CN105752322A - Electrically-driven undercarriage system and aircraft comprising same - Google Patents
Electrically-driven undercarriage system and aircraft comprising same Download PDFInfo
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- CN105752322A CN105752322A CN201610243547.3A CN201610243547A CN105752322A CN 105752322 A CN105752322 A CN 105752322A CN 201610243547 A CN201610243547 A CN 201610243547A CN 105752322 A CN105752322 A CN 105752322A
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- landing gear
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/34—Alighting gear characterised by elements which contact the ground or similar surface wheeled type, e.g. multi-wheeled bogies
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/50—Steerable undercarriages; Shimmy-damping
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
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Abstract
The invention relates to an electrically-driven undercarriage system and an aircraft comprising the same.The electrically-driven undercarriage system is arranged at the bottom of the aircraft, the aircraft comprises a nose, a fuselage and a tail which are in sequential connection, the undercarriage system comprises a pair of main undercarriage mechanisms symmetrically arranged on two sides of the bottom of the body and a driving control mechanism electrically connected with the main undercarriage mechanisms respectively, each main undercarriage mechanism comprises a main undercarriage arranged at the bottom of the fuselage, a driving motor arranged on the main undercarriage, and a main wheel in transmission connection with the driving motor, and each driving motor is electrically connected with the corresponding driving control mechanism.Compared with the prior art, the electrically-driven undercarriage system has the advantages that the main wheel on each main undercarriage is utilized to drive the aircraft so as to improve takeoff performance of the aircraft; in addition, the undercarriage system has excellent steering capability and high automation level, takeoff noise is lowered, and a takeoff taxing means is provided for other aircrafts.
Description
Technical field
The invention belongs to aircraft landing gear technical field, relate to a kind of electric drive Landing Gear System and the aircraft containing this system.
Background technology
Undercarriage is one of necessary building block of most of Fixed Wing AirVehicle.Not having driving device on undercarriage traditional at present, aircraft remains in sliding race process and is driven by jet engine or propeller.In order to accelerate rapidly in sliding race process, Power System of Flight Vehicle needs bigger power, and this power is much higher than aircraft power needed for cruising condition.Therefore, aircraft is more than in the flight time of 90%, and most of margin of power of its dynamical system does not play a role, and greatly reduces the efficiency of aircraft.Meanwhile, jet engine or propeller can send huge noise under high thrust operating mode so that aircraft produces serious noise pollution in the starting heats stage, reduces the comfortableness of comfort level and the airport surrounding enviroment flying Passenger On Board.Additionally, run in accelerator sliding, this propulsion mode is due to slip-stream kinetic energy rejection, and its propulsive efficiency is also relatively low.
In recent years, flapping wing aircraft quickly grows.This aircraft can utilize fluttering of wing to produce required thrust in cruising condition, promotes aircraft flight.But, under ground static or lower-speed state, the thrust that flapping wing can be generated by is very limited.Hands can be adopted to throw mode for microminiature flapping wing aircraft to take off, but for the weight flapping wing aircraft more than 10kg, this mode is just unrealistic.Therefore, it is necessary to design new drive system of taking off to solve the problem of taking off of flapping wing aircraft.
The Chinese utility model patent that Authorization Notice No. is CN204750559U discloses a kind of undercarriage with wheel driving device, including wheel shaft, the wheel being fixed on wheel shaft two ends and the support bar being connected with wheel shaft, also include the driving device that live axle rotates；Described driving device is the dual-axle motor that rotor stretches out to two ends, and the rotor of described dual-axle motor is wheel shaft, and described support bar is fixing with the housing of dual-axle motor to be connected.In the technical scheme of above-mentioned patent disclosure, driving device can drive the wheel of undercarriage to rotate, and produces power, but this undercarriage is comparatively inconvenient when aircraft turns to, and automaticity is relatively low, needs further improvement.
Summary of the invention
Defect that the purpose of the present invention is contemplated to overcome above-mentioned prior art to exist and provide a kind of main wheel that can utilize on main landing gear to drive aircraft, thus improve aircraft takeoff data and have excellence steering capability, electric drive Landing Gear System that automaticity is high.
Another object of the present invention is just to provide a kind of aircraft containing electric drive Landing Gear System.
