts of the aircraft is used as a fire barrier.

The fireproof barrier that is set between the combustible gas buoyancy balloon of the aircraft of the present invention and "the rest of the aircraft except the fuel balloon", is characterized in that: when the combustible gas buoyancy balloon is suspended on the "except the fuel balloon" In the case of an independent gas chamber composed of several flammable gas buoyancy balloons above the top of the "rest of the aircraft", the separation space between the gas chamber and "the rest of the aircraft except the fuel balloon" is used as a fire barrier to isolate combustion and high temperature; When the combustible gas buoyancy balloon is a connected buoyancy chamber composed of several combustible gas buoyancy balloons adjacent to "the rest of the aircraft except the fuel balloon", the gas chamber and "the rest of the aircraft except the fuel balloon" The partition wall composed of fire-resistant and fire-extinguishing materials serves as a fire barrier.

The high-temperature automatic detachment protection device between the fuel balloon of the aircraft, the flammable gas buoyancy balloon and the rest of the aircraft is characterized in that: when the fuel balloon, the flammable gas buoyancy balloon and the rest of the aircraft use the separated space as a protective barrier, Materials that are flammable at a certain temperature and can be automatically cut off at high temperatures are used as connecting ropes between fuel balloons, flammable gas buoyancy balloons and other parts; The trip mechanism activated by hydrogen-sensitive and heat-sensitive elements is used to release the integral connection between the gas cabin, the combustible gas buoyancy chamber and the rest of the aircraft when the hydrogen-sensitive and heat-sensitive elements are activated.

The fuel gas in the fuel balloon used by the aircraft of the present invention as generating power is characterized in that: the energy utilization mode of the fuel gas is: the engine can adopt a jet engine, or an internal combustion engine or an electric motor is used as the engine, and the propeller is used as a navigation engine. The propeller of the aircraft; the air pump for regulating the flight airflow of the aircraft is driven by an internal combustion engine; the air pump for regulating the distribution of buoyancy gas among different balloons is driven by an electric motor. The electricity required for the operation of the aircraft and the motor is supplied by the internal combustion generator set or the fuel cell after converting the energy of the fuel gas into electrical energy.

Each unit balloon of the present invention and the terminal bronchus connected thereto, each unit balloon all has its own electronic barometer; the terminal bronchus connected to each unit balloon has a cut-off valve that can be opened and closed automatically, and the opening and closing of the cut-off valve It is controlled by the aircraft automatic control system and driving instructions. Each unit balloon is equipped with an air sensor sensitive to a certain concentration of air component gas. The principle of controlling the opening and closing of the cut-off valve (JF) is: the same group of balloons should be inflated and deflated, and the air pressure of each balloon should be uniform; when the balloon bursts, the air enters the balloon, and the air sensor of the unit balloon sends a message, which is controlled by the automatic control system The terminal bronchi shut-off valve (JF) of the balloon is closed, and the inflation and deflation flow of the balloon is stopped.

In the present invention, when the hydrogen balloon is separated from the aircraft and the buoyant inflating mechanism is a spare inflatable umbrella, the part below the maximum diameter skeleton circle of the hydrogen cabin is no longer provided with a main load-bearing skeleton.

In the present invention, except that the maximum diameter of the fuel tank is the skeleton circle connected with the aircraft, there is no main load-bearing skeleton; the auxiliary facilities such as fuel balloons and brackets in the fuel tank are as light and simple as possible, and high-strength light and thin materials are used. Make the self-weight of the fuel tank as small as possible.

The structural materials of the aircraft are flame-retardant and fire-resistant materials. The aircraft shell has an anti-static coating. All control circuits and other circuits in the fuel gas chamber and the combustible gas buoyancy chamber of the aircraft of the present invention are explosion-proof grades, the switch electrical appliances are non-contact switches, the wire joints are welded, and the control motor is a non-sparking explosion-proof induction motor. Because the present invention is loaded with a large amount of combustible gas, the take-off and landing and berthing sites should be far away from residents and downtown areas, or elevated take-off and landing and berthing airports should be adopted.

4. Description of drawings

Fig. 1 is a front view of the appearance of the present invention), Fig. 2 is a front view of the appearance of the present invention, and Fig. 3 is a bottom view of the appearance;

Fig. 4 is an appearance view of an embodiment of the present invention, and Fig. 5 is a bottom view of the appearance of the embodiment of the figure, wherein TC is a natural gas tank; HC is a helium gas tank; J is an engine room; Z is a cockpit; R is a soft air cushion bag; Natural gas main jet engine. C is a balloon cabin (including a hydrogen cabin and a helium cabin).

Fig. 6 is the schematic diagram that the aircraft circumferential skeleton with the lower bottom surface of the fixed standby inflatable umbrella-shaped balloon belt is connected with the cabin and the cockpit skeleton according to the present invention.

Fig. 7 is the structure diagram that the present invention adopts jet engine nacelle, and cockpit is disc shape.

5. Specific implementation

The first embodiment of the present invention is: the balloon cabin includes a gas cabin—a natural gas cabin, and a buoyancy gas cabin—a helium cabin. The internal combustion engine is used to drive the propeller propeller. Referring to the drawings in the manual, HC is a helium tank; TC is a natural gas tank; J is an engine room; Z is a cockpit; Y is a wing; L is a propeller propeller; R is a soft air cushion bag; W is a tail cone after the cockpit; D for the tail rudder.

The buoyancy regulation of the helium balloon in the helium chamber (HC) is realized by using an electronic control system or computer program to control and adjust the different densities and pressure distributions of helium between different helium balloons; its self-control and stability is achieved by using an electronic control system or computer The program controls the distribution and intensity of the airflow ejected to the outside world by the "regulating flight airflow air pump".

