WO2013159672A1 - 一种飞行汽车 - Google Patents

一种飞行汽车 Download PDF

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Publication number
WO2013159672A1
WO2013159672A1 PCT/CN2013/074370 CN2013074370W WO2013159672A1 WO 2013159672 A1 WO2013159672 A1 WO 2013159672A1 CN 2013074370 W CN2013074370 W CN 2013074370W WO 2013159672 A1 WO2013159672 A1 WO 2013159672A1
Authority
WO
WIPO (PCT)
Prior art keywords
wing
wings
vehicle body
flying
sides
Prior art date
Application number
PCT/CN2013/074370
Other languages
English (en)
French (fr)
Inventor
赵辉
张艺婷
Original Assignee
Zhao Hui
Zhang Yiting
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 CN2012101217859A external-priority patent/CN102616096A/zh
Application filed by Zhao Hui, Zhang Yiting filed Critical Zhao Hui
Publication of WO2013159672A1 publication Critical patent/WO2013159672A1/zh

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60F—VEHICLES FOR USE BOTH ON RAIL AND ON ROAD; AMPHIBIOUS OR LIKE VEHICLES; CONVERTIBLE VEHICLES
    • B60F5/00—Other convertible vehicles, i.e. vehicles capable of travelling in or on different media
    • B60F5/02—Other convertible vehicles, i.e. vehicles capable of travelling in or on different media convertible into aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C37/00—Convertible aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/30—Aircraft characterised by electric power plants
    • B64D27/35—Arrangements for on-board electric energy production, distribution, recovery or storage
    • B64D27/353—Arrangements for on-board electric energy production, distribution, recovery or storage using solar cells
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T10/00—Road transport of goods or passengers
    • Y02T10/60—Other road transportation technologies with climate change mitigation effect
    • Y02T10/7072—Electromobility specific charging systems or methods for batteries, ultracapacitors, supercapacitors or double-layer capacitors
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/50—On board measures aiming to increase energy efficiency

Definitions

  • the invention relates to a vehicle, in particular a flying car.
  • the patent entitled “Flying Cars” disclosed a flying car, both of which used the aerodynamic layout of the front wing of the car body and the main wing at the rear.
  • the canard is an auxiliary wing that is much smaller in area than the main wing and produces only a small amount of lift.
  • Both of the above patents adopt the layout of the canard in front and the main wing in the rear.
  • the pneumatic bearing surface that generates the main lift in flight is still the main wing installed at the rear of the vehicle body, and this aerodynamic layout will lead to the aerodynamic wing.
  • the focus is far from the center of gravity of the flying car, and it is difficult to achieve pitch stability during flight.
  • the Chinese patent number is ZL200920053565.0, and the authorization announcement date is March 10, 2010.
  • the patent entitled “Double-ducted propeller can take off and land the flying car” discloses a vertical take-off and landing flying vehicle.
  • the propeller propeller achieves vertical takeoff and landing and horizontal flight, but without the organic wing, it is impossible to fly long distances.
  • the technical problem to be solved by the present invention is to provide a flying vehicle that can combine the functions of both the automobile and the aircraft.
  • the technical problem to be further solved by the present invention is to realize a vertical take-off and landing function or a water, land, and air amphibious function.
  • a further technical problem to be solved by the present invention is to solve the problem of direct use of solar energy as a power source for automobiles, airplanes and ships.
  • the technical solution adopted by the present invention is: adopting an unconventional aerodynamic layout in aircraft design - aerodynamic layout of tandem wings, and folding wing technology to design a flying car, realizing the basic On the basis of not increasing the size of the existing family car, the larger wing area required for take-off is obtained, which better solves the long-standing problem of combining the car and the aircraft. Further, the present invention solves the design problem of a water, land, and air amphibious flying vehicle by using left and right front pull layouts and wheel lifting techniques. Another improvement of the present invention solves the design challenge of a vertical takeoff and landing flying vehicle by using a tandem wing layout and a tiltable engine technology.
  • the main difference between the aerodynamic layout of the tandem wing and the aerodynamic layout of the duck is that the front and rear wings of the aerodynamic layout of the tandem wing are the main wing, the main function is to generate lift, and the duck-wing aerodynamic layout of the duck wing is an auxiliary machine.
  • the main function of the wing is to assist in maneuvering or aerodynamic coupling to the main wing to increase the lift of the main wing.
  • a specific solution of the present invention is: a flying vehicle including a vehicle body, a wheel mounted on a lower portion of the vehicle body, a main wing mounted on both sides of the vehicle body capable of generating a lifting force, and a propeller mounted on the vehicle body capable of generating a thrust
  • the main wing includes a pair of front wings and a pair of rear wings, the pair of front wings are movably connected to the front sides of the vehicle body and can be folded and retracted, and the pair of rear wings and the rear sides of the vehicle body are movable Connect and fold and retract.
  • the wing roots of the pair of front wings are respectively movably connected to the front wing frames on both sides of the front part of the vehicle body through the front wing connecting device, so that the unfolded front wing can be folded and folded around the front wing connecting device On both sides.
  • the wing roots of the pair of rear wings are respectively movably connected to the rear wing frames on both sides of the rear part of the vehicle body through the rear wing connecting device, so that the unfolded rear wing can be folded and folded around the rear wing connecting device On both sides.
  • the wing roots of the pair of rear wings pass through the rear wing connecting device and the rear of the vehicle body respectively.
  • the two sides are connected to each other, and the inner wing and the outer wing of the rear wing are movably connected by the wing folding device, so that the outer wings of the unfolded rear wing can be respectively turned up to realize that the rear wing is folded in half, and then the pair of rear wings are integrally wound around each other.
  • the rear wing attachment of the wing root rotates horizontally forward and closes to the top of the body.
  • the rear side of the vehicle body is further provided with a rear wing support bar movably connected to the vehicle body, and the rear wing support bar extends obliquely upward to be movably connected with the inner wing of the rear wing.
  • the propeller is installed at the rear of the vehicle body.
  • a nacelle is mounted on each of the left and right sides of the front portion of the vehicle body, and the propeller is installed on each of the nacelles.