The purpose of the present invention can be achieved through the following technical solutions:
A kind of electric drive Landing Gear System, this Landing Gear System is arranged at the bottom of aircraft, described aircraft includes the head, fuselage and the tail that are sequentially connected with, main landing gear mechanism that described Landing Gear System includes a pair being symmetricly set in fuselage bottom both sides and the driving controlling organization that the frame mechanism that falls with two main starting respectively electrically connects, described main landing gear mechanism includes the main wheel being arranged at the main landing gear of fuselage bottom, the drive motor being arranged on main landing gear and being in transmission connection with drive motor, and described drive motor electrically connects with driving controlling organization.
Described Landing Gear System also includes the nose landing gear mechanism being arranged at bottom head and the tail landing gear mechanism being arranged at bottom tail.
The described controlling organization that drives includes a pair electric machine controller, automatic control unit and the power supply being connected in series, and each electric machine controller is electrically connected with the drive motor of corresponding side by circuit.
Described automatic control unit includes tachogenerator, compass and the PID controller electrically connected respectively with tachogenerator, compass and electric machine controller.
Described tachogenerator includes the one in velocity sensor or acceleration transducer.
Preferably, described tachogenerator is acceleration transducer.
Described compass includes the one in magnetic compass, gyrocompass, telecompass or astro-compass.
Preferably, described compass is magnetic compass.
Described nose landing gear mechanism includes the nose landing gear that can turn to, the head pulley being arranged on nose landing gear and the nose landing gear that is in transmission connection with nose landing gear turns to servo unit；
Described tail landing gear mechanism includes the tail undercarriage that can turn to, the tail wheel being arranged on tail undercarriage and the tail undercarriage that is in transmission connection with tail undercarriage turns to servo unit.
Described nose landing gear turns to servo unit to include nose landing gear directional drive and the nose landing gear rocker-arm link being in transmission connection respectively with nose landing gear directional drive and nose landing gear, and described nose landing gear directional drive includes the one in electrical servo steering wheel or hydraulic actuator；
Described tail undercarriage turns to servo unit to include tail undercarriage directional drive and the tail undercarriage rocker-arm link being in transmission connection respectively with tail undercarriage directional drive and tail undercarriage, and described tail undercarriage directional drive includes the one in electrical servo steering wheel or hydraulic actuator.
Described drive motor is brushless electric machine.
A kind of aircraft containing electric drive Landing Gear System.
When actual design, nose landing gear directional drive and the tail undercarriage directional drive of small-sized unmanned aircraft can be selected for electrical servo steering wheel, and nose landing gear directional drive and the tail undercarriage directional drive of large-scale manned vehicle can be selected for hydraulic actuator.
The rudder of aircraft can control nose landing gear directional drive and tail undercarriage directional drive respectively through circuit, produce to move back and forth or rotary motion, afterwards, reciprocating motion or the convert rotational motion of nose landing gear directional drive are the rotation of nose landing gear by nose landing gear rocker-arm link, tail undercarriage rocker-arm link is by the reciprocating motion of tail undercarriage directional drive or rotation that convert rotational motion is tail undercarriage, and then realizes nose landing gear and the rotation of tail undercarriage.
When practical application, drive motor is fixedly installed on main landing gear, and main wheel can be directly mounted in the rotating shaft of drive motor, to reduce structure complexity.Two drive motors are by the unified power supply of power supply.Automatic control unit can dynamically adjust the power of two drive motors according to pilot command or aircraft duty by two electric machine controllers, and then control the power output of both sides main wheel, by the Acceleration Control of aircraft in rational scope, the startup stage of avoiding, acceleration is excessive, simultaneously differential by both sides main wheel, assisting in flying device turns to.Nose landing gear and tail undercarriage can turn to servo unit and tail undercarriage to turn to servo unit to realize turning to respectively through nose landing gear.Meanwhile, nose landing gear mechanism, tail landing gear mechanism constitute four-point undercarriage layout together with Liang Ge main landing gear mechanism.
