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WO2000047470A2 - Systeme de transport aerien personnel sans ailes - Google Patents

Systeme de transport aerien personnel sans ailes Download PDF

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Publication number
WO2000047470A2
WO2000047470A2 PCT/US2000/002456 US0002456W WO0047470A2 WO 2000047470 A2 WO2000047470 A2 WO 2000047470A2 US 0002456 W US0002456 W US 0002456W WO 0047470 A2 WO0047470 A2 WO 0047470A2
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WO
WIPO (PCT)
Prior art keywords
pat
engine
thrusters
platform
craft
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/US2000/002456
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English (en)
Other versions
WO2000047470A3 (fr
WO2000047470B1 (fr
Inventor
Karl F. Milde, Jr.
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Individual
Original Assignee
Individual
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Priority claimed from US09/352,522 external-priority patent/US6179247B1/en
Application filed by Individual filed Critical Individual
Priority to AU46398/00A priority Critical patent/AU4639800A/en
Publication of WO2000047470A2 publication Critical patent/WO2000047470A2/fr
Publication of WO2000047470A3 publication Critical patent/WO2000047470A3/fr
Publication of WO2000047470B1 publication Critical patent/WO2000047470B1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
    • B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
    • B64C29/0016—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers
    • B64C29/0025—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers the propellers being fixed relative to the fuselage
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft

