CN111498106A - Tilting hybrid electric-transmission vertical take-off and landing fixed-wing unmanned aerial vehicle - Google Patents
Tilting hybrid electric-transmission vertical take-off and landing fixed-wing unmanned aerial vehicle Download PDFInfo
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- CN111498106A CN111498106A CN202010405391.0A CN202010405391A CN111498106A CN 111498106 A CN111498106 A CN 111498106A CN 202010405391 A CN202010405391 A CN 202010405391A CN 111498106 A CN111498106 A CN 111498106A
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- 230000007246 mechanism Effects 0.000 claims abstract description 16
- 239000000463 material Substances 0.000 claims description 5
- 230000005540 biological transmission Effects 0.000 claims description 4
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 3
- 239000004917 carbon fiber Substances 0.000 claims description 3
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 3
- 230000009977 dual effect Effects 0.000 claims description 2
- 230000005611 electricity Effects 0.000 claims description 2
- 230000005484 gravity Effects 0.000 claims description 2
- 238000000034 method Methods 0.000 abstract description 16
- 230000008569 process Effects 0.000 abstract description 12
- 239000000446 fuel Substances 0.000 abstract description 7
- 230000002035 prolonged effect Effects 0.000 abstract description 3
- 230000033001 locomotion Effects 0.000 description 2
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/28—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
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- 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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
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- B64D27/026—
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/11—Propulsion using internal combustion piston engines
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
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- Electric Propulsion And Braking For Vehicles (AREA)
Abstract
The invention discloses a tilting hybrid electric-transmission vertical take-off and landing fixed wing unmanned aerial vehicle, which comprises: fuselage, tail, rotor subassembly, the subassembly and the power component of verting, power component installs in the fuselage, including oil tank, engine, generator and battery, the output shaft drive generator work of engine, and the battery is connected with the generator and the motor that verts respectively through the cable. By adopting the technical scheme of combining the hybrid system and the tilting mechanism, the unmanned aerial vehicle can fully utilize the characteristic of high energy density of a fuel engine, so that the flight time and the hovering time are greatly prolonged, and the performance is optimized and improved; meanwhile, double backup is provided for an energy system, and the aircraft can normally fly even if the engine fails; in the fixed-point hovering process, when the suspended fixed-wing aircraft hovers, only batteries are used for supplying power, the energy of the generator is increased, and the output of the battery power is reduced, so that the hovering time can be increased by more than one time compared with the hovering time of a common conventional fixed-wing unmanned aerial vehicle.
Description
Technical Field
The invention relates to a fixed wing unmanned aerial vehicle, in particular to a tilting hybrid electric drive vertical take-off and landing fixed wing unmanned aerial vehicle, and belongs to the technical field of unmanned aerial vehicles.
Background
The unmanned aerial vehicle is an unmanned aerial vehicle mainly controlled by radio remote control or a qualification program, has the advantages of small volume, low cost, convenient use and maintenance and the like, and has rapidly increased application requirements in the fields of national defense and civil use. Along with the development of technology, unmanned aerial vehicle's performance constantly promotes, and the kind also constantly increases. The unmanned aerial vehicle is classified according to power sources and can be divided into an electric unmanned aerial vehicle, an oil-driven unmanned aerial vehicle, an oil-electricity hybrid unmanned aerial vehicle and other energy (such as hydrogen fuel) unmanned aerial vehicles; the unmanned aerial vehicle is classified according to purposes and can be classified into a military unmanned aerial vehicle, an industrial unmanned aerial vehicle, a consumer unmanned aerial vehicle and the like; according to the flight platform classification, can be divided into fixed wing unmanned aerial vehicle, rotor unmanned aerial vehicle and other flight platforms.
The fixed wing unmanned aerial vehicle is an unmanned aerial vehicle which generates forward thrust or pull force by a power device, generates lift force by wings fixed on a body, flies in the atmosphere and is heavier than air. Wherein, the definition of VTOL fixed wing unmanned aerial vehicle is: can take off/land at zero speed, has hovering capability and can fly horizontally in a fixed wing mode. Compared with the traditional aircraft, the drooping fixed-wing unmanned aerial vehicle has the performance advantages of high flying speed, long voyage and long voyage of the fixed-wing aircraft, and can finish take-off and landing in small-area and complex areas such as mountainous areas, jungles and surface ships with limited fields and airspaces, thereby being more and more widely valued in the industry.