The shape of the helium chamber is an inverted ball table with an upper diameter of 30 meters, a lower diameter of 6 meters, and a thickness of 5 meters. Its volume is about 1903 cubic meters; The engine room (J) with a height of 1 meter is connected; the lower bottom of the engine room is connected with the cockpit (Z) with a length of 4 meters, a length of 3.5 meters, a width of 2 meters and a height of 2 meters. Along the first 3 meters of the lower bottom of the cockpit, a soft air cushion (RD) with the same length and width as the lower bottom of the cockpit and a height of 0.5 meters is attached. The two ends of the cabin and the cockpit along the length direction are respectively defined as the front end and the rear end of the aircraft (the meanings of "front" and "rear" in this specification are consistent with this). The connecting surfaces between the front and rear ends of the upper roof of the cabin and the front and rear sides of the helium tank, the connecting surfaces between the upper roof and the lower bottom of the cabin, and the connecting surfaces between the upper roof and the lower bottom of the cockpit are all smooth curved surfaces; The upper edge of the transition curve connecting the front end and the front and rear sides of the balloon cabin extends to the 10-meter-diameter section of the helium cabin. In addition, on the basis of the above structure, the cabin and the cockpit are additionally made with a tapered tail (W) 1 meter long (the extended transition surface at the upper part of the rear end of the cabin is no longer extended backward); The tail rudder (D) which can be controlled by electric signal is equipped with the tapered tail trailing edge at the rear end of the cockpit.

The helium cabin, engine room, and cockpit are made of carbon fiber composite material pipes or aramid fiber composite material pipes to make an integrated overall skeleton, and the panels of the same material are used as the outer walls of the engine room and cockpit. Or other high-strength membranes as skins. The top of the helium tank is partially covered with plates. The structural materials of the aircraft are flame-retardant and fire-resistant materials.

Along the cabin, the cockpit width direction, from the cabin, cockpit left and right side respectively stretch out the 2 meter long wing, also make its skeleton, shell by the same material as cabin skeleton, outer wall. The end of the wing is connected with the side of the helium tank through a transition surface. The wing is 0.3 meters thick and 1 meter wide, and the front and rear parts of the cross section are curved and smoothly connected with the upper and lower parts (the cross section becomes the streamlined shape of the aircraft wing). The length of the wing is perpendicular to the length direction of the cabin and the cockpit, the center plane of the width of the wing is aligned with the center plane of the length of the cabin, and the center plane of the thickness of the wing is aligned with the interface between the cabin and the cockpit. Elevators that can be controlled by electrical signals are installed behind the two wings.

The left and right wings are each equipped with a propelling internal combustion engine and a propeller propeller driven by it. The propeller is made of carbon fiber or polyester composite material (as a hollow shell). The propeller is in the front, and the internal combustion engine and its propeller are placed in the cylindrical engine room of the left and right wings; the engine room is embedded in the center of the left and right wings along the length of the wing, and is connected to the surface of the wing through a smooth transition surface. The tail end of the engine compartment is tapered. The frame and skin materials of the engine compartment are the same as those of the wings. The rotating diameter of the propeller is 1.4 meters to 1.8 meters. Left and right engine rooms to the front, rear, upper and lower positions of the wing section between the left and right wing along the long and far ends of the wing, and on the transition curved surface where the wing end is connected with the helium tank, each is provided with a belt Air nozzles with controllable air valves (two wings, 10 wing nozzles in 5 directions). The other ends of the controllable air valves of the left and right air nozzles of the wing are connected with the regulating airflow pipes of the left and right wings, and the left and right regulating airflow pipes converge and lead to the air pump for "controlling flight airflow" (airflow pump for short) in the cabin. ) of the air outlet; the air inlet of the airflow pump is led to the air inlet by the pipeline, and the air inlet is opened at the front end and the rear end of the cabin, and is switched by a controllable air valve.

On the transition curved surface where the front and rear sides of the helium cabin are connected with the front and rear sides of the engine room; there is also an air nozzle with a controllable air valve (a total of three air nozzles on the top of the balloon cabin and the side air nozzles), respectively. The air jet pipes for controlling the air flow are connected respectively, and each air jet pipe is connected to the air outlet of the air flow pump after converging. The two air inlets of the airflow pump are also made into air nozzles, and the air intake or jet is switched by the controllable air valve of the airflow pump. The air nozzle on the top of the helium cabin sprays upwards, passes through the pipeline passing through the fuel tank, and sprays air to the upper sky; the front and rear air nozzles on the sides of the balloon cabin spray downwards.

The internal-combustion engine power of airflow pump is 20 horsepowers, and the outlet end of airflow pump is also connected with the small trachea of supplying the exchange air in the cabin.

The interior of the helium chamber is the main balloon A cabin B and the auxiliary balloon cabin. Each of these three balloon sub-chambers can accommodate 27 unit balloons. Their inflated volumes are equal, and most of the balloons are cube-shaped when inflated. The shape of the balloon near the boundaries of a small number of subdivisions can be irregular with the boundaries. The unit balloon membrane is made of high-strength, high-elasticity and low-density film material. Each balloon sub-compartment is equipped with in-cabin support components (used as pipes) to ensure the mechanical strength of the cabins; it is also equipped with balloon installation components separating the space of the balloon unit (used as thinner pipes), and each unit The balloons are all hung on the components at the top of the corresponding partitioned spaces. A part of the unit balloon has an emergency deflation nozzle that is strictly sealed at ordinary times and can be manually opened in case of emergency. Each balloon subdivision has a square cross-section channel in the center of the horizontal direction. All the channels are connected as a whole and enter the cabin. The opening on the top of the cabin is used as a space for pipelines, circuits, and personnel to pass through; the channels are separated by longitudinal intervals. Pipelines, circuits and personnel pass through the channel (hereinafter referred to as the channel). There are doors that open into the passage between the passage and each cabin and sub-cabin.