Definitions

  • the present invention relates to a wingless, personal air transport or "PAT" which is capable of taking off and landing vertically as well as hovering, if desired.
  • the wingless PAT can maneuver, forward and back as well as side to side, and is capable of traveling forward at a reasonable speed.
  • VTOL Small vertical take-off and landing
  • the most well known is the helicopter which operates with powered rotor blades arranged above the craft body that rotate about a substantially vertical axis, and a powered tail rotor that rotates about a substantially horizontal axis.
  • the pitch of the tail rotor blades is controlled in the cockpit by two pedals — one for the right foot and one for the left — which permit the operator to rotate the craft about the vertical axis or to hold it in a fixed, stable orientation by pressing on the right or left pedal, as desired.
  • the pitch of the upper rotor blades is controlled by two levers: an up-down lever which changes the pitch if all blades at once and a directional "joystick" that selectively changes the pitch of the blades as they rotate through a 360° arc.
  • the joystick is used to tilt the craft and thus impart lateral motion.
  • Another craft which is capable of VTOL utilizes shrouded rotor blades for extra lift. Instead of arranging the lifting blades in open air, as in the case of a helicopter, they are placed in a vertical "wind tunnel". As air is drawn in, it passes over a smooth upper rim of the tunnel, reducing the air pressure on this rim in accordance with Bernoulli's Principal.
  • Such a shroud thus not only prevents the air from exiting laterally outward, horizontally from the rotor blades, it also adds lift by this application of Bernoulli's Principal, thereby adding a multiple of about 1.5 to the static thrust as compared to an unshrouded set of rotor blades.
  • VTOL craft which utilize shrouded rotor blades are therefore considerably more efficient and require less energy to remain airborne.
  • Aircraft of this type are known from the U.S. Patent Nos. 3,614,030; DES 292,194; 5,213,284 and 5,881,970.
  • PAT personal air transport
  • a stable, shrouded platform with a plurality N of thrusters distributed around a circle substantially equidistant from each other, with each thruster arranged to provide upward thrust along a substantially vertical axis. If the number N of thrusters is made equal to or greater than five, the PAT can retain its stable orientation in space and continue to fly even in the event of a thruster failure.
  • the present invention takes advantage of the fact that small yet powerful internal combustion (IC) engines, as well as jet engines, are available commercially.
  • the power-to-weight ratio of such engines is approximately one horsepower per pound, which is comparable to that of larger, air-cooled IC engines used for winged aircraft.
  • the invention may make use of so-called "air amplifiers" which utilize the coanda effect. Such air amplifiers are also available commercially.
  • twin cylinder reciprocating engine with opposed pistons, or possibly even a Wankel engine.
  • the two cylinder IC engine has the additional advantage, over a single cylinder engine, that it will continue to operate, even though one of the two cylinders may temporarily cease producing power.
  • the IC engine drives a propeller having a diameter in the range of 12-24 inches. This dictates that the engine should have a cubic inch displacement in the range of 2.0 to 5.0.
  • the propeller will have more than two blades, preferably four or more, for maximum thrust.
  • a muffler system is provided to substantially muffle the noise of the various engines.
  • a system may include a single large muffling "ring" which surrounds the PAT and receives the exhaust from all engines.
  • the PAT may be powered by a plurality of one or two-cylinder, four cycle IC engines available commercially from Echo, Inc., Lake Zurich, Illinois 60047. Such an engine may deliver over 100 pounds of static thrust when outfitted with a multiple blade, 24 inch propeller with a 12 inch pitch.
  • the PAT may be powered by a plurality of Zenoah model airplane IC engines, such as the model GT-74, 4.45 cubic inch, twin cylinder engine which delivers 6 horsepower to drive a 22 x 12 or 24 x 10 inch twin blade propeller at 7200 RPM.
  • Zenoah model airplane IC engines such as the model GT-74, 4.45 cubic inch, twin cylinder engine which delivers 6 horsepower to drive a 22 x 12 or 24 x 10 inch twin blade propeller at 7200 RPM.
  • two engines are arranged back to back with their crankshafts on a common axis.
  • the propellers of the two engines will be driven in opposite directions, minimizing the loss of energy caused by moving the air laterally, in a direction offset from the common axis.
  • Such a combination of IC engines, or a single IC engine, which drives one or more propellers or fans, or alternatively a jet engine, air amplifier or the like, that moves air downward in the axial direction and thereby provides upward thrust, is herein termed a "thruster.”
  • ten of these thrusters may be designed to lift over 1000 pounds without a shroud. In a shrouded configuration ten such engines should be able to lift about 1.5 times this weight or 1500 pounds. Assuming a craft weight of 700 pounds (including thrusters weighing 200 lbs.) plus a full tank (40 gallons) of fuel weighing 300 pounds, the craft will be able to lift a payload of about 500 pounds.
  • All of the thrusters are controlled as a group to cause the craft to rise, fall or hover.
  • the speed of each thruster is also controlled separately in a manner to be described hereinbelow to cause the craft to tilt in any desired direction and thus to move horizontally.
  • the thruster throttles are controlled by servo-motors which, in turn, are controlled electronically.
  • a first throttle lever is used by the operator to increase or decrease the thrust of all thrusters at once.