The fixed wing unmanned aerial vehicle that hangs down mainly can divide into: three types of power, tailstock formula and the compound power of verting, the power formula of verting unmanned aerial vehicle that hangs down realizes rotor or jet engine from level to vertically interconversion through the mechanism of verting, and power overcomes the resistance along the horizontal direction during horizontal flight, and power overcomes gravity along the vertical direction during vertical flight. However, existing tilt-VTOL fixed wing drones also have some limitations.
The invention patent with the application number of 201710981102 discloses an oil-electricity hybrid power unmanned aerial vehicle with vertical take-off and landing fixed wings for long-term navigation, which adopts a parallel layout of three bodies to enable the bodies to have more load spaces, and a tilting mechanism and an oil-driven variable-pitch mechanism are combined to bring higher pneumatic efficiency and higher load capacity. The unmanned aerial vehicle takes off, cruises, descends the in-process, and first fuel power tilting pitch system and second fuel power tilting pitch system provide the main vertical lift in vertical take-off and landing stage, and first lift motor, second lift motor provide the supplementary vertical lift in vertical take-off and landing stage, and four driving system combinations provide the required gesture adjusting moment of every single move and roll. This unmanned aerial vehicle will lead to the flight to break off when the engine breaks down, has four driving system moreover, and whole energy utilization efficiency is lower.
Disclosure of Invention
In order to solve the defects of the prior art, the invention aims to provide the tilting hybrid electrically-driven vertical take-off and landing fixed-wing unmanned aerial vehicle, which combines the characteristics of hybrid movement and tilting, is beneficial to improving the flight time and the hovering time, has double backup for an energy system, and can normally fly even if an engine fails.
In order to achieve the above object, the present invention adopts the following technical solutions:
a tilting hybrid electrically-driven vertical take-off and landing fixed wing drone, comprising:
the airplane body comprises an airplane body and a pair of wings symmetrically arranged on two sides of the airplane body, and the pair of wings are provided with arms extending along the axial direction of the airplane body at the same positions;
a tail;
the rotor assembly comprises a plurality of rotors and power motors for driving the rotors;
the tilting assembly is arranged at the front end of the arm and comprises a tilting motor and a tilting mechanism, and the tilting mechanism enables the tilting motor to be switched between a horizontal state and a vertical state;
the power assembly is installed in the machine body and comprises an oil tank, an engine, a generator and a battery, the output shaft of the engine drives the generator to work, and the battery is connected with the generator and the tilting motor through cables respectively.
Preferably, aforementioned rotor is two, divides to establish and installs the back end in the horn, power motor installs in the rotor below, for unmanned aerial vehicle provides the supplementary lift in the stage of hanging down.
Preferably, the tail comprises a pair of vertical tails and a horizontal tail, wherein the vertical tails are arranged at the tail part of the arm downwards, the horizontal tail is connected with the tail end of the arm, and the yaw moment and the pitch moment of the unmanned aerial vehicle can be adjusted through the tail.
Preferably, the body is made of carbon fiber material.
More preferably, the focus of aforementioned power component is located the axis in organism to ensure that unmanned aerial vehicle weight distributes evenly, thereby ensures to fly steadily.
More preferably, the unmanned aerial vehicle further comprises an electric control module, the engine and the generator are both connected with the electric control module, and the electric control module is used for controlling an engine throttle and performing energy distribution control on electric energy of the generator.
Still preferably, the battery is a secondary battery.
Further preferably, when the unmanned aerial vehicle flies flatly, the generator provides advancing power energy for the fixed wing unmanned aerial vehicle, and simultaneously provides a charging demand for the battery.
Still further preferably, this unmanned aerial vehicle has energy system double backup, and when the engine broke down, the battery started promptly and provides the power source, further improves unmanned aerial vehicle security and reliability, avoids flight trouble.