The soft airbag at the bottom of the cockpit is a soft airbag whose upper end is fixed on the bottom of the cockpit. It has a volume of 3×2×0.5=3 cubic meters and accommodates two layers of 8 rectangular unit air bags. They are connected with an air pump similar to a balloon group. The air duct system is connected to the airflow pump through the lung duct type air duct system and the controllable air valve of the main pipe; the air duct system is also divided into an inflatable duct system and an exhaust duct system, and the main air duct bypasses the interlayer at the rear of the cockpit and enters the cabin.

The connection between the non-integral components of the aircraft structure is mainly connected by rivets, and a few connections are connected by bolts when necessary. The component density of the aircraft structure, the section of the component pipe, the section of the structural skin, the section of the rivet and the bolt are all determined by the aircraft load (static load, dynamic load, accidental distributed load) and the mechanical properties of the material, and are determined by engineering mechanics calculations. flight

The connection between the non-integral components of the aircraft structure is mainly connected by rivets, and a few connections are connected by screws when necessary. The component density, component pipe section, structural skin section, rivet, and screw inspection section of the aircraft structure are all determined by the aircraft load (static load, dynamic load, accidental distributed load) and material mechanical properties, and are determined by engineering mechanics calculations.

The top of the balloon cabin can also be used as a deck for the crew to visit. There are remote control automatic lifting guardrails on the edge of the deck, and all boarders are equipped with safety belts to fix on the "deck".

The main equipment in the engine room includes airflow pump, air pump, air valve, battery pack, control cabinet equipment, communication equipment, computer and air conditioner. The air pump electric motor power is 1 kilowatt to 3 kilowatts. The air conditioner uses two branch trachea drawn from the airflow pump piping system to take in and out the air.

The aircraft of the present invention is also equipped with the following sensing devices: front and rear, left and right horizontal inclination sensors (all adopting a connecting pipe liquid level relay), flight speed and direction sensors, several acceleration sensors (using stress-sensitive materials to transform the stress generated by the acceleration into electrical signal), a number of distance sensors from the height of the ground or adjacent obstacles in all directions (using laser ranging or ultrasonic ranging devices), a number of ambient air pressure and wind speed sensors (wind speed sensors are installed at the connecting section between the wing end and the balloon cabin) , cabin front end, tail end, etc.), several environmental electrostatic sensors, mechanical and electrical equipment status sensors, and several external camera recording heads.

The front part of the cockpit is the driving position, and the basic equipment for the driver to operate is the steering wheel (uplift the steering wheel, press down to control the aircraft’s ascent and descent movement), and the control panel. Meters and pedal brakes, several flat screens, video heads, microphones, speakers; there are computer keyboards and mice that can be drawn out in the control panel.

Items in the cockpit should be made of non-metal elastic materials as much as possible. The internal volume of the cockpit (not including the tapered tail) is 2.5 meters long, 1.8 meters wide and 1.8 meters high. Three rows of seats are arranged along the length direction. The front row is the driver's seat and the flip-up seats on both sides. The middle row is for passenger seats and flip-up seats; the rear row is for sleeping seats, and the bottom of the sleeping seats is for storage boxes for food, water, faucets, aerial work clothes and other appliances. The backrest of the middle row seat has the same structure as the front side panel under the seat, and can be turned into a backrest (with an extended backrest that can be opened and stowed corresponding to the flipped up seat), side panels, and bed panels. Can move forward and backward as a whole. There are tabletops that can be turned up on the left and right walls of the cabin. The cockpit is sealed, and the internal connection and exhaust holes of the air conditioner are opened at the front and rear ends of the cockpit roof. There is a door behind the rear seat that leads to the part of the space at the conical tail of the cockpit. Through the door, you can enter the toilet and toilet in the conical tail space of the cockpit (1 meter long, 1.8 meters high, and the width shrinks from 2 meters to zero). Discharge directly into the air. The bathroom door and the toilet should be at both ends of the width direction. A small internal combustion generator (with a capacity of about 1 kW to 3 kW) penetrates from the tail cone space of the engine room to the tail cone space of the cockpit. The external fuel gas and buoyancy gas source intake pipes, external charging power and water supply are also connected here. The cockpit is equipped with a ladder.

Aircraft of the present invention adopts the computer of equipment special-purpose application software to control (but the direct control system of a cover of electrical equipment does not go through computer again), actuator adopts multistage solid-state relay, uses special-purpose between solid-state relay and computer I/O interface. Encoder (integrated circuit), decoder (integrated circuit), channel connection. The terminal solid state relay controls each electric motor, each electric controllable air valve, and each servo micromotor for auxiliary manipulation. All kinds of sensor signals adopt information processor, and the information processing circuit that converts analog information into digital signal becomes digital signal, and then enters the computer I/O interface after being encoded by the encoder. Encoders, decoders, information processors, and solid-state relays are all in the control cabinet.

The aircraft of the present invention is equipped with a radio remote controller, and the remote controller can replace the driving control equipment to make the driver be in any part of the aircraft for driving operation.

The main control system of aircraft driving control and automatic control of the present invention is as follows:

(1) Speed control: The pilot's flight speed command (or preset program) and the sensor's flight speed information are transformed into speed regulation commands (acceleration, deceleration, stop) of the propulsion motor.

(2) Direction control: the pilot's flight direction command (or preset program) and the sensor's flight direction information are converted into rudder movement commands.