  • a joystick is used to control the relative thrusts of the thrusters and thus the tilt of the craft.
  • pedals are provided to enable the operator to rotate the craft. These pedals mechanically actuate two "paddles” or flaps arranged beneath the thrusters on opposite sides of the craft, in the downwash of the driven air, to rotate the craft about its vertical axis.
  • the PAT according to the invention is preferably configured as follows:
  • a substantially horizontal circular inner platform is arranged at the center of the craft to carry the craft passengers.
  • the inner platform carries a seat for at least one person and has a preferably transparent, hemispherical enclosure arranged as a "bubble" over the passenger seat for protecting the passengers of the craft and providing a smooth surface for the flow of air.
  • the enclosure extends downward to the circular outer extremity of the inner platform which has a diameter Dl.
  • a substantially horizontal annular outer platform is arranged coaxially and surrounds the inner platform.
  • the outer platform has a central opening with a second diameter D2 , this second diameter being greater than the first diameter.
  • the annular outer platform has a shroud forming a substantially smooth upper surface extending inward and downward into the space between the inner platform and outer platform.
  • At least one thruster is arranged in the space between the inner and outer platforms for forcing air downward to lift and propel the craft.
  • a thruster may comprise a single IC engine, centrally arranged on the inner platform, for driving fan blades disposed in the space between the inner and outer platforms which rotate about the central vertical axis of the craft.
  • a plurality of thrusters may be arranged in the space between the inner and outer platforms, thus providing a measure of safety in case a thruster should fail.
  • five or more thrusters are arranged in a circle, equidistant from each other.
  • the IC engines are started one-by-one by a single electric motor which moves in a circle and engages the spinner or hub of each respective engine. As each engine is rotated to start it, electric power is applied to the engine glow plug or spark plug. Once the engine has started, the mechanical power of the starter is removed and thereafter applied to the next engine in succession.
  • the PAT is preferably outfitted with casters, allowing the craft to be rolled by hand into a garage or the like.
  • the PAT is also provided with a flexible dust skirt, enabling it to hover on sand or water, if desired. This skirt collapses when the craft is lowered onto the casters.
  • telescoping "stilts” are provided to absorb the landing shock. These stilts are retracted when the craft is flying and while the craft is being rolled on its casters.
  • the center of gravity of the passengers (and luggage) disposed gravitationally below the level at which the thrusters lift the craft.
  • the system for selectively varying the thrust of the thrusters thereby to tilt the craft and cause it to move in the horizontal direction
  • the passenger seat(s) can be made to pivot forward and backward so that the passenger (s) can remain substantially level, even though the PAT craft may tilt forward (for traveling forward) or backward (for traveling backward) .
  • Fig. 1 is a perspective view of the wingless, personal air transport (PAT) according to a preferred embodiment of the present invention.
  • PAT personal air transport
  • Fig. 2 is a cross-sectional view of the PAT of Fig. 1 showing the relative positions of the major components.
  • Fig. 3 is a top view of the PAT of Fig. 1.
  • Fig. 4 is a bottom view of the PAT of Fig. 1.
  • Fig. 5 is a detailed view of the cockpit of the PAT of Fig. 1.
  • Fig. 6 is a detailed view of a portion of the control panel of the PAT of Fig. 1.
  • Fig. 7 is a detailed view of an engine of the PAT of Fig. 1.
  • Fig. 8 is a detailed view of a landing "stilt" of the PAT of Fig. 1.
  • Fig. 9 is a diagram of a PAT showing the minimum number of thrusters for fail-safe operation.
  • Fig. 10 is a detailed view of the starter mechanism of the PAT of Fig. 1.
  • Fig. 11 is a detailed diagram of a craft rotator flap or "paddle", used for rotating the PAT about its central vertical axis.
  • Fig. 12 is a diagram of the electronic circuit for actuating the throttle servos of the thrusters.
  • Fig. 13 is a top view of a portion of the PAT showing an alternative embodiment for balancing and steering the craft according to the invention.
  • Fig. 14 is a side view of the cockpit portion of the PAT shown in Fig. 13.
  • Fig. 15 is a detailed diagram showing a particular design of a thruster for the PAT of Fig. 1.
  • Fig. 16 is a top view showing the propeller blades of the thruster of Fig. 15.
  • Fig. 17 is a representational diagram of an engine or prime mover which rotates two coaxial shafts in opposite directions.
  • Fig. 18 is a detailed diagram of a mechanism used in the engine of Fig. 17 for connecting the oppositely rotating shafts.
  • Fig. 19 is a representational diagram illustrating the operation of the mechanism of Fig. 18.
  • Fig. 20 is a representational diagram of a reciprocating engine of the type shown in Fig. 17.
  • Fig. 21 is a top view of a PAT according to the invention having two external, horizontal thrusters.
  • Fig. 22 is a side view of a PAT having external thrusters as shown in Fig. 21.
  • Fig. 23 is a side elevational view of a PAT having two counter-rotating propeller blades.
  • Fig. 24 is a bottom view of the PAT of Fig. 23 showing one of the propeller blades.
  • Fig. 25 is a representational diagram showing an alternative embodiment of the blade configuration for the PAT of Fig. 23.
  • Fig. 26 is a representational diagram of a jet engine suitable for use as a thruster in the PAT according to the invention.