The invention has the advantages that:
(1) the vertical take-off and landing fixed wing unmanned aerial vehicle adopts the technical scheme of combining the hybrid system and the tilting mechanism, so that the unmanned aerial vehicle can fully utilize the characteristic of high energy density of a fuel engine, the flight time and the hovering time are greatly prolonged, and the performance is optimized and improved; meanwhile, double backup is provided for an energy system, and the aircraft can normally fly even if the engine fails;
(2) the tilting motor is provided with a tilting mechanism, and is in a vertically upward state in a vertical stage to provide upward pulling force; compared with the traditional battery power supply for the similar unmanned aerial vehicle in the vertical lifting stage, the invention can share the output of the battery in the vertical lifting process due to the adoption of the tilting motor, so that the battery with smaller capacity can be used, the weight of the battery is reduced by about 50 percent, the weight of the whole unmanned aerial vehicle is reduced, and the energy utilization rate is further improved;
(3) in the process of horizontal flight, the tilting motor is in a horizontal state to provide horizontal tension for forward flight; meanwhile, the generator can provide advancing power energy for the fixed-wing unmanned aerial vehicle, and more electricity can also provide charging requirements for the battery, so that the battery is ensured to be in a full-charge state in each landing process, and the flight safety is ensured; if the engine fails in the flying process, the battery is started in time, so that double backup of an energy system is realized, and the aircraft can fly normally when the engine fails;
(4) in the fixed-point hovering process, when the suspended fixed-wing aircraft hovers, only batteries are used for supplying power, the energy of the generator is increased, and the output of the battery power is reduced, so that the hovering time can be increased by more than one time compared with the hovering time of a common conventional fixed-wing unmanned aerial vehicle.
Drawings
Fig. 1 is a top view of an embodiment of a tilt hybrid electrically-driven vtol fixed wing drone of the present invention;
FIG. 2 is a front view of the embodiment shown in FIG. 1;
FIG. 3 is a side view of the embodiment shown in FIG. 1;
FIG. 4 is a schematic illustration of the connection of the powertrain of the present invention;
fig. 5 is a partially enlarged schematic view of fig. 3.
The meaning of the reference symbols in the figures: 1. fuselage, 2, wing, 3, horn, 4, vertical tail, 5, horizontal tail, 6, rotor, 7, the motor that verts, 8, the mechanism that verts, 9, the oil tank, 10, the engine, 11, the generator, 12, the battery, 13, preceding rotor, 14, motor power.
Detailed Description
The invention is described in detail below with reference to the figures and the embodiments.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on those shown in the drawings, and are used only for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be construed as limiting the present invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
As shown in fig. 1 to 3, the tilt hybrid electrically-driven vertical take-off and landing fixed wing drone of the present invention includes a fuselage 1, a tail, a rotor 6 assembly, a tilt assembly and a power assembly. Wherein, fuselage 1 includes that organism and symmetry divide locates a pair of wing 2 of organism both sides, installs the horn 3 that extends along organism axis direction in the same position of a pair of wing 2, can guarantee like this that unmanned aerial vehicle's focus distributes evenly, and then ensures to fly steadily. The tail includes a pair of vertical tails 4 and the horizontal tail 5 of connecting the 3 tail ends of horn 3 that the tail portion of horn set up downwards, is provided with the rudder on vertical tails 4 and is used for producing unmanned aerial vehicle yawing moment, then is provided with the elevator on the horizontal tail 5 and is used for producing unmanned aerial vehicle pitching moment.
The rotor 6 assembly is used only for vertical take-off and landing and provides auxiliary vertical lift, and comprises a plurality of rotors 6 and power motors 14 for driving the rotors 6, wherein the energy required by the power motors 14 also comes from a power system which is described in more detail later. Specifically in this embodiment, rotor 6 is two, establishes separately and installs back end in horn 3, and power motor 14 is also two correspondingly, installs respectively in rotor 6 below, can realize the perpendicular short distance take-off and landing motion of unmanned aerial vehicle.