The operation principle of the present invention is: the direct driving host wheel of drive motor, provides driving force for sliding race of aircraft, utilizes the huge advantage of drive motor low speed torque, it is possible to achieve quickly accelerate, shortens the sliding distance run of aircraft.Meanwhile, automatic control unit passes through tachogenerator and compass, the real-time acceleration measuring aircraft horizontal direction and course, and is regulated the power output of drive motor by PID controller, it is achieved steady, linear accelerating.By main wheel differential control, it is possible to effectively reduce aircraft radius of turn and improve the Heading control ability in accelerator.
Compared with prior art, the invention have the characteristics that:
1) efficiency is high, accelerate fast: the efficiency of the direct driving host wheel of drive motor is higher than the drive efficiency of jet engine or propeller, and the moment of torsion under lower-speed state is big, it is possible to increase the sliding acceleration run of aircraft takeoff, shorten the distance of starting heats, and then improve efficiency of taking off；
2) steering capability is strong: two drive motors are respectively by two motor controller controls so that main wheel can be realized differential control by automatic control unit, and then the sliding of raising aircraft runs cornering ability, even realizes pivot stud；
3) automaticity is high: automatic control unit can pass through tachogenerator, compass and PID controller, measures acceleration and the course of aircraft in real time, and regulates the power output of drive motor in time so that it is reaches OK range, simplify operation；
4) special device for producing thrust under flapping wing or other low-speed situations provides a kind of starting heats means；
5) noise is low: adopt drive motor and main wheel drive form, and drive motor is brushless electric machine, and noise situation is substantially better than electromotor and drives with propeller, reduces the noise that takes off.
Accompanying drawing explanation
Fig. 1 is the overall structure schematic diagram of aircraft of the present invention；
Fig. 2 is the structural representation of electric drive Landing Gear System of the present invention；
Description of symbols in figure:
1 drive motor, 2 main wheels, 3 main landing gears, 4 electric machine controllers, 5 automatic control units, 6 power supplies, 7 nose landing gear, 8 nose landing gear turn to servo unit, 9 tail undercarriages, 10 tail undercarriages to turn to servo unit, 11 heads, 12 fuselages, 13 tails, 14 head pulleys, 15 tail wheels.
Detailed description of the invention
Below in conjunction with the drawings and specific embodiments, the present invention is described in detail.The present embodiment is carried out premised on technical solution of the present invention, gives detailed embodiment and concrete operating process, but protection scope of the present invention is not limited to following embodiment.
Embodiment 1:
A kind of aircraft containing electric drive Landing Gear System is as shown in Figure 1.Electric drive Landing Gear System is arranged at the bottom of aircraft, aircraft includes the head 11, fuselage 12 and the tail 13 that are sequentially connected with, main landing gear mechanism that Landing Gear System includes a pair being symmetricly set in fuselage 12 two bottom sides and the driving controlling organization that the frame mechanism that falls with two main starting respectively electrically connects, main landing gear mechanism includes the main wheel 2 being arranged at the main landing gear 3 bottom fuselage 12, the drive motor 1 being arranged on main landing gear 3 and being in transmission connection with drive motor 1.Drive motor 1 is brushless electric machine, and electrically connects with driving controlling organization.Landing Gear System also includes the nose landing gear mechanism being arranged at bottom head 11 and the tail landing gear mechanism being arranged at bottom tail 13.The structure of electric drive Landing Gear System is as shown in Figure 2.
Wherein, driving controlling organization to include a pair electric machine controller 4, automatic control unit 5 and the power supply 6 being connected in series, each electric machine controller 4 is electrically connected with the drive motor 1 of corresponding side by circuit.Automatic control unit 5 includes acceleration transducer, magnetic compass and the PID controller electrically connected respectively with acceleration transducer, magnetic compass and electric machine controller 4.Nose landing gear mechanism includes the nose landing gear 7 that can turn to, the head pulley 14 being arranged on nose landing gear 7 and the nose landing gear that is in transmission connection with nose landing gear 7 turns to servo unit 8；Tail undercarriage mechanism includes the tail undercarriage 9 that can turn to, the tail wheel 15 being arranged on tail undercarriage 9 and the tail undercarriage that is in transmission connection with tail undercarriage 9 turns to servo unit 10.