  • Fig. 27 is a perspective view of the PAT, according to another preferred embodiment of the present invention, having a plurality of thrusters, such as jet engines, arranged in a circle outside the inner platform.
  • thrusters such as jet engines
  • Fig. 1 is an illustration of the wingless PAT 10 in flight.
  • the craft comprises a circular inner platform 12 having a clear plastic bubble in the shape of a hemisphere.
  • the inner platform supports two passenger/operators 29 and 30 on seats 22 within the bubble as well as the controls, indicated by the joystick 24.
  • the bubble is provided with a door (not shown) for the passengers.
  • annular outer platform 14 Surrounding and connected to the inner platform 12 is an annular outer platform 14. Like the inner platform, the outer platform has a smooth, rounded upper surface extending inward and downward toward the annular region 16 between the two platforms. As indicated in Fig. 1, this region is covered by a protective screen but air is drawn downward into the space by thrusters comprising engines 18 and propellers 20 (Fig. 2) , and exhausted out the bottom. Each thruster engine may operate a single, multiblade propeller, or may operate two propellers, as shown, which are rotated in the same or opposite direction. As the air passes over the upper surfaces of the inner and outer platforms it reduces the pressure on these surfaces, in accordance with Bernoulli's Principal, increasing the lift or upward thrust produced by the engines.
  • the outer platform 14 comprises an upper annulus 11 which encloses a plurality of fuel tanks 13 (e.g., thirteen, one per thruster) arranged symmetrically about the circle, an outer shroud 15 and an inner shroud 17. These shrouds as well as a dust-catching skirt 15a, are configured to prevent the air forced downward by the propellers 20 from recycling upward and entering the driven airstream again.
  • fuel tanks 13 e.g., thirteen, one per thruster
  • the outer platform 14 also includes an exhaust muffling system (not shown) for the engines, whereby all engine exhaust is supplied to a single muffler and then released downward into free space.
  • an exhaust muffling system (not shown) for the engines, whereby all engine exhaust is supplied to a single muffler and then released downward into free space.
  • FIG. 3 there are shown the two passengers 29 and 30 sitting in the center of the craft on the inner platform. Thirteen engines 18 and propellers 20 surround the inner platform and these, in turn, are surrounded by the outer platform 14. In the upper right quadrant of the diagram there is indicated an electric starter motor 36. More will be said about this starter motor in connection with Fig. 10.
  • Fig. 4 shows the reverse (bottom) side of the PAT.
  • the engines 18 are opposed, two cylinder IC engines, preferably four-cycle in operation.
  • the engines and attached to the outer platform are four casters 32 interspersed by four landing "stilts" (shock absorbers) 34. More will be said about these landing stilts (LS) in connection with Fig. 8.
  • Fig. 3 and 4 illustrate the respective size (diameters) of the inner and outer platforms.
  • the inner platform has an outer diameter Dl whereas the outer platform has an inner diameter D2>D1.
  • the difference (D2 minus Dl or D3) is slightly greater than the diameter of the propellers 20.
  • the outer diameter Dl is 6 feet
  • the inner diameter D2 is between 8 and 10 feet
  • the overall diameter D4 is between 10 and 12 feet.
  • the space D3 for the propellers is therefore approximately in the range of 1 to 2 feet.
  • the Zenoah twin-cylinder reciprocating engine referred to above, may operate with a multi-blade, 22 inch propeller having a 12 inch pitch.
  • two such engines, with their propellers, are arranged back to back on a common axis to form each thruster.
  • Fig. 5 illustrates the cockpit controls for the craft.
  • Joystick 24 is used in its conventional way to orient the craft front to back and side to side.
  • This control adjusts the relative speeds of the engines to cause the craft to tilt. For example, pushing the joystick forward causes the rearward engines of the craft to increase in speed and (if desired) the front engines to decrease their speed slightly, thereby increasing the relative lift in the back and causing the craft to tilt forward. This forward tilt results in the craft moving forward in the horizontal direction.
  • the control arms 26 are throttle controls which operate all engines simultaneously and in unison. If this arm or lever is pulled upward, the engines speed up, causing the craft to rise. If this lever is pushed down, the craft is allowed to sink. At one particular setting of the lever 26 the craft will hover.
  • the joystick 24 and lever 26 operate variable resistors in an electrical circuit that produces the proper pulse code modulated (PCM) signals for the engine throttle servos.
  • PCM pulse code modulated
  • Each engine is controlled by its own individual servo which rotates the throttle spindle of the engine.
  • the electronic circuit for this function will be explained in connection with Fig. 12.
  • Pedals 28 operate flaps or "paddles" on opposite sides of the craft, as shown in Figs. 2, 4 and 11. These flaps move in opposite directions in the airstream to rotate the craft.
  • the rotator flaps 52 are pivoted about an axis 54 and are operated by cables 56 mechanically connected to the pedals 28. Pressing the right pedal causes the craft to rotate clockwise; pressing the left pedal causes it to rotate counter-clockwise.
  • Fig. 6 shows a portion of the instrument panel 38 relating to engine control and operation.
  • the usual navigation instruments e.g., gyro and magnetic compass
  • gyro and magnetic compass have been omitted for reasons of clarity.