In order to alleviate unmanned aerial vehicle's weight, the organism adopts carbon fiber material to make, and the organism is hollow shell structure for install power component. Specifically, as shown in fig. 1 and 4, the power assembly includes an oil tank 9, an engine 10, a generator 11, and a battery 12, an output shaft of the engine 10 drives the generator 11 to operate, and the battery 12 is connected to the generator 11 and the tilt motor 7 by cables, respectively, to constitute a hybrid system. It should be noted that the hybrid power here refers to that the engine 10 drives the generator 11 to provide electric energy for the system and the surplus electric energy is used to charge the battery 12, which is significantly different from the prior art that the fixed wing uses the fuel engine 10 for the front flying power and uses the battery 12 for the vertical stage to supply power. In the invention, the unmanned aerial vehicle mainly provides the power for the vertical flight and the forward flight by the tilting motor 7, the system realizes energy supply by adopting electric energy transmission, and the energy transmission and the supply can be realized only by adopting connection modes such as cables and the like without mechanical structural parts in the electric energy transmission, so that the unmanned aerial vehicle is very convenient.
As for the mounted position of power component in the organism, do not have special requirement in this application, engine 10, generator 11 and battery 12 etc. all can set up on unmanned aerial vehicle according to fuselage 1 overall arrangement and start-up demand, but generally speaking, power component's focus should be located the axis of organism, just so can guarantee unmanned aerial vehicle's smooth flight.
At the vertical take-off and landing stage, the motor 7 that verts is in the perpendicular upward state, provides the pulling force that makes progress, and when fixed wing unmanned aerial vehicle changes the flat in-process that flies, the motor 7 that verts is in the horizontality, for flying before providing horizontal pulling force, this technique is realized through the subassembly that verts. As shown in fig. 3 and 5, the tilting assembly is installed at the front end of the horn 3, and includes the tilting motor 7 and the tilting mechanism 8, the tilting mechanism 8 switches the tilting motor 7 between a horizontal state and a vertical state, and the tilting motor 7 drives the front rotor 13 to move so as to generate a pulling force in a corresponding direction. The tilting mechanism 8 is well-known in the art, and therefore, the present invention will not be described in detail.
As a further improvement of the invention, the unmanned aerial vehicle further comprises an electric control module, wherein an engine 10 and a generator 11 of the power assembly are both connected with the electric control module, the electric control module is used for controlling an accelerator of the engine 10, performing energy distribution control on electric energy of the generator 11, and providing a vertical take-off and landing energy source for the fixed-wing unmanned aerial vehicle together with a battery 12, and the generator 11 directly provides forward energy power in the horizontal flight process. That is to say, during the horizontal flight, the electric control module is used for controlling the electric energy of the generator 11 to supply energy to the tilting motor 7, and during the vertical flight, the electric energy of the battery 12 and the generator 11 is commonly used for energy demand during the vertical flight.
The flight process of the tilting hybrid electric-transmission vertical take-off and landing fixed wing unmanned aerial vehicle is briefly described as follows:
(1) when the vertical take-off and landing are carried out, the tilting motor 7 is in a vertically upward state to provide main vertical lift force; the rotor wing 6 components are started simultaneously to provide auxiliary vertical lift force, and the vertical take-off and landing process is completed;
(2) when the cruise flight is carried out, the tilting mechanism 8 drives the tilting motor 7 to tilt for 90 degrees, and the motor is in a horizontal state to provide horizontal pulling force for forward flight. In the flat process of flying, generator 11 can provide the power energy that advances except that can for fixed wing unmanned aerial vehicle, still can provide the function of charging for battery 12, and battery 12 is not used for doing the power energy this moment, only supplies the airborne equipment power supply to use, guarantees to be in full charge state at landing in-process battery 12 at every turn, ensures flight safety. And once engine 10 breaks down, battery 12 starts immediately, guarantees unmanned aerial vehicle's normal flight, has realized the dual backup of energy system promptly.