  • at least one thruster is mounted on the front of the vehicle body to generate a vertical downward thrust; at least one thruster is mounted on the rear of the vehicle body to generate a vertical downward thrust, and when horizontally mounted, mounted behind the vehicle body The propeller of the section is tilted about 90° to produce the rearward thrust required for horizontal flight.
  • a solar panel is mounted on the upper surface and the lower surface of the pair of front wings and the pair of rear wings, and a solar panel is mounted on the surface of the tail fin and the vehicle body; a battery is mounted on the vehicle body, and the solar panel is mounted on the vehicle body And the battery constitutes a combined power supply system.
  • the flying car is equipped with a life saving umbrella, an in-vehicle airbag and a vehicle airbag.
  • the present invention has the following beneficial effects:
  • the front wing and the rear wing have a large spacing, which together serve as the main pneumatic bearing surface to form a tandem wing layout.
  • the lift of the front and rear wings balances the torque generated by the flying car, and the front machine
  • the aerodynamic interference of the wing to the rear wing is small;
  • the flying car is similar in size to the family car. It can be driven on the road and take off and land. It is better to combine the functions of both the car and the aircraft.
  • the front and rear wings of the flying car and the surface of the body are equipped with large-area solar panels. After the wings are deployed, the whole car becomes a large solar charger, which maximizes the direct and indirect radiation of sunlight. Self-sufficient, green and pollution-free, with good endurance performance, it solves the difficulty of using solar energy as a power for conventional-sized vehicles. question;
  • the amphibious flying vehicle realizes water driving and water take-off and landing; combining the functions of the automobile, the aircraft and the ship;
  • a vertical take-off and landing flying vehicle can be used for long-distance horizontal flight and vertical take-off and landing, combining the functions of a car, a fixed-wing aircraft, and a helicopter;
  • a complete life-saving system is installed on the flying car to solve the safety problem of the home aircraft.
  • Figure 1 is a perspective view of a flying car of the present invention
  • FIG. 2 is a schematic view showing the principle of folding and retracting the wing of the flying car of the present invention
  • Figure 3 is a perspective view of the flying wing of the flying car of the present invention after being folded;
  • Figure 4 is a partial schematic view of the rear wing support bar of the flying car of the present invention.
  • Figure 5 is a perspective view of the amphibious flying vehicle of the present invention.
  • FIG. 6 is a schematic view showing the principle of the upward hoisting of the wheel of the amphibious flying vehicle of the present invention.
  • Figure 7 is a perspective view of a vertical take-off and landing flying vehicle of the present invention with two tilting ducted engines at the rear;
  • Figure S is a vertical take-off and landing flying vehicle of the present invention, and a tiltable ducted engine is mounted at the rear of the vehicle.
  • Figure 9 is a perspective view of the vertical take-off and landing flying vehicle of the present invention.
  • Figure 10 is a schematic illustration of the operation of the lifesaving system of the present invention.
  • the flying car includes a body 1, a front wing 3, a rear wing 6, a propeller 17, a wheel 2, a vertical tail 14 and the like, and the front side of the body 1 is a pair of foldable folds.
  • the front wing 3, the rear side of the body 1 are two rear flaps 6 which are foldably folded, and the wing roots of the pair of front wings 3 pass through the front wing connecting device 4 and the front sides of the front side of the body 1 respectively
  • the wing frame 5 is movably connected, and the wing roots of the pair of rear wings 6 are movably connected to the vertical shafts on the upper rear sides of the vehicle body 1 through the rear wing connecting device 7, respectively, and the rear wing inner wing 8 and the rear wing outer wing 9 pass
  • the inter-wing hinge folding device 10 is connected.
  • the two pairs of wings form a front and rear tandem dual-wing aerodynamic layout along the body 1 and serve as the main pneumatic bearing surface for generating lift.
  • the front wing 3, the rear wing 6, and the vertical tail 14 are mounted with rudder surfaces 16. These rudder surfaces 16 can be used as elevators, ailerons, flaps or other control surfaces, and are also used in combination.
  • a propeller is installed at the rear of the flying vehicle.
  • the propeller 17 includes an engine and a propeller.
  • the engine can directly drive the propeller to rotate or drive the propeller to rotate through the transmission to generate the power required for flight.
  • the front wing 3 and the rear wing 6 are both main wing wings with large wing areas and long wingspans.
  • the front wing 3 has a wingspan of about 6 meters, a chord length of about 0.8 meters, a wing area of about 5 square meters, and a rear wing 6 having a wingspan of about 8 meters.
  • the wing area is about 9 square meters, so the wingspan and chord length of the front wing 3 is at least 60% of the rear wing 6, so that the front and rear pairs of wings are similar in size, all of which are large wing areas.
  • the main wing of the long wingspan, and the front wing 3 and the front part of the body 1 are connected by the front wing connecting device 4, and can be folded and retracted.
  • the front wing connecting device 4 adopts the same two-axis rotating wing folding mechanism as the American ICON A5 aircraft, wherein the axis of the first rotating shaft is the spanwise direction of the wing, and the axis of the second rotating shaft is vertical.
  • the horizontal pair of front wings 3 are first turned around the first axis of rotation to the keel and the ground is substantially perpendicular, and then rotated around the second axis of rotation, and finally The folds are received on both sides of the body 1, and the spanwise direction of the front wing 3 is substantially parallel to the longitudinal axis of the body 1, and the chord is substantially perpendicular to the earth.
  • the rear wing inner wing 8 and the rear wing outer wing 9 are movably connected by the wing-to-wing folding device 10, and the rear side of the body 1 has vertical
  • the shaft and the vertical shaft pass through the rear wing 6 wing root and the rear wing inner wing 8 are firmly connected.
  • the principle is similar to that of the American variable swept-wing fighter F-14.
  • the wing can be rotated in the horizontal plane to realize folding and retracting. .
  • the upward lift is jointly generated to lift the flying car, and the equivalent aerodynamic focus of the front wing 3 and the rear wing 6 is located on the front wing 3
  • the position of the center of gravity of the flying car is close to the position of the equivalent aerodynamic focus and is located in front of the latter.
  • the wing generates a pair of balancing moments on the center of gravity of the flying car.