(3) Straight-line self-control: the acceleration information of the sensor is transformed into the differential speed regulation instruction of the left and right propulsion motors (actually) (4) Altitude control: the flight altitude command (or preset program) of the driver and the flight altitude of the sensor The information is transformed into the starting instruction of the inflatable motor and the opening and closing instructions of the corresponding controllable air valve.

(5) Stable self-control: The flight tilt information and wind speed information of the sensor are transformed into the starting command of the airflow pump, the opening and closing command of the corresponding controllable air valve (realizing stable flight) and the horizontal rudder movement command.

(6) Avoidance (also divided into avoidance and braking) self-control: the information from the sensor to the obstacle (including the ground) and the set safety distance information are transformed into the start-up speed regulation instructions and the corresponding adjustable speed of the internal combustion engine, airflow pump and air pump. The switch instruction of the air control valve is a reasonable modification instruction to the original movement speed and direction. When the driving command and the direct control command of the electrical equipment are inconsistent with the avoidance command, the control system mechanism guarantees to obey the latter. (7) Electrical equipment current, voltage, thermal protection, and other automatic control systems for safety protection.

(8) Unmanned automatic flight control:

When there is no driving command, the driving command channel is automatically switched to the automatic flight information setting device (also a kind of information processor). At this time, the aircraft flies according to the original direction, speed and altitude and performs straight-line self-control, stable flight self-control and avoidance self-control . If the direction, speed, and altitude drift, there are two ways: eliminate the drift and follow the drift.

The fuel tank of the present embodiment has the same area and shape as the bottom surface and the upper bottom of the helium tank, and is an upwardly protruding spherical segment. The spherical segment has a diameter of 30 meters, a height of 3 meters, and a volume of 1074 cubic meters, which can accommodate about 700kg of natural gas (equivalent to 722kg of gasoline).

The gas chamber is a soft airbag with a built-in fuel balloon. The edge of the bottom surface of the gas tank is bound to the suspension ring of the upper edge structure framework of the helium gas tank with ropes, and the ropes are tightened and bound until there is no gap. The rope that binds the gas cabin is not a high-temperature-resistant flammable material. When the fuel balloon burns or a high-temperature fault occurs, it will automatically burn off; but the rope has sufficient mechanical strength at the working temperature. Although the rope that binds the gas cabin has multiple stressed rope segments and suspension points, it is a simple closed line connected by a continuous rope passing through many suspension rings. As long as one part is disconnected, it will be completely untied. The rope binding the gas chamber and the helium chamber also has a loose buckle, which is normally locked reliably. When there is a failure of combustion or high-temperature combustible gas leakage, the gas sensor and thermal sensor will automatically activate the tripping mechanism, which can be released. Slip buckle for tying the rope, immediately releasing the integral connection of the gas tank to the rest of the aircraft

In order to prevent the loss of the gas cabin due to accidental mechanical breakage of the rope when there is no combustion or high temperature failure, a safety rope is added to the center of the lower bottom of the gas cabin. on the safety rope hoist. When the suspension rope at the edge of the gas cabin accidentally breaks mechanically when there is no combustion or high temperature failure, the safety rope winch can wind up the safety rope under automatic control or human control, pull it back to the gas cabin, and then repair the binding rope at the edge of the gas cabin.

The second embodiment of the present invention is: the balloon cabin includes a gas cabin-a natural gas cabin, a buoyancy gas cabin-a helium cabin, and adopts a disc-shaped cabin, a cockpit and a jet engine. See Figures 4 and 5.

In this embodiment, on the basis of the first embodiment, the cabin and the cockpit are changed from elongated to disc-shaped. That is: the cabin is an inverted circular platform with an upper diameter of 7 meters, a lower diameter of 5 meters, and a height of 1 meter; the cockpit is an inverted circular platform with an upper diameter of 5 meters, a lower diameter of 4 meters, and a height of 2 meters; the soft air cushion has a diameter of 4 meters and a height of 0.5 meters of cylinders. The balloon cabin, the cabin, and the cockpit are connected with smooth transitions, making the entire aircraft a flat-topped, arc-bottomed disc-shaped object. The aircraft is no longer provided with wings and tail cones; the engines are several (for example 2 to 4) jet engines burning natural gas evenly distributed on the side of the cabin, and the nozzles of the jet engines are self-controlling nozzles that can be automatically controlled and change the jet flow direction. Each engine power is 20 to 40 horsepower.

In this embodiment, the inflator for regulating the distribution of helium gas among different helium balloons is driven by a motor, and its power is supplied by a natural gas internal combustion engine generator set in the engine room. The present embodiment does not establish the air flow pump, but the spare jet engine of upward spraying is set at the center of the gas cabin top. The jet engine can be controlled by the cabin automatic control system and driving control instructions through the remote control device, and the energy required for the jet engine's electric fire, start, operation control, and shutdown control is supplied by a micro-rechargeable battery and a small hydrogen fuel cell; Available non-contact switch, welding terminal wired circuit, power supply and control.