  • the top row of gauges 40 shows the fuel level in four separate tanks: front, rear, left side and right side. While there may be more fuel tanks (e.g., one per engine as noted above) it is assumed that the fuel levels in four tanks around the periphery of the craft are representative of the fuel levels in all tanks.
  • the next line relates to the landing stilts of the craft.
  • This landing gear will be described in detail in connection with Fig. 8.
  • a single switch 42 for raising and lowering all landing stilts as a group.
  • four lights 44 which indicate whether each respective landing stilt is in the extended (landing) position.
  • the remaining rows on the instrument panel are numbered 1, 2, 3 ... 12, 13. These numbers specify an engine number on the craft.
  • a starter button 46 for the starter motor for the starter motor, an on/off switch 48 for the engine ignition or glow plug(s) and an over-heat temperature light 50.
  • These controls enable the operator to start each respective engine and to monitor it during flight. Engines are switched off by moving the throttle lever 26 to the "off" position, thereby preventing fuel from entering the engines.
  • Fig. 7 is an illustration of a single engine 18 and its associated propeller 20 and spinner hub 21.
  • the engine is a twin piston and cylinder type internal combustion engine.
  • the opposed cylinders are outfitted with glow plugs 47.
  • a suitable voltage e.g. 1.5 volts
  • the engine 18 is attached to the craft 12 , 14 by means of bracket members 19.
  • An "X" configuration of these brackets is shown, but any suitably robust arrangement will suffice.
  • Engine exhaust is ported to the exhaust muffler system (not shown) in the outer platform 14.
  • Fig. 8 shows a telescoping landing stilt 60 which is preferably attached to, and extends downward from the outer annular platform 14.
  • the landing stilt is pneumatically operated by an air pump 62, that is capable of pumping air in either of two directions. This air is conveyed to or from the landing stilt 60 via a tube 64 connected to the attachment bracket 63.
  • the telescoping elements 65, 66, 67 and 68 extend downward and provide a pneumatic spring and shock absorber for landing.
  • the telescoping elements retract.
  • a small pad or "foot” 69 ensures that the landing stilt secures a firm footing on the ground.
  • Fig. 9 illustrates the advantage of having at least five separate thrusters 18, 20 on the PAT craft. Assuming that each thruster drives at least one propeller 20, preferably mounted coaxially with the engine drive shaft, it may be seen that five thrusters 18A, 18B, 18C, 18D and 18E, spaced equidistantly around the inner platform 12 are the minimum number required for fail-safe operation. If one of these thrusters fails, the remaining four will be able to lift and support the craft without causing it to flip over.
  • the craft will also continue to fly or, if there is insufficient lift, to at least hover or descend slowly while maintaining a level platform.
  • Fig. 9 shows only five propellers 20A, 20B, etc. , one for each thruster engine. It is also possible for each thruster engine to drive two or more propellers about a common axis or even about multiple axes by providing a suitable mechanical linkage. For example, five engines arranged equidistantly as shown in Fig. 9 could drive a total of ten propellers arranged in a circle in the manner shown in Fig. 3.
  • Fig. 10 illustrates how the engines 18 may be started using an electric starter motor 36. This starting motor has a chuck 23 which engages the spinner hub 21 of each engine 18. The starter motor 36 is arranged on a ring or a track that surrounds the inner platform 12 and is caused to move around the platform 12 stopping at each engine, in turn, to start it.
  • the starter may be incremented to this engine and engaged with the engine for starting.
  • Fig. 12 is a block diagram of the electronic circuit 70 used to control the thirteen servos that operate the throttles of the thirteen engines.
  • the joystick 24 selectively varies the resistance of a star-shaped array of resistors 72 which receive a constant voltage V at this center point.
  • the output voltages of the various resistors are converted to digital numbers in a series of analog-to-digital converters 73.
  • the throttle lever 26 adjusts the resistance of a single variable resistor 74 causing the input voltage V to vary.
  • the output voltage is then converted to a digital number by an analog-to-digital converter 75.
  • the outputs of the A/D converters 73 and 75 are read by a microcomputer 71 which also receives a vertical reference signal from a gyroscopic device 76.
  • the gyroscopic device maintains a stable horizontal platform and outputs a reference signal indicating the angular deviation of the PAT craft from the horizontal. Stated another way, the device 76 continuously informs the microcomputer which way is vertically "down" .
  • Other inputs 79 to the microcomputer 71 may comprise GPS generated information defining the craft's position on the globe (latitude and longitude) ; altimeter generated information regarding the craft's altitude above sea level and above ground; compass generated information as to the direction of true north; radar generated information as to the position and distance to other objects, etc.
  • the microcomputer calculates the throttle values required to orient the craft in the manner selected by the joystick 24 and the throttle lever 26. In so doing, the microcomputer insures that the craft will not be tilted so far in any direction, for example more than 30° from the horizontal, as to dangerously reduce the lift or tumble over. The microcomputer also insures that the craft will land "softly”; that is, that the craft speed in downward direction will be reduced as the craft approaches the ground. Finally, the microcomputer serves a collision-avoidance function to prevent mid-air collisions with other craft or other solid objects.