  • the principle is similar to that of the front and rear two people lifting the sedan.
  • the front and rear lifts are evenly laid out. After adopting the pneumatic layout of the tandem wing, the flying car can get a large enough total wing area, which is enough for the flying car to take off smoothly.
  • a pair of front wings 3 are folded and folded around the front wing connecting device 4, with the wing chord direction being approximately vertical and the spanwise direction being approximately parallel to the vehicle body.
  • the state of the longitudinal axis is closed on both sides of the body 1 and locked; the rear wing outer wings 9 are respectively turned up to realize the wing folding, and the rear wing 6 is horizontally rotated horizontally around the vertical axis of the respective wing roots, respectively. Top and locked.
  • the rear side of the vehicle body 1 is also provided with a rear wing support bar 12 connected by a rear wing support hinge 13, and the rear wing support bar hinge 13 may be spherical.
  • the rear wing support rod 12 extends obliquely upwardly, and is movably connected to the lower surface of the rear wing inner wing 8 and the wing support rod hinge 13 , and the rear wing support rod 12 can be accompanied by the rear wing 6 retracting. activity.
  • a telescopic support link can be used.
  • the present invention may also employ a telescoping wing.
  • the front wing 3 and the rear wing 4 of the flying car unfold, becoming an aircraft with a tandem wing layout, capable of flying fast and taking off and landing on the road, and The airflow interference of the front wing 3 to the rear wing 6 is avoided.
  • the front wing 3 can appropriately adopt the lower contra-angle
  • the rear wing 6 appropriately adopts the upper contra-angle, so that the respective aerodynamic characteristics are independent.
  • the flying car retracts the wing, its outer shape is close to that of an ordinary family car, combining the functions of both the car and the aircraft without obvious defects.
  • the doors can be mounted on conventional side positions. Of course, depending on the mounting position of the pusher 17, the door can also be mounted at the front or the rear of the body 1.
  • lifesaving is an unavoidable problem.
  • the aircraft is equipped with a complete lifesaving system consisting of a life saver 26, an inboard airbag 27 and a underbody airbag 28.
  • At least one of the life-saving umbrellas 26 is mounted on the top of the vehicle body 1 and connected to the integral structural member of the vehicle body 1; a plurality of in-vehicle airbags 27 are installed inside the passenger compartment, in the interior of the cabin and in the vehicle body in front of the occupant, and a plurality of vehicle bottoms are installed.
  • Instantly inflated airbag When an emergency occurs during flight, the life-saving umbrella 26 is thrown and opened.
  • Embodiment 2 When the emergency landing is over, the under-airbag 28 is immediately full of air and popped up, forming an airbag buffer in the lower part of the vehicle body 1 to reduce the impact of the vehicle body on the ground.
  • the impact force achieves a safe soft landing when the flying car is forced to land, and the airbag 27 in the vehicle is opened to protect the safety of the personnel inside the vehicle.
  • the amphibious flying vehicle has a balanced performance of water, land and air to meet the needs of people living in the seaside or rivers and lakes.
  • the left and right sides of the front portion of the vehicle body 1 are each provided with an inclined nacelle 18, and each of the inclined nacelles 18 is provided with a propeller 17 for providing the required pulling force for flight.
  • the propeller 17 is mounted at a high position on the front of the vehicle body 1 at a certain height from the water surface, and is protected by the front lower wing 3 to protect the propeller 17 from splashing water.
  • the propellers on both sides rotate each other to cancel the torque.
  • the bottom of the body 1 is a V-shaped bottom with a ramp angle.
  • the wheel 2 adopts the wheel folding and lifting technology adopted on the current high-speed amphibious vehicle, which can bend the wheel 2 upward and retract, and realize the bottom of the vehicle body 1.
  • the streamlined shape of the shape so that when sailing in the water, the water resistance can be minimized to achieve high-speed take-off and landing on the water;
  • the interior of the body 1 is a plurality of water-sealed cabin structures, which increase the anti-sinking property;
  • a pair of floats 21 are installed on the left Below the right front wing 3, increase the stability of the flying car on the water surface.
  • the pontoon 21 can also be mounted on the lower side of the body 1 to achieve the same anti-rolling effect.
  • the bottom is installed with a water propeller such as a water jet propeller, which is used for water navigation propulsion, and the spout has a vector steering and a reverse spray function, omitting the rudder, and can realize various water navigation states.
  • a water propeller such as a water jet propeller, which is used for water navigation propulsion
  • the spout has a vector steering and a reverse spray function, omitting the rudder, and can realize various water navigation states.
  • tails 14 There are two left and right vertical tails 14 at the rear, and a horizontal tail 15 connects the upper ends of the two vertical tails 14 to form a three-wing layout, which not only strengthens the structural strength, but also serves as an auxiliary pneumatic bearing for the flying vehicle. Surface, used to enhance stability and maneuverability in flight. Of course, other types of tail fins, such as the V-tail, can also be used.
  • the upper surface and the lower surface of the front wing 3 and the rear wing 6 of the flying vehicle are mounted with a solar panel 20, including a plurality of components including the vertical tail 14, the horizontal tail 15, and the vehicle body 1.
  • the solar panel 20 is mounted on the surface, and the effective area is up to several tens of square meters.
  • the solar panel 20 on the upper surface of the wing and the top of the body 1 receives direct radiation from sunlight, the lower surface of the wing, and other parts of the body 1.
  • the solar panel 20 receives indirect radiation reflecting sunlight, which improves the utilization of solar energy, so that the entire vehicle becomes a huge solar charger after the wing is deployed, and the solar panel 20 can obtain at least 10 degrees of electricity during the day, which is enough Driving nearly 100 kilometers. This cleverly solves the problem of direct application of solar power to automobiles, airplanes and ships, and can travel long distances on land or water without charging equipment.
  • a battery 19 is mounted inside the vehicle body 1, and the battery 19 is any type of battery including a battery or a fuel cell, and the solar battery panel 20 and the battery 19 constitute a hybrid power supply system.
  • the solar panel 20 When the solar panel 20 is insufficiently powered and has no light intake, it can be switched to the battery power supply mode, or the battery power supply is also powered by the solar panel 20, which can greatly extend the flight or flight time of the flying vehicle.