The third embodiment of the present invention is: on the basis of the second embodiment, the helium tank in the second embodiment is changed to a hydrogen tank, and the "inflating mechanism that can generate buoyancy when the hydrogen balloon leaves the aircraft" is added— - "the spare inflatable umbrella-shaped bag that the lower part has a communication airway with the outside world". The shape of the side and lower bottom of the hydrogen cabin coincides with the shape of the fixed frame of the lower bottom of the spare inflatable umbrella, and the hydrogen cabin is either closely attached to the fixed frame of the lower bottom of the spare inflatable umbrella, or suspended, aligned, and slightly higher than the spare inflatable umbrella The lower bottom of the shaped capsule fixes the skeleton. The gas cabin is tied to the hydrogen cabin with ropes. Fix the aircraft circumferential frame on the lower surface of the spare inflatable umbrella-shaped balloon belt, and connect as a whole with the cabin and the cockpit frame. See accompanying drawing 6: among the figure TC is a natural gas tank; J is a cabin; Z is a cockpit; R is a soft air cushion; SN is a spare inflatable umbrella bag;

This embodiment continues to use the existing invention of safe hydrogen buoyancy, hydrogen fuel blue sky spaceship hydrogen balloon and other parts of the aircraft to be provided with isolated combustion, high temperature fire barriers, and is equipped with hydrogen balloon combustion caused by high temperature The hydrogen balloon automatically separates from the rest of the aircraft Part of the automatic protection device. The inflatable mechanism that can generate buoyancy when the hydrogen balloon leaves the aircraft—the spare inflatable umbrella-shaped bag that can be naturally inflated by the relatively rising air flow when the hydrogen balloon leaves the aircraft. There is a large area between the inner circle of the annular lower bottom surface as the hole that the inside of the umbrella-shaped bag communicates with the outside air, and the top cover of the umbrella-shaped bag ball is usually folded on the lower bottom surface and is in an inflated state.

The buoyancy-generating hydrogen cabin of the aircraft of the present embodiment and the aircraft contact mode have two schemes again: the hydrogen cabin can be an independent hydrogen cabin suspended over the top of the rest of the aircraft; .

The aircraft of the present embodiment produces the buoyancy of the hydrogen cabin and the other parts of the aircraft and is provided with an isolated combustion, a high-temperature fire barrier. It is characterized in that: when the hydrogen balloon is an independent hydrogen cabin suspended over the top of the rest of the aircraft , the separation space between the hydrogen cabin and other parts of the aircraft is used as a fire barrier to isolate combustion and high temperature; when the hydrogen balloon is a connected hydrogen cabin composed of several hydrogen balloons adjacent to other parts of the aircraft, the hydrogen cabin and Between other parts of the aircraft, the partition walls made of fire-resistant and fire-extinguishing materials are used as fire barriers.

The high-temperature automatic detachment protection device between the hydrogen cabin of the aircraft and the rest of the aircraft in this embodiment, when the hydrogen cabin and the rest of the aircraft use a separate space as a protective barrier, use a material that is combustible at a certain temperature and can be automatically cut off at high temperatures , as the connection rope between the hydrogen tank and other parts. In this case, the rope for hanging the hydrogen cabin is not a high-temperature-resistant flammable material. When the hydrogen balloon burns or a high-temperature failure occurs, it can automatically burn off; but the rope has sufficient mechanical strength at the working temperature. Although the rope for hanging the hydrogen cabin has multiple stress-bearing rope segments and suspension points, it is a simple closed line connected by a continuous rope passing through many suspension rings. As long as one part is disconnected, it will be completely untied.

The high-temperature automatic detachment protection device between the hydrogen cabin of the aircraft and the rest of the aircraft in this embodiment, when the hydrogen cabin and the rest of the aircraft are shielded from each other by a fire partition wall, a tripping mechanism activated by hydrogen-sensitive and heat-sensitive elements is adopted. , which is used to release the overall connection between the hydrogen tank and the rest of the aircraft during hydrogen-sensitive and heat-sensitive starts. The outer diameter of the maximum diameter of the hydrogen chamber is slightly smaller than the inner diameter of the "annular fixed frame at the junction of the top surface and the bottom surface of the umbrella-shaped bag", and it just fits into the latter. On the "annular fixed skeleton at the junction of the top surface and the bottom surface of the umbrella-shaped bag", several tubular members are uniformly distributed along the radial direction and the circumference, that is, 5 in the accompanying drawing 2, and are blocked on the outer diameter skeleton of the hydrogen cabin. As a combined load-bearing component (hereinafter referred to as the load-bearing beam) that connects the hydrogen cabin and the helium cabin as a whole at ordinary times. Each bearing beam all has a rotatable shaft, namely 6 among accompanying drawing 2, is locked and can't rotate freely at ordinary times. Once the hydrogen balloon burns, gas leaks, and high temperature occurs, the thermal sensor, smoke sensor, and hydrogen sensor arranged in several places in the hydrogen cabin will send out a fault message. And through the controller, this information is converted into the load-bearing beam rotating shaft sleeve lock release command, so that the normally locked load-bearing beam becomes free to rotate, so that the load-bearing beam turns up under the action of buoyancy, And then let go of the entire hydrogen cabin, realize the hydrogen cabin floats, and break away from the helium cabin and the rest of the aircraft.

The present embodiment helium balloon is made of two groups of main balloons, one group of auxiliary balloons, and the gas volume distribution between each group of balloons is regulated by the automatic control system; A group of auxiliary balloons is composed of an automatic control system to adjust the air volume distribution between each group of balloons.

The fourth embodiment of the present invention: the nacelle of the third embodiment, the cockpit are changed back to the style of the first embodiment, and the nacelle and the cockpit appendages such as wings and propellers of the first embodiment are restored. Turn jet engines into internal combustion engines. All the other are the same as the third embodiment.