In conclusion, the vertical take-off and landing fixed wing unmanned aerial vehicle adopts the technical scheme that the hybrid system is combined with the tilting mechanism 8, so that the unmanned aerial vehicle can fully utilize the characteristic of high energy density of the fuel engine 10, the flight time and the hovering time are greatly prolonged, and the performance is optimized and improved; meanwhile, double backup is provided for an energy system, and the aircraft can normally fly even if the engine 10 fails; moreover, because the tilting motor 7 can share the output of the battery 12 in the vertical lifting process, the battery 12 with smaller capacity can be used, the weight of the battery 12 is reduced by about 50 percent, the weight of the whole machine is reduced, and the energy utilization rate is further improved; in addition, in the fixed-point hovering process, the vertical fixed-wing aircraft is powered by the battery 12 only when hovering, but the energy of the generator 11 is increased, the output of the electric energy of the battery 12 is reduced, and therefore the hovering time can be increased by more than one time compared with that of the conventional vertical take-off and landing fixed-wing aircraft.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
In the description herein, references to the description of the term "one embodiment," "some embodiments," "an example," "a specific example," or "some examples," etc., mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.
The foregoing illustrates and describes the principles, general features, and advantages of the present invention. It should be understood by those skilled in the art that the above embodiments do not limit the present invention in any way, and all technical solutions obtained by using equivalent alternatives or equivalent variations fall within the scope of the present invention.
Claims (9)
1. The utility model provides a vert and mix dynamic electricity transmission VTOL fixed wing unmanned aerial vehicle which characterized in that includes:
the airplane body comprises an airplane body and a pair of wings symmetrically arranged on two sides of the airplane body, and the pair of wings are provided with arms extending along the axial direction of the airplane body at the same positions;
a tail;
the rotor assembly comprises a plurality of rotors and power motors for driving the rotors;
the tilting assembly is arranged at the front end of the arm and comprises a tilting motor and a tilting mechanism, and the tilting mechanism enables the tilting motor to be switched between a horizontal state and a vertical state;
the power assembly is installed in the machine body and comprises an oil tank, an engine, a generator and a battery, the output shaft of the engine drives the generator to work, and the battery is connected with the generator and the tilting motor through cables respectively.
2. The tilt-mix electrokinetic vertical take-off and landing fixed wing drone of claim 1, wherein the number of rotors is two, and the rotors are separately installed in the rear section of the horn, and the power motor is installed below the rotors.
3. The tilt-mix electrokinetic vertical take-off and landing fixed wing drone of claim 1, wherein the tail includes a pair of vertical tails disposed downwardly at the tail of the horn and a horizontal tail connecting the tail of the horn.
4. The tilt-mix electrokinetic-driven VTOL fixed wing drone of claim 1, wherein the body is made of carbon fiber material.
5. The tilt-mix electrokinetic vertical take-off and landing fixed wing drone of claim 1, wherein the center of gravity of the power assembly is located on the central axis of the airframe.
6. The tilting hybrid electric drive vertical take-off and landing fixed wing unmanned aerial vehicle as claimed in claim 1, further comprising an electronic control module, wherein the engine and the generator are both connected to the electronic control module, and the electronic control module is configured to control an engine throttle and perform energy distribution control on electric energy of the generator.
7. The tilt hybrid electrically driven VTOL fixed wing drone of claim 1, wherein the battery is a battery.
8. The tilt-mix electrokinetic vertical take-off and landing fixed wing drone of any of claims 1 to 7, wherein the generator provides a forward power source for the fixed wing drone while providing a battery charging requirement during flat flight.
9. The tilt hybrid electrically driven VTOL fixed wing drone of claim 8, wherein the drone has dual backup of energy system, battery activated to provide power source when engine failure occurs.
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| CN202010405391.0A CN111498106A (en) | 2020-05-14 | 2020-05-14 | Tilting hybrid electric-transmission vertical take-off and landing fixed-wing unmanned aerial vehicle |
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| CN202010405391.0A CN111498106A (en) | 2020-05-14 | 2020-05-14 | Tilting hybrid electric-transmission vertical take-off and landing fixed-wing unmanned aerial vehicle |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113753230A (en) * | 2021-10-11 | 2021-12-07 | 广东汇天航空航天科技有限公司 | Aircraft, wing subassembly and hovercar |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113753230A (en) * | 2021-10-11 | 2021-12-07 | 广东汇天航空航天科技有限公司 | Aircraft, wing subassembly and hovercar |
| CN113753230B (en) * | 2021-10-11 | 2023-08-18 | 广东汇天航空航天科技有限公司 | Aircraft, wing assembly and aerocar |
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