  • the front wing 3 and the rear wing 6 can adaptively adjust the upper and lower reverse angles so that the sun rays illuminate the surface of the wing as perpendicularly as possible, thereby improving solar photovoltaic power generation efficiency.
  • Embodiment 3 is a diagrammatic representation of Embodiment 3
  • a coaxial twin propeller vertical takeoff and ducted duct thruster 23 is mounted on the front of the vehicle body 1 to provide a vertical downward thrust, and the propeller rotates in a horizontal plane without generating torque to the vehicle body 1 in the ducted intake air.
  • Two upper cover plates 24 are connected to the body 1 hinge, and the exhaust port is provided with an array of parallel multi-piece baffles 25, the array of baffles 25 and the body 1 Active connection.
  • the array of multi-piece baffles 25 can be deflected to achieve control of the in-flight roll attitude.
  • the upper cover 24 of the duct inlet and the array of the deflector 25 of the exhaust port are deflected, substantially covering the duct opening, sealing the body 1, and reducing flight resistance.
  • the two tail-mounted single propellers of the rear of the vehicle can tilt the ducted propellers 22, and the respective propeller blades rotate in opposite directions to cancel the torque.
  • the two propellers 17 at the rear of the vehicle can be tilted by approximately 90 degrees. To produce the backward thrust required for horizontal flight.
  • the upper vertical cover 24 and the lower baffle 25 of the front vertical take-off duct thruster 23 are opened, and the front and rear engines are simultaneously started to generate downward thrust, and the flying car is gradually lifted off the ground.
  • the flying car opens the front and rear pairs of wings in the air, then the two tilting ducted propellers 22 at the rear of the car start to tilt while increasing the thrust, generating a horizontal backward thrust component, and the flying car is gradually obtained.
  • the forward flight speed, the wing generates more and more lift and finally the flying car is lifted up and the flight, the upper cover 24 and the lower baffle 25 are closed, and the two tilting ducted propellers 22 at the rear of the vehicle are tilted About 90 degrees.
  • the flying car is in a horizontal flight state.
  • the above inverse process is performed when transitioning from a horizontal flight to a vertical landing state.
  • Embodiment 4 is a diagrammatic representation of Embodiment 4:
  • the wing roots of a pair of front wings 3 are movably connected to the front wing frames 5 on both sides of the front side of the vehicle body 1 through the front wing connecting device 4, respectively, so that the deployed front wing 3 can surround the front
  • the wing connecting device 4 is folded and folded and closed on both sides of the vehicle body 1;
  • the wing roots of the pair of rear wings 6 are movably connected to the rear wing frame 11 on both sides of the rear portion of the vehicle body 1 through the rear wing connecting device 7, respectively, so that the wings are connected
  • the rear wing 6 can be folded over around the rear wing connecting device 7 and then received on both sides of the vehicle body 1.
  • a vertical take-off and ducting duct thruster 23 is mounted on the front of the vehicle body 1, the propeller rotates in a horizontal plane to generate a vertical downward thrust, and the outlet of the duct is mounted with an array of parallel multi-piece baffles 25, diversion
  • the array of sheets 25 is movably connected to the body 1.
  • the deflector 25 can be deflected to conduct the flow of the inflow and the downwash flow, reducing the ducted airflow resistance or intentionally increasing
  • the inflow and outflow resistance of the large duct can cancel the torque generated on the vehicle body 1 when the single propeller rotates in the front portion, and can also appropriately control the deflection of the deflector 25 to achieve the control of the roll attitude during flight.
  • a deflectable aerodynamic rudder surface 16 can also be mounted below the propeller.
  • a coaxial propeller tilting ducted fan thruster 22 is mounted to the rear of the body 1 so that no torque is applied to the body 1 during the tilting process.
  • the outlet of the duct is also equipped with an array of parallel multi-piece baffles 25, which adjusts the attitude of the body 1 during vertical take-off and landing.
  • the tail tilting ducted fan thruster 22 When transitioning from the vertical takeoff state to the horizontal flight state, the tail tilting ducted fan thruster 22 is gradually tilted by about 90 degrees. , causing the propeller to rotate in the plane of the vertical axis of the vertical body 1 to generate the backward thrust required for horizontal flight. After fully transferring to the horizontal flight, the flying car is completely propelled by the tilting ducted fan propeller 22 of the tail.