The fifth embodiment of the present invention: the balloon cabin only has the gas cabin inflated with non-hydrogen combustible gas, and it doubles as the buoyancy air cabin, and no other buoyancy air cabin is established; the jet engine cabin and the cockpit are disc-shaped. See accompanying drawing 7 of the description, among the figure TC is a natural gas tank; J is an engine room; Z is a cockpit; R is a soft air cushion bag; SS is a spare inflatable umbrella bag;

This embodiment is obtained on the basis of the third embodiment (hydrogen gas cabin, jet engine, spare inflatable umbrella bag) by merging the hydrogen gas cabin and the gas cabin of the third embodiment into a gas cabin. In other words, the gas cabin of the third embodiment is expanded to include the scope of the original hydrogen cabin (the upper part is a spherical segment with a diameter of 30 meters and a height of 3 meters, and the lower part is a large bottom with a diameter of 30 meters, a height of 5 meters, and a small bottom with a diameter of 6 meters. inverted table). The gas cabin replaces the hydrogen cabin and is connected with the "annular fixed frame at the junction of the top surface and the bottom surface of the umbrella" and is connected by means of rope binding; the structure of its connection and fault release is the same as that of the gas cabin and the third embodiment. The connection and fault trip structure of the hydrogen chamber. The inside of the gas cabin is further divided into A cabin and B cabin. The air pump installed in the engine room regulates the different density distribution of gas between the two cabins, so as to properly and slightly adjust the buoyancy of the gas cabin; The pump motor is powered by an internal combustion generator set or a fuel cell, and the air pump motor is controlled by the aircraft automatic control system and driving instructions. The present embodiment can carry about 2977 cubic meters of natural gas, which is approximately equivalent to 2201 kg of gasoline. Its initial loadable buoyancy is about 1268kg, and its final buoyancy is zero. Therefore, its operation has a special mode: take off with buoyancy, maintain the lift with jets, and rely on the spare inflatable parachute to land freely when the fuel is almost exhausted. Among the inflatable aircraft, its biggest feature is the smallest volume, the highest speed, and safety and reliability.

The sixth embodiment is to change the height of the upper ball gap and the lower table of the gas chamber of the fifth embodiment, and the others are the same as the fifth embodiment. The height change of the upper ball gap and the lower table of the gas cabin has the following plans: (1) the height of the upper ball gap is 5 meters, and the height of the lower table is 3 meters; (2) the height of the upper ball gap is 0 meters, and the height of the lower table is 5 meters; (3) The height of the upper ball is 5 meters, and the height of the lower table is 0 meters; (4) the height of the upper ball is 5 meters, and the height of the lower table is 5 meters; (5) the height of the upper ball is 5.2 meters, and the height of the lower table is 5 meters.

The seventh embodiment scheme is on the basis of the foregoing embodiments, the propeller and the internal combustion engine thereof of the first and fourth embodiments are replaced by the main engine of the wing jet engine at the same position, and the airflow pump nozzles for regulating the flight airflow are replaced with small ones. Jet engine (comprising the spare jet engine on the top of the original aircraft), but the small jet engine of each wing is merged into the wing jet engine auxiliary machine, which splits the jet from the original airflow pump and nozzle position; all the other structures remain unchanged. For the fifth embodiment, its engine room and cockpit are then changed into the first embodiment pattern earlier, and then the engine is set as wing jet engine main engine, small jet engine, wing jet engine auxiliary engine as aforementioned; but the natural gas cabin still holds concurrent buoyancy Air chamber, the rest of the structure remains unchanged.

The eighth embodiment scheme is on the basis of the foregoing embodiments, and the rotor (coaxial reversed dual rotors) similar to a helicopter is set at the center of the gas tank top, and at this moment, the air nozzle at the top of the aircraft is canceled.

The ninth embodiment scheme is then on the basis of the foregoing embodiments, laying 60 kilowatts of solar cells on the top cabin roof of the aircraft, or a solar energy-hydrogen energy converter, with reference to accompanying drawing 6: if laying solar cells, the engine will be changed to Corresponding power motors, airflow pump motors are set separately, and the hydrogen in the hydrogen balloon is no longer used as energy. If the solar energy-hydrogen energy converter is laid, the hydrogen energy internal combustion engine is still used as the engine. The solar-hydrogen converter can supplement the hydrogen energy consumed in the hydrogen balloon. When hydrogen is produced by solar energy, it is necessary to place the aircraft under appropriate altitude and weather conditions to obtain water vapor in the atmosphere as a raw material for hydrogen production.

The tenth embodiment is: change the appearance of the balloon cabin (referring to the overall shape formed by the gas cabin, the buoyancy air cabin, and the umbrella bag) of the foregoing embodiment into a sphere, but cut a small piece of the ball (the ball) under the sphere. The height is much smaller than the diameter of the ball), and the section cut out is used as the upper top surface of the aircraft cabin. The upper part of the balloon cabin that is basically a sphere is a gas cabin, the middle part is a buoyancy gas cabin, and the bottom is an umbrella-shaped bag (no umbrella-shaped bag when adopting a helium gas cabin). When the bottom is an umbrella-shaped bag, the volume of the upper part is greater than that of the bottom; when the bottom is a helium chamber, the volume of the upper part is smaller than that of the bottom. If adopt natural gas jet engine, nacelle, cockpit are disc-shaped; If adopt natural gas internal combustion engine to drive propeller propeller, nacelle, cockpit, wing shape are with the first embodiment. The spare hydrogen energy jet engine and ancillary equipment thereof that can upwardly spray on the top of the balloon cabin are identical with the foregoing embodiments.