  • Figs. 13 and 14 illustrate how the PAT craft may be controlled by shifting the weight of the passenger (s) . As is best seen in Fig. 13, the passenger seat may be moved in the horizontal direction, either forward or back, to the right or to the left, or a combination of these movements, to change the position of the center of gravity of the craft.
  • the center of gravity or CG of a seated person is located approximately at the position of the person ' s navel, or at the point where the seat belt passes across the person's torso. If this CG point is moved horizontally from a central position on the craft, the craft will tilt. This tilting may be used, either in addition to, or instead of the individual engine throttle control described above, to maneuver the craft horizontally.
  • Fig. 14 shows the position of the CG 80 at substantially the center of the craft.
  • Fig. 14 also shows a pivot point 81 either through the bottom of, or beneath the seat 22 about which the passenger 29 may be tipped forward or backward. In this way, the passenger can remain substantially level even though the craft is tilted sharply forward when traveling in the forward direction.
  • Fig. 15 illustrates a preferred embodiment of a thruster for the personal air transport.
  • the thruster comprises an engine 85 mounted within the annular region 16 between the inner platform 12 and the outer platform 14.
  • the engine 85 rotates two propellers 86 and 87 either in the same direction or, preferably, in opposite rotational directions.
  • the propellers are preferably multi-blade propellers for increased efficiency, as illustrated, in top view, in Fig. 16.
  • the engine drives the propellers at speeds up to 7500 RPM or 125 revolutions per second.
  • Such propellers may have a maximum diameter of about 21 inches to maintain the tip speed below about .7 times the speed of sound or 700 feet per second.
  • the maximum tip speed at 125 revolutions per second is:
  • the blades operating at 125 revolutions/second can move air at a maximum of 125 feet per second.
  • Fig. 17 illustrates a thruster 90 which drives counter rotating shafts 91 and 92.
  • the thruster comprises a first prime mover 94, a second prime mover 95 and a central transmission 96 which couples the two shafts 91 and 92 for counter rotation.
  • the prime movers 94 and 95 produce substantially the same horsepower so that the transmission 96 operates to synchronize the engines together, rather than to transmit a substantial amount of power from one to the other.
  • the transmission 96 is illustrated in Figs. 18 and 19. As illustrated there, the shafts 91 and 92 are both coupled mechanically to a separate shaft 98.
  • the shafts 91 and 92 are both coupled mechanically to a separate shaft 98.
  • the shafts 91 and 92 are both coupled mechanically to a separate shaft 98.
  • the pulley 102 surrounds two pulley wheels 104 and 105 of identical diameter.
  • the shafts 91 and 92 rotate at the same speed, but in opposite directions.
  • the prime movers 94 and 95 in Fig. 17 are preferably internal combustion engines such as reciprocating piston engines or Wankel engines.
  • the cylinders 106 and 107 may be arranged in opposed relationship, as illustrated in Fig. 20, so that the pistons 108 and 109, respectively, will move in exactly opposite directions, thus reducing engine vibration due to imbalance of the reciprocating parts.
  • Figs. 21 and 22 illustrate the addition of small thrusters 110 and 112 on opposite sides of the personal air transport.
  • These thrusters which may be small jet engines, rocket motors, shrouded motor driven propellers or air amplifiers which utilize the coanda effect, or fans, operate to speed the craft in the forward direction and, upon reversal of thrust by rotating the engines to the position shown in dashed lines 112a, the thrusters serve to rapidly break the forward motion of the vehicle in mid-air.
  • Figs. 23 and 24 illustrate an alternative embodiment whereby two large fans are driven about a central vertical axis of the craft.
  • a first fan 114 operates (rotates) in one direction while a second fan 116 rotates in the opposite direction.
  • Fixed blades 118 redirect the air as it is forced downward at an angle by the blades 114.
  • the engine 120 preferably comprises two separate engines and a central transmission, as are shown in Fig. 17 , for counter rotating the fan blades 114 and 116 about the central shafts 122 and 124, respectively.
  • the engines 120 receive fuel from the fuel tanks in the outer platform 14 via tubes 126. These tubes also serve to transport liquid coolant from small radiators (not shown) within the airstream generated by the fans 114 and 116.
  • Fig. 25 illustrates an alternative embodiment whereby the fans 114 and 116 may be composed of successive fan blades 114a and 114b, 116a and 116b, respectively. In between the rotating blades 114 and 116 are a series of fixed blades 118a, 118b and 118c. These blades are designed to provide the maximum upward thrust available in a configuration of this type.
  • individual thrusters in the form of jet engines may be provided, as illustrated in Fig. 26, with each thruster in its own separate cylindrical channel 120 as illustrated in Fig. 27.
  • the thrusters may be in the form of air amplifiers which utilize the coanda effect. Air pressure for driving such air amplifiers may be obtained from a jet engine or from an air pump driven by an internal combustion engine. Air amplifiers are available commercially from Exair Corp. (See “www.exair.com”) .
  • Fig. 27 shows the personal air transport having eight air thrusters, such as jet engines, arranged in eight separate, cylindrical channels.
  • thrusters of the type illustrated in Fig. 2 or in Fig. 15 can be disposed in the individual, cylindrical channels.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Emergency Lowering Means (AREA)
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Abstract