  • the array of baffles 25 of the upper and lower inlet and outlet of the vertical take-off and ducting propeller 23 at the front of the vehicle is deflected to substantially cover the ducted passage, and functions to aerodynamically rectify and seal the vehicle body 1 to reduce flight resistance.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Transportation (AREA)
  • Mechanical Engineering (AREA)
  • Other Liquid Machine Or Engine Such As Wave Power Use (AREA)
  • Motorcycle And Bicycle Frame (AREA)

Abstract

一种采用串列式气动布局的折叠机翼飞行汽车，包括车身（1），安装于车身下部的车轮（2），安装于车身两侧的能够产生向上升力的主机翼，以及安装于车身上能够产生推力的推进器（17），其中前机翼（3）和后机翼（6）均为大翼面积和长翼展的主机翼，飞行汽车的机翼展开时，前机翼和后机翼沿车身构成纵向串列式气动布局，共同产生向上的抬升力。飞行汽车的机翼收起时，前机翼翻转折叠后收在车身两侧，后机翼翻转折叠后收在车身顶部或车身两侧。机翼和车身安装有大面积的太阳能电池板（20），全车成为一个大太阳能充电器，增加续航能力。本发明还在此基础上进一步实现了垂直起降飞机汽车和水路空飞行汽车。

Description

一种飞行汽车
技术领域
本发明涉及一种交通工具， 尤其是一种飞行汽车。
背景技术
将汽车和飞机两种运输工具结合起来， 是人类由来已久的一个想法。 到目前为止， 国内 外出现过不少飞行汽车方案和一些产品实物， 多具有各种各样的设计缺陷。 例如美国的 Terrafugia飞行汽车和莫尔顿.泰勒的飞行汽车，只能称作可在公路上行驶的折叠机翼飞机。与 本发明最相近的几个国内外专利， 如美国专利号 US6619584B11 , 名称为 《ROAD/AIR VEHICLE》的专利中公开了一种飞行汽车， 以及中国专利申请号为 CN201110047409.5, 公开 日为 2011年 7月 27日， 名称为 《飞行汽车》 的专利中公开了一种飞行汽车， 这两种飞行汽 车都釆用了车身前部安装鸭翼， 车身后部安装主翼的气动布局。 在飞行器设计中， 鸭翼是一 种辅助机翼， 其面积比主机翼小得多， 仅产生少量升力。 以上两个专利均采用了鸭翼在前、 主翼在后的布局方式， 飞行中产生主要升力的气动承力面仍是安装在车身后部的主翼， 而这 种气动布局方式将导致机翼气动焦点与飞行汽车的重心相距较远，飞行时难以取得俯仰稳定。 中国专利号为 ZL200920053565.0, 授权公告日为 2010年 3月 10日， 名称为 《双涵道螺旋桨 可垂直起降飞行汽车》 的专利中， 公开了一种可垂直起降飞行汽车， 依靠涵道螺旋桨推进器 实现垂直起降和水平飞行， 但是却不带有机翼， 无法远距离飞行。
内燃机汽车排放的废气造成了严重的大气污染。 太阳能是可再生的清洁能源， 但由于太阳 能的不稳定性、 分散性， 常规尺寸大小的汽车、 飞机、 船舶等直接使用太阳能作为动力是目 前难以克服的瓶颈。
总之， 以上方案和实物都无法实现汽车和飞机的较好结合， 也无法解决直接使用太阳能作 为动力能源的难题。
发明内容 针对上述现有技术存在的缺陷， 本发明要解决的技术问题是提供一种飞行汽车， 可结合汽 车和飞机二者功能。
本发明进一步要解决的技术问题是实现垂直起降功能或水陆空三栖功能。
本发明更进一步要解决的技术问题是解决汽车、 飞机和船舶直接使用太阳能作为动力能源 的问题。
为了解决上述技术问题， 本发明所采用的技术方案是： 采用了飞机设计中一种非常规气动 布局——串列机翼气动布局， 以及折叠机翼技术， 来设计飞行汽车， 实现了在基本不增加现 有家用轿车尺寸的基础上， 获得了起飞所需的较大机翼面积， 较好解决了汽车和飞机二者结 合这个长久以来的难题。 进一步， 本发明釆用左、 右前拉布局和车轮提升技术解决了水陆空 三栖飞行汽车设计难题。 本发明的另一改进， 利用串列翼布局和可倾转发动机技术解决了垂 直起降飞行汽车设计难题。
串列机翼气动布局和鸭式气动布局的主要区别在于， 串列机翼气动布局的前、 后机翼均 为主机翼， 主要作用是产生升力， 而鸭式气动布局的鸭翼是辅助机翼， 主要作用是辅助操纵 或与主机翼近距离气动耦合以增加主机翼的升力。
本发明具体解决方案是： 一种飞行汽车， 包括车身， 安装于车身下部的车轮， 安装于车身 两侧的能够产生向上升力的主机翼， 以及安装于车身上能够产生推力的推进器， 所述主机翼 包括一对前机翼和一对后机翼， 所述一对前机翼与车身前部两侧活动连接并能折叠收放， 所 述一对后机翼与车身后部两侧活动连接并能折叠收放。
所述一对前机翼的翼根分别通过前机翼连接装置与车身前部两侧的前机翼架活动连接， 使 得展开的前机翼能够围绕前机翼连接装置翻转折叠后收于车身两侧。
所述一对后机翼的翼根分别通过后机翼连接装置与车身后部两侧的后机翼架活动连接， 使 得展开的后机翼能够围绕后机翼连接装置翻转折叠后收于车身两侧。
后机翼还有另一种折叠方式， 所述一对后机翼的翼根分别通过后机翼连接装置与车身后部 两侧活动连接， 后机翼的内翼和外翼通过翼间折叠装置活动连接， 使得展开的后机翼的外翼 可以分别向上翻转实现后机翼对折， 然后一对后机翼整体绕各自翼根的后机翼连接装置向前 方水平旋转， 收于车身顶部。