The eleventh embodiment is: change the appearance of the balloon cabin (referring to the overall shape formed by the gas cabin, the buoyancy air cabin, and the umbrella bag) of the foregoing embodiment into the olive shape that the traditional airship adopts, with a tail rudder at the tail and a tail rudder at the bottom. Connect the cabin and cockpit. The upper part of the balloon cabin is a hydrogen cabin, the middle part is a buoyancy air cabin, and the lower part is an umbrella-shaped bag (there is no umbrella-shaped bag when a helium cabin is adopted). The connecting parts of the upper part, the middle part and the lower part do not adopt the suspended structure of the separated space. When the bottom is an umbrella-shaped bag, the volume of the upper part is greater than that of the bottom; when the bottom is a helium chamber, the volume of the upper part is smaller than that of the bottom. Nacelle, cockpit, wing, engine, propeller, the structure and position of regulating flight air flow nozzle can be similar to the first embodiment; At this time, the engine still uses a hydrogen internal combustion engine to drive the propeller propeller. The propeller can be installed at the front or rear end of the cabin, cockpit, or at the tail end of the balloon cabin. The nozzles for controlling the flight airflow can be distributed around the cabin, the cabin and the balloon cabin proper location. The spare hydrogen energy jet engine and ancillary equipment thereof that can upwardly spray on the top of the balloon cabin are identical with the foregoing embodiments. When the center of the gas tank roof is provided with a rotor similar to a helicopter, the air nozzle on the top of the aircraft is canceled; if the rear of the aircraft is provided with a small propeller to prevent the rotation of the aircraft, the rotors on the top of the gas tank can be single, not a pair.

The present invention can also have embodiments adopting other appearance shapes different from those of the foregoing embodiments. The exterior shapes of all the embodiments of the present invention should also be adjusted after aerodynamic calculations and tests.

If the present invention uses methane as fuel, with a helium balloon or a hydrogen balloon as the buoyancy balloon, when the buoyancy balloon volume is 1000 cubic meters and the lift is 1293kg (self-weight: hydrogen 89.9kg helium 178.5kg, remove the loadable load of self-weight: hydrogen 1203kg helium 1114.5kg), can carry 600 cubic meters of methane, 429.9kg (net buoyancy 345kg, the maximum range of buoyancy interference is 28.7% to hydrogen, 30.96% to helium, roughly equivalent to the buoyancy adjustment rate of a balloon from sea level to 3000 meters above sea level is about 30 %, but the buoyancy adjustment methods of constant external pressure degeneration and constant external pressure are different. The former buoyancy balloon membrane needs to bear the pressure of 0.43 atmospheric pressure to cope with 30% constant external pressure degeneration buoyancy adjustment). 1kg natural gas is equivalent to 1.032kg gasoline, thus it can be seen that the present invention can at least carry the gasoline that is equivalent to 36.9% to 39.8% of the aircraft's buoyancy and can carry 36.9% to 39.8% of the load ("fuel tank" weight is estimated by an equal-volume hydrogen balloon, which is about 1/10 of the buoyancy weight) First, the weight of methane is 0.18, and the buoyancy of the aircraft can carry the load 0.0694, 0.0663).

The first embodiment of the present invention: the volume of the buoyant balloon is 1903 cubic meters, and it carries about 1074 cubic meters of natural gas, which is equivalent to 722 kg of gasoline; the fifth embodiment: the initial loadable buoyancy is 1268 kg, and it carries about 2977 cubic meters of natural gas, which is equivalent to 2201 kg of gasoline.

Such a considerable amount of energy can be sufficient to supply the high-speed and long-range endurance of the buoyant inflatable aircraft, which is enough to make up for the problems of low speed and short cruising range caused by the replacement of aircraft aviation by buoyant inflatable aircraft aviation. In addition, the present invention also has the advantages of saving petroleum energy and superior navigation safety performance, so it has strong vitality. In the embodiment of the present invention using jet engines, medium and small jet engines are used to regulate the flight airflow, backed by sufficient natural gas energy, and powerful stable and balanced flight adjustment capabilities can be obtained, which is also a significant advantage.

The disadvantage of the present invention is that it still consumes a large amount of fossil energy, but it is relatively clean and less polluting energy, and it opens up the use of natural gas—especially for transportation and aviation in large quantities. Natural gas is better than gasoline and hydrogen for aviation: natural gas is cheaper than gasoline (the price of gasoline is 4.54 yuan per kg, and the price of natural gas is about 3.07 yuan per kg), and it has more energy per cubic meter than hydrogen (per cubic meter The energy of natural gas is approximately equal to the energy of 3.2 cubic meters of hydrogen).

The invention is particularly suitable for use as a small-sized, fast personal flying tool for special purposes, and as a large-scale high-speed, long-distance civil aviation vehicle.

Claims (10)

1, high speed remote voyage natural gas airship, at least be provided with two groups of buoyancy gas containers---software balloon or software, hardware balloon, between the different balloon groups by plumbing connection, on pipeline, connect force lift, be inflation pump and charging and discharging valve, rely on aerating ballon to produce buoyancy, buoyancy gas is implemented in different pressures, the Density Distribution of different balloon groups under the effect of inflation pump pressure, thus automatic guidance buoyancy; The buoyant device bottom connects manned or manned double loading container, and the buoyancy regulation and control are utilization electronic control system or the different densities of computer program control and regulation buoyancy gas between each group balloon, and distribution of pressure is realized; It is characterized in that: the balloon of aircraft has fuel balloon and buoyant balloon; Aircraft uses the fuel gas in the fuel balloon, as producing the powered aircraft movements, supporting the energy that aircraft moves; Rely on the gas in the buoyant balloon to produce lift upwards; Gas in the fuel balloon can be natural fuels, or the methane in the natural fuels, acetylene, ethene, or other is lighter than the non-hydrogen fire gases of air; Gas in the buoyant balloon can be helium, hydrogen, and natural fuels, or the methane in the natural fuels, acetylene, ethene, or other is lighter than the fire gases of air.