L'invention concerne un système de transport aérien sans ailes comprenant deux parties principales. Premièrement, une plate-forme interne circulaire sensiblement horizontale dont l'extrémité externe a un premier diamètre (D1), laquelle comporte un siège accueillant au moins une personne et un carénage formant une surface supérieure lisse qui s'étend vers l'extérieur et vers le bas jusqu'à l'extrémité externe. Deuxièmement, une plate-forme externe annulaire sensiblement horizontale coaxiale par rapport à la plate-forme interne, laquelle a une ouverture centrale de second diamètre (D2) et un carénage formant une surface supérieure sensiblement lisse qui s'étend vers l'intérieur et vers le bas dans l'ouverture centrale. Le second diamètre (D2) est supérieur au premier diamètre (D1). De préférence, au moins cinq propulseurs sont disposés dans l'espace compris entre les plates-formes interne et externe pour fournir une poussée d'air vers le bas. De préférence également, une bulle hémisphérique en plastique transparent est placée sur le haut de la plate-forme interne pour protéger les passagers et assurer un écoulement fluide de l'air.
PCT/US2000/002456 1999-02-09 2000-02-01 Systeme de transport aerien personnel sans ailes Ceased WO2000047470A2 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AU46398/00A AU4639800A (en) 1999-02-09 2000-02-01 Wingless, personal air transport