进一步的， 所述车身的两侧还安装有与车身活动连接的后机翼支撑杆， 该后机翼支撑杆斜 向上伸出， 与后机翼的内翼活动连接。
进一步的， 所述推进器安装在车身尾部。
进一步的， 所述车身前部的左右两侧各安装有一个短舱， 每个短舱上各安装有所述推进器。 进一歩的， 至少一个推进器安装在车身的前部， 以产生垂直向下的推力； 至少一个推进器 安装在车身后部， 以产生垂直向下的推力， 当水平飞行时， 安装在车身后部的所述推进器倾 转约 90° ， 以产生水平飞行所需的向后的推力。
进一步的， 所述一对前机翼和一对后机翼的上表面和下表面安装有太阳能电池板， 尾翼和 车身的表面安装有太阳能电池板； 车身上安装有电池， 所述太阳能电池板和所述电池组成联 合供电系统。
进一步的， 该飞行汽车上安装有救生伞、 车内安全气囊和车底安全气囊。
有益效果
本发明对比已有技术具有以下有益效果：
1. 前机翼、 后机翼的间距大， 共同作为主要气动承力面， 形成串列机翼布局， 飞行中， 前、 后机翼的升力对飞行汽车产生的力矩相互平衡， 且前机翼对后机翼的气动干扰小；
2. 前、 后机翼折叠收起机翼后， 飞行汽车与家用轿车大小相近， 可在公路上行驶和起飞 降落， 较好结合汽车和飞机二者的功能；
3. 飞行汽车的前、 后机翼和车身各部位的表面安装有大面积太阳能电池板， 机翼展开后 整个汽车成为一个大太阳能充电器， 最大限度利用了阳光的直接辐射和间接辐射， 能源自给 自足且绿色无污染， 续航性能好， 解决了常规尺寸的交通工具直接利用太阳能作为动力的难 题；
4. 本发明的另一种改进， 三栖飞行汽车实现了水上行驶和水上起飞降落； 结合了汽车、 飞 机和船舶三者的功能；
5. 本发明的另一种改进， 垂直起降飞行汽车可以远距离水平飞行和垂直起飞降落， 结合了 汽车、 固定翼飞机、 直升机三者的功能；
6. 飞行汽车上安装有完备的救生系统， 解决了家用飞行器的安全问题。
具体实施方式
下面结合附图对本发明的具体实施方式做进一步详细的说明。
图 1是本发明飞行汽车的立体示意图；
图 2是本发明飞行汽车的机翼折叠收放原理示意图；
图 3是本发明飞行汽车的机翼折叠收起后的立体示意图；
图 4是本发明飞行汽车的后机翼支撑杆局部示意图；
图 5是本发明三栖飞行汽车立体示意图；
图 6是本发明三栖飞行汽车车轮向上收起原理示意图；
图 7是本发明垂直起降飞行汽车， 车尾装有两部可倾转涵道发动机的立体示意图； 图 S是本发明垂直起降飞行汽车、 车尾装有一部可倾转涵道发动机的立体示意图； 图 9是本发明垂直起降飞行汽车收起机翼的立体示意图；
图 10是本发明的救生系统工作示意图。
图中： 1.车身， 2.车轮， 3.前机翼， 4.前机翼连接装置， 5.前机翼架， 6.后机翼， 7.后机翼连 接装置， 8.后机翼内翼， 9.后机翼外翼， 10.翼间折叠装置， 11.后机翼架， 12.后机翼支撑杆， 13.后机翼支撑杆铰链， 14.垂直尾翼， 15.水平尾翼， 16.舵面， 17.推进器， 18.短舱， 19.电池， 20.太阳能电池板， 21.浮筒， 22.可倾转涵道推进器， 23.垂直起降涵道推进器， 24.上盖板， 25. 导流片， 26.救生伞， 27.车内安全气囊， 28.车底安全气囊。 实施例一：
参见附图 1、 2， 本飞行汽车包括车身 1、 前机翼 3、 后机翼 6、 推进器 17、 车轮 2、 垂直尾 翼 14等部件， 车身 1前部两侧是可翻转折叠的一对前机翼 3 , 车身 1后部两侧是可翻转折叠 的两副后机翼 6， 一对前机翼 3的翼根分别通过前机翼连接装置 4与车身 1前部两侧的前机 翼架 5活动连接， 一对后机翼 6的翼根分别通过后机翼连接装置 7与车身 1后上方两侧的竖 轴活动连接， 后机翼内翼 8和后机翼外翼 9通过翼间铰链折叠装置 10连接。这两对机翼沿车 身 1构成前后串列式双主翼气动布局， 共同作为产生升力的主要气动承力面。 其中前机翼 3、 后机翼 6、 垂直尾翼 14上安装有舵面 16， 这些舵面 16可以作为升降舵、 副翼、 襟翼或其他 操纵面使用， 还混合使用。
飞行汽车的车尾安装一部推进器 17，推进器 17包括发动机和螺旋桨，发动机可以直接驱动 螺旋桨旋转或通过传动装置驱动螺旋桨旋转， 以产生飞行所需的动力。
与常用于增强飞机操纵性或产生耦合涡增强主机翼升力的小型辅助机翼- -鸭翼不同，所述前 机翼 3和后机翼 6均为大翼面积和长翼展的主机翼， 在本实施例子中， 前机翼 3的翼展约为 6米， 弦长约为 0.8米， 机翼面积约为 5平方米， 后机翼 6的翼展约为 8米， 弦长约为 1.1米， 机翼面积约为 9平方米， 这样前机翼 3的翼展和弦长至少相当于后机翼 6的 60%以上， 这样 前、 后两对机翼大小相近， 均为大翼面积和长翼展的主机翼， 而且前机翼 3与车身 1前部两 侧通过前机翼连接装置 4连接， 并可折叠收放。
在本实施例中，前机翼连接装置 4采用与美国 ICON A5飞机相同的两轴旋转机翼折叠机构， 其中第一个旋转轴的轴线是机翼翼展方向， 第二个旋转轴的轴线垂直于大地， 在收起前机翼 3时， 水平状态的一对前机翼 3先围绕第一个旋转轴翻转到翼弦与大地基本垂直状态， 再绕 第二个旋转轴向后旋转， 最后折叠收于车身 1两侧， 这时前机翼 3的翼展方向基本平行于车 身 1纵轴， 翼弦与大地基本垂直。
后机翼内翼 8和后机翼外翼 9通过翼间折叠装置 10活动连接， 车身 1后上方两侧分别有竖 轴， 竖轴穿过后机翼 6翼根与后机翼内翼 8牢固连接， 原理与美国变后掠翼战斗机 F-14的活 动装置相类似， 机翼可在水平面内旋转， 实现折叠收放。