2,, it is characterized in that fuel balloon and buoyant balloon both can be provided with respectively by the described high speed remote voyage natural gas airship of claim 1; Also can integrate, promptly with the fuel balloon buoyant balloon of holding concurrently; Be provided with between its " fuel balloon and fire gases buoyant balloon " and " the aircraft remainder " and isolate burning, hi-heat fire-proof curtain; And equipment " fuel balloon or fire gases buoyant balloon " burning causes that high temperature situation " balloon that takes fire " breaks away from the automatic safety device of " aircraft remainder " automatically; The buoyancy of balloon can be regulated and control, and the buoyancy regulation and control are utilization electronic control system or the different densities of computer program control and regulation buoyancy gas between different buoyant balloon, and distribution of pressure is realized.When buoyant balloon does not adopt helium balloon, also have and break away from the aircraft situation at fuel balloon, fire gases buoyant balloon and can produce buoyancy, the inflation mechanism of avoiding aircraft to fall fast.

3, by claim 1 or 2 described high speed remote voyage natural gas airships, the automatic guidance that it is characterized in that the steady weighing apparatus of sporting flying is that distribution, the intensity of using electronic control system or computer program control jet engine or pneumatic pump to be ejected into extraneous air-flow realize.

4,, it is characterized in that the fuel balloon hangs on the independent combustion gas cabin that the sky, aircraft remainder top is combined by some fuel balloons by claim 1 or 2 described high speed remote voyage natural gas airships; Or with the combustion gas cabin that links to each other other part adjacency of aircraft, that combine by some fuel balloons.

5,, it is characterized in that to hang on the independent buoyancy gas cabin that " the aircraft remainder except that the fuel balloon " sky, top is combined by some buoyancy air balloons by claim 1 or 2 described high speed remote voyage natural gas airships; Again with the buoyancy gas cabin that links to each other " the aircraft remainder except that the fuel balloon " adjacency, that combine by some buoyancy air balloons,

6, by claim 1 or 2 described high speed remote voyage natural gas airships, it is characterized in that aircraft at the fuel balloon, the inflation mechanism that fire gases buoyant balloon disengaging aircraft situation can produce buoyancy is: at the fuel balloon, the standby inflation umbrella shape capsule that the windstream that fire gases buoyant balloon disengaging aircraft situation can be risen is relatively heaved naturally, umbrella shape capsule spherical zone shape bottom surface is fixed on the aircraft circumference skeleton, have than the hole that large tracts of land is inner as the umbrella shape capsule and outside air communicates between the circle in the spherical zone shape bottom surface, umbrella shape capsule spherical crown upper top cover is folded on the bottom surface at ordinary times, be in not inflated condition.Fixedly the aircraft circumference skeleton of umbrella shape capsule spherical zone shape bottom surface and aircraft nacelle, passenger cabin skeleton are connected as a single entity.Standby inflation umbrella shape capsule, and fixing skeleton, that the skeleton that links to each other with fuel balloon, fire gases buoyant balloon all adopts is high temperature resistant, fire proofing is made.

7, by claim 1 or 2 described high speed remote voyage natural gas airships, it is characterized in that the isolation burning that is provided with between other parts of the fuel balloon of aircraft and aircraft, hi-heat fire-proof curtain, when the fuel balloon is when hanging on the independent combustion gas cabin that the sky, aircraft remainder top combines by some fuel balloons, serve as to isolate burning, hi-heat fire-proof curtain with the compartment between combustion gas cabin and other parts of aircraft; When fuel balloon during with the continuous combustion gas cabin that is centered around around other parts of aircraft, combines by some fuel balloons, with between combustion gas cabin and other parts of aircraft, with the interval body of wall of fire prevention extinguish material composition as fire-proof curtain.

8, by claim 1 or 2 described high speed remote voyage natural gas airships, it is characterized in that the isolation burning that is provided with between the fire gases buoyant balloon of aircraft and " the aircraft remainder except that the fuel balloon ", hi-heat fire-proof curtain, when the fire gases buoyant balloon is when hanging on the independent combustion gas cabin that " the aircraft remainder except that the fuel balloon " sky, top combines by some fire gases buoyant balloon, serve as to isolate burning, hi-heat fire-proof curtain with the compartment between combustion gas cabin and " the aircraft remainder except that the fuel balloon "; When the fire gases buoyant balloon be with " the aircraft remainder except that the fuel balloon " adjacency, by linking to each other during buoyancy gas cabin that some fire gases buoyant balloon combine, with interval body of wall between combustion gas cabin and " the aircraft remainder except that the fuel balloon ", that form with the fire prevention extinguish material as fire-proof curtain.

9, by claim 1 or 2 described high speed remote voyage natural gas airships, it is characterized in that the high temperature between fuel balloon, fire gases buoyant balloon and the aircraft remainder breaks away from fender guard automatically, when fuel balloon, fire gases buoyant balloon and aircraft remainder are protected the barrier situation with the compartment as one, the employing uniform temperature is flammable, the material that when high temperature, can cut off automatically, the connecting rope of the balloon that acts as a fuel, fire gases buoyant balloon and other parts; When fuel balloon, fire gases buoyant balloon and aircraft remainder are made mutual barrier situation with fire partition, employing is quick with hydrogen, the trip mechanism of thermal element starting, during in order to, temperature-sensitive quick starting, remove the combustion gas cabin at hydrogen, fire gases buoyancy gas cabin is connected with the integral body of aircraft remainder

10, by claim 1 or 2 described high speed remote voyage natural gas airships, it is characterized in that aircraft is employed as the fuel gas in the fuel balloon that produces power, the energy utilization mode of fuel gas is: driving engine can adopt jet engine, or, drive the propelling unit of propeller as navigation for employing combustion engine, electrical motor are driving engine; The pneumatic pump of the regulation and control flight air-flow of aircraft is by internal-combustion engine drives; The inflation pump that regulation and control buoyancy gas distributes between different balloons is by motor drives.Aircraft operation and the required electric power of electrical motor are to supply behind the electric energy by internal combustion engine generator group or fuel cell with the transformation of energy of fuel gas.

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