Applications Claiming Priority (8)

Application Number Priority Date Filing Date Title
US24716399A 1999-02-09 1999-02-09
US09/247,163 1999-02-09
US10309399A 1999-04-08 1999-04-08
US29/103,093 1999-04-08
US09/352,522 1999-07-13
US09/352,522 US6179247B1 (en) 1999-02-09 1999-07-13 Personal air transport
US11525599A 1999-12-09 1999-12-09
US29/115,255 1999-12-09

Publications (3)

Publication Number Publication Date
WO2000047470A2 true WO2000047470A2 (fr) 2000-08-17
WO2000047470A3 WO2000047470A3 (fr) 2000-12-14
WO2000047470B1 WO2000047470B1 (fr) 2001-01-18

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2000/002456 Ceased WO2000047470A2 (fr) 1999-02-09 2000-02-01 Systeme de transport aerien personnel sans ailes

Country Status (2)

Country Link
AU (1) AU4639800A (fr)
WO (1) WO2000047470A2 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2011004186A3 (fr) * 2009-07-06 2011-07-07 Aesir Limited Embarcation et procédé d'assemblage d'embarcation à spin contrôlé
US11377220B1 (en) 2021-09-27 2022-07-05 Hoversurf, Inc. Methods of increasing flight safety, controllability and maneuverability of aircraft and aircraft for implementation thereof
US11383831B1 (en) * 2021-06-01 2022-07-12 Hoversurf, Inc. Methods of vertical take-off/landing and horizontal straight flight of aircraft and aircraft for implementation
US11541999B2 (en) 2021-06-01 2023-01-03 Hoversurf, Inc. Methods of vertical take-off/landing and horizontal straight flight of aircraft and aircraft for implementation

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US3082977A (en) * 1960-07-06 1963-03-26 Arlin Max Melvin Plural rotor sustained aircraft
DE1756879A1 (de) * 1968-07-26 1970-10-01 Karl Jaeger Flugscheibe
US3614030A (en) * 1969-12-10 1971-10-19 Paul S Moller Aircraft
CH568187A5 (fr) * 1973-09-25 1975-10-31 Kaelin J R
US4457476A (en) * 1981-11-20 1984-07-03 Frank Andresevitz Wingless aircraft
US5239830A (en) * 1992-03-05 1993-08-31 Avco Corporation Plural engine power producing system

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2011004186A3 (fr) * 2009-07-06 2011-07-07 Aesir Limited Embarcation et procédé d'assemblage d'embarcation à spin contrôlé
US9162764B2 (en) 2009-07-06 2015-10-20 Aesir Limited Craft and method for assembling craft with controlled spin
US11383831B1 (en) * 2021-06-01 2022-07-12 Hoversurf, Inc. Methods of vertical take-off/landing and horizontal straight flight of aircraft and aircraft for implementation
US11541999B2 (en) 2021-06-01 2023-01-03 Hoversurf, Inc. Methods of vertical take-off/landing and horizontal straight flight of aircraft and aircraft for implementation
US11377220B1 (en) 2021-09-27 2022-07-05 Hoversurf, Inc. Methods of increasing flight safety, controllability and maneuverability of aircraft and aircraft for implementation thereof

Also Published As

Publication number Publication date
AU4639800A (en) 2000-08-29
WO2000047470A3 (fr) 2000-12-14
WO2000047470B1 (fr) 2001-01-18

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