飞行汽车的前机翼 3和后机翼 6展开飞行时， 共同产生向上的升力将飞行汽车抬起来飞行， 这时前机翼 3和后机翼 6共同的等效气动焦点位于前机翼 3和后机翼 6之间， 飞行汽车的重 心位置与等效气动焦点的位置接近并位于后者的前方， 机翼对飞行汽车的重心产生一对平衡 力矩， 原理类似于前后两人抬轿子， 这样前后升力布局均匀。 本飞行汽车采用了串列机翼气 动布局后， 可以得到足够大的机翼总面积， 足以让本飞行汽车顺利起飞。
如附图 3所示， 当飞行汽车收起机翼时， 一对前机翼 3围绕前机翼连接装置 4翻转折叠， 以机翼翼弦方向大约为竖直、 翼展方向大约平行于车体纵轴的状态收于车身 1两侧并锁定； 后机翼外翼 9分别向上翻转实现机翼对折， 后机翼 6再分别整体绕各自翼根的竖轴向前方水 平旋转， 收于车身 1顶部并锁定。
参见附图 4， 为了改善后机翼 6的结构受力， 车身 1 的两侧还安装有以后机翼支撑杆铰链 13连接的后机翼支撑杆 12， 后机翼支撑杆铰链 13可以采用球形铰链， 后机翼支撑杆 12斜向 上伸出， 与后机翼内翼 8的下表面以后机翼支撑杆铰链 13活动连接， 后机翼支撑杆 12可伴 随着后机翼 6的收放而活动。在后机翼 6旋转过程中， 后机翼支撑杆 12长度受限时， 可采用 伸缩式支撑连杆。
除了折叠机翼， 本发明还可采用伸缩机翼。
当在公路上要起飞时， 本飞行汽车前机翼 3和后机翼 4展开， 就变成一架串列机翼布局的 飞机， 能远距离快速飞行并在公路上起飞和降落， 同时为了避免前机翼 3对后机翼 6的气流 干扰， 飞行中前机翼 3可适当采用下反角、 后机翼 6适当采用上反角， 实现了各自气动特性 的独立。
本飞行汽车收起机翼时， 外形尺寸接近普通家用轿车， 结合了汽车和飞机二者的功能而不 具有明显缺陷。 车门可安装在常规的两侧位置。 当然视推进器 17的安装位置， 车门也可安装在车身 1前部 或后部。
对于飞行器来说， 救生是无法回避的问题。 参见附图 10， 本飞行汽车上安装有完备的救生 系统， 由救生伞 26、 车内安全气囊 27和车底安全气囊 28组成。 其中至少一个救生伞 26安 装在车身 1顶部并与车身 1整体结构件连接； 若干个车内安全气囊 27安装在乘员舱内部， 位 于舱内顶部和乘员面前的车体内， 车底安装有若干个可瞬时充气的安全气囊。 当飞行时遇到 紧急情况时， 救生伞 26抛出并打开， 在紧急迫降落地时， 车底安全气囊 28立即充满气并弹 出， 构成车身 1下部的气囊缓冲区， 减轻车体撞击地面所受的冲击力， 实现飞行汽车迫降时 的安全软着陆， 同时车内安全气囊 27打开， 保护车内人员安全。 实施例二：
本实施例为三栖飞行汽车， 水陆空综合性能均衡， 以满足生活在海边或河流湖泊地区人 们的需要。
参见附图 5、 6， 所述车身 1前部的左、 右两侧各安装有一个倾斜的短舱 18， 每一个倾斜短 舱 18上各安装有推进器 17， 用于提供飞行所需拉力。 推进器 17安装在车身 1前部较高的位 置， 距离水面一定高度， 而且得到前下方的前机翼 3保护， 免受溅起的水花损坏推进器 17。 两侧的螺旋桨旋转时互相抵消扭矩。 车身 1的底部为带有斜升角的 V形底部， 所述车轮 2采 用目前高速水陆两栖车上采用的车轮翻折提升技术， 可以让车轮 2向上方弯折收起， 实现了 车身 1底部外形的流线型， 这样在水中航行时， 可以最大限度的减少水中阻力， 实现了水上 高速起飞和降落； 车身 1内部为多个水密封舱结构， 增大抗沉性； 一对浮筒 21安装在左、 右 前机翼 3下方， 增加飞行汽车在水面的稳定性。 当然浮筒 21也可安装在车身 1两侧下方， 同 样能起到减摇效果。
在水上航行时， 除了可使用车身 1前部的左右两侧的推进器 17空气动力推进， 也可以在车 底安装如喷水推进器一类的水中推进器， 用于水上航行推进， 且喷口具有矢量转向和倒喷功 能， 省略了船舵， 可以实现各种水上航行状态。
车尾有左右两部垂直尾翼 14， 一个水平尾翼 15将两部垂直尾翼 14的上端连接，构成三翼 面布局， 这样既加强了结构强度， 并且水平尾翼 15作为飞行汽车的一个辅助气动承力面， 用 于增强飞行中的安定性和操纵性。 当然也可以采用 V型尾翼等其他类型的尾翼。
本实施例中，飞行汽车的前机翼 3、后机翼 6的上表面和下表面安装有太阳能电池板 20， 包括所述垂直尾翼 14、水平尾翼 15和车身 1在内的多个部件的表面安装有太阳能电池板 20， 有效面积可达数十平方米以上，机翼上表面和车身 1顶部等部位的太阳能电池板 20接受来自 太阳光的直接辐射，机翼下表面和车身 1其他部位等的太阳能电池板 20接受反射阳光的间接 辐射， 提高了对太阳能的利用率， 这样机翼展开后整个汽车成为一个巨大的太阳能充电器， 太阳能电池板 20—个白天可以得到至少 10度电能， 足以行驶近百公里。 这样巧妙的解决了 汽车、 飞机、船舶直接应用太阳能驱动的难题， 可在缺乏充电设备的陆地或水上远距离旅行。
所述车身 1的内部安装有电池 19， 所述电池 19是包括蓄电池或燃料电池在内的任意类 型电池， 所述太阳能电池板 20和所述电池 19组成混合供电系统。 当太阳能电池板 20电力不 足且无光线摄入时， 可切换至蓄电池供电模式， 或者蓄电池供电的同时也利用太阳能电池板 20供电， 可以大大延长飞行汽车的航程或航时。
在充电时， 前机翼 3和后机翼 6可以自适应调整上、 下反角度， 使得太阳光线尽量垂直照 射机翼表面， 提高太阳能光伏发电效能。
其他内容同实施例一。
实施例三：
参见附图 7， 一部共轴式双螺旋桨垂直起降涵道推进器 23安装在车身 1前部， 提供垂直 向下的推力， 螺旋桨在水平面内旋转不对车身 1产生扭矩， 在涵道进气口设置两扇与车身 1 铰链连接的上盖板 24， 排气口设置有平行的多片式导流片 25阵列， 导流片 25阵列与车身 1 活动连接。多片式导流片 25阵列可以进行偏转， 以实现飞行中侧倾姿态的控制。水平飞行时， 涵道进气口的上盖板 24和排气口的导流片 25阵列都进行偏转， 基本掩盖了涵道口， 密封车 身 1， 减小飞行阻力。
车尾的安装两部并列的单螺旋桨可倾转涵道推进器 22， 各自的螺旋桨叶片旋转方向相反， 以相互抵消扭矩。 由垂直起飞状态向水平飞行状态过渡时， 车尾的两部推进器 17 可倾转约 90度。 ， 以产生水平飞行所需的向后的推力。
当飞行器垂直起飞时，打开前部垂直起降涵道推进器 23的上盖板 24和下部导流片 25阵 列， 前后发动机同时发动， 产生向下的推力， 将飞行汽车渐渐抬升离地， 这时飞行汽车在空 中张开前、后两对机翼， 然后车尾的两部可倾转涵道推进器 22加大推力的同时开始倾转， 产 生一个水平向后的推力分量， 飞行汽车于是逐渐获得前飞速度， 机翼产生越来越大的升力并 最终将飞行汽车抬起来飞行， 上盖板 24和下部导流片 25关闭， 车尾的两部可倾转涵道推进 器 22倾转到约 90度。 ， 这时飞行汽车处于水平飞行状态。
当由水平飞行向垂直降落状态过渡时， 执行上述逆过程。
其他内容同以上实施例。
实施例四：
垂直起降飞行汽车还有另一种实现方式。
参见附图 8、 9, 一对前机翼 3的翼根分别通过前机翼连接装置 4与车身 1前部两侧的前 机翼架 5活动连接， 使得展开的前机翼 3能够围绕前机翼连接装置 4翻转折叠后收于车身 1 两侧；一对后机翼 6的翼根分别通过后机翼连接装置 7与车身 1后部两侧的后机翼架 11活动 连接， 使得展开的后机翼 6能够围绕后机翼连接装置 7翻转折叠后收于车身 1两侧。
一部垂直起降涵道推进器 23安装在车身 1前部， 螺旋桨在水平面内旋转， 以产生垂直向 下的推力， 涵道的出口安装有平行的多片式导流片 25阵列， 导流片 25阵列与车身 1活动连 接。 导流片 25可以进行偏转， 对入流和下洗气流进行导流， 减小涵道进出气流阻力或有意增 大涵道进出气流阻力， 可以抵消前部的单螺旋桨旋转时对车身 1产生的扭矩， 而且还可以适 当控制导流片 25偏转， 以实现飞行中对侧倾姿态的控制。 如果是导流片 25阵列是固定偏角 的， 还可以在螺旋桨的下方安装可偏转的气动舵面 16。
一部共轴螺旋桨可倾转涵道风扇推进器 22安装在车身 1后部， 这样在倾转过程中， 不会 给车身 1造成扭矩。涵道的出口同样安装有平行的多片式导流片 25阵列， 在垂直起降过程中 起调整车身 1姿态等作用。
当由垂直起飞状态向水平飞行状态过渡时，车尾的可倾转涵道风扇推进器 22逐渐倾转约 90度。 ， 使螺旋桨在垂直车身 1纵轴的平面内旋转以产生水平飞行所需的后向推力， 完全转 入水平飞行后， 飞行汽车完全依靠车尾的可倾转涵道风扇推进器 22推进， 而车前部的垂直起 降涵道推进器 23的上、下进出口的导流片 25阵列偏转到基本掩盖了涵道口，起到气动整流， 密封车身 1， 减小飞行阻力的作用。
其他内容同以上实施例。
以上结合附图对本发明的具体实施方式作了说明， 但这些说明不能被理解为限制了本发明 的范围， 本发明的保护范围由随附的权利要求书限定， 任何在本发明权利要求基础上的改动 都在本发明的保护范围内。

Claims

1. 一种飞行汽车， 包括车身， 安装于车身下部的车轮， 安装于车身两侧的能够产 生向上升力的主机翼， 以及安装于车身上能够产生推力的推进器， 其特征在于， 所 述主机翼包括一对前机翼和一对后机翼， 所述一对前机翼与车身前部两侧活动连接 并能折叠收放， 所述一对后机翼与车身后部两侧活动连接并能折叠收放。
2. 根据权利要求 1所述的飞行汽车， 其特征在于， 所述一对前机翼的翼根分别通过 前机翼连接装置与车身前部两侧的前机翼架活动连接， 使得展开的前机翼能够围绕 前机翼连接装置翻转折叠后收于车身两侧。
3. 根据权利要求 2所述的飞行汽车， 其特征在于， 所述一对后机翼的翼根分别通过 后机翼连接装置与车身后部两侧的后机翼架活动连接， 使得展开的后机翼能够围绕 后机翼连接装置翻转折叠后收于车身两侧。
4. 根据权利要求 2所述的飞行汽车， 其特征在于， 所述一对后机翼的翼根分别通过 后机翼连接装置与车身后部两侧活动连接， 后机翼的内翼和外翼通过翼间折叠装置 活动连接， 使得展开的后机翼的外翼可以分别向上翻转实现后机翼对折， 然后一对 后机翼整体绕各自翼根的后机翼连接装置向前方水平旋转， 收于车身顶部。
5. 根据权利要求 4所述的飞行汽车， 其特征在于， 所述车身的两侧还安装有与车身 活动连接的后机翼支撑杆，该后机翼支撑杆斜向上伸出，与后机翼的内翼活动连接。
6. 根据权利要求 3或 4所述的飞行汽车， 其特征在于， 所述推进器安装在车身尾部。
7. 根据权利要求 3或 4所述的飞行汽车， 其特征在于， 所述车身前部的左右两侧各 安装有一个短舱， 每个短舱上各安装有所述推进器。
8. 根据权利要求 3或 4所述的飞行汽车， 其特征在于， 至少一个推进器安装在车身 的前部， 以产生垂直向下的推力； 至少一个推进器安装在车身后部， 以产生垂直向 下的推力， 当水平飞行时， 安装在车身后部的所述推进器倾转约 90°， 以产生水平飞 行所需的向后的推力。
9. 根据权利要求 3或 4所述的飞行汽车， 其特征在于， 所述一对前机翼和一对后机 翼的上表面和下表面安装有太阳能电池板，尾翼和车身的表面安装有太阳能电池板; 车身上安装有电池， 所述太阳能电池板和所述电池组成联合供电系统。
10. 根据权利要求 3或 4所述的飞行汽车， 其特征在于， 该飞行汽车上安装有救生伞、 车内安全气囊和车底安全气囊。
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