Nose landing gear turns to servo unit 8 to include nose landing gear directional drive and the nose landing gear rocker-arm link being in transmission connection respectively with nose landing gear directional drive and nose landing gear 7, and nose landing gear directional drive is electrical servo steering wheel；
Tail undercarriage turns to servo unit 10 to include tail undercarriage directional drive and the tail undercarriage rocker-arm link being in transmission connection respectively with tail undercarriage directional drive and tail undercarriage 9, and tail undercarriage directional drive is electrical servo steering wheel.
The rudder of aircraft can control nose landing gear directional drive respectively through circuit and tail undercarriage directional drive produces rotary motion, afterwards, nose landing gear rocker-arm link is by the rotation that convert rotational motion is nose landing gear 7 of nose landing gear directional drive, tail undercarriage rocker-arm link is by the rotation that convert rotational motion is tail undercarriage 9 of tail undercarriage directional drive, and then realizes nose landing gear 7 and the rotation of tail undercarriage 9.
Drive motor 1 is fixedly installed on main landing gear 3, and main wheel 2 is directly installed in the rotating shaft of drive motor 1, to reduce structure complexity.Two drive motors 1 are by the unified power supply of power supply 6.Automatic control unit 5 can dynamically adjust the power of two drive motors 1 according to pilot command or aircraft duty by two electric machine controllers 4, and then control the power output of both sides main wheel 2, by the Acceleration Control of aircraft in rational scope, the startup stage of avoiding, acceleration is excessive, simultaneously differential by both sides main wheel 2, assisting in flying device turns to.Nose landing gear 7 and tail undercarriage 9 can turn to servo unit 8 and tail undercarriage to turn to servo unit 10 to realize turning to respectively through nose landing gear.Meanwhile, nose landing gear mechanism, tail landing gear mechanism constitute four-point undercarriage layout together with Liang Ge main landing gear mechanism.Wherein, nose landing gear mechanism plays a major role, and tail landing gear mechanism only uses in sliding initial start stage of running.
When starting heats start, automatic control unit 5 is sent instruction by pilot or other control system, and aircraft acceleration, by dynamically regulating the power output of drive motor 1, is controlled at proper level by automatic control unit 5.Running acceleration relatively greatly due to sliding, and propulsive force is originated and main wheel 2, its position, lower than aircraft center of gravity, can produce a bigger nose-up pitching moment, cause aircraft to come back.Tail wheel 15 is prevented from aircraft afterbody and contacts to earth damage, provides certain course changing control ability simultaneously.Along with speed increases, the aerodynamic force that aircraft produces is gradually increased, and after reaching certain speed, aircraft recovers the sliding race state of routine, and head pulley 14 lands, and now the Heading control of aircraft is controlled with rudder by head pulley 14.Aircraft further speeds up in this state, until reaching takeoff speed, leaves ground.Now electric machine controller 4 will cut off the power supply of drive motor 1.Afterwards, aircraft flies in a usual manner.
Additionally, when ground taxi or starting heats, automatic control unit 5 also can receive directional control signal.Both sides main wheel 2 is carried out Differential Control according to the deviation of bogey heading Yu the current course of aircraft by automatic control unit 5, for instance, as needed aircraft to turn right, then increase the driving power of left side main wheel 2, reduce the driving power of right side main wheel 2.Thus improve aircraft course changing control ability.
Embodiment 2:
A kind of aircraft containing electric drive Landing Gear System is as shown in Figure 1.Electric drive Landing Gear System is arranged at the bottom of aircraft, aircraft includes the head 11, fuselage 12 and the tail 13 that are sequentially connected with, main landing gear mechanism that Landing Gear System includes a pair being symmetricly set in fuselage 12 two bottom sides and the driving controlling organization that the frame mechanism that falls with two main starting respectively electrically connects, main landing gear mechanism includes the main wheel 2 being arranged at the main landing gear 3 bottom fuselage 12, the drive motor 1 being arranged on main landing gear 3 and being in transmission connection with drive motor 1.Drive motor 1 is brushless electric machine, and electrically connects with driving controlling organization.Landing Gear System also includes the nose landing gear mechanism being arranged at bottom head 11 and the tail landing gear mechanism being arranged at bottom tail 13.The structure of electric drive Landing Gear System is as shown in Figure 2.
Wherein, driving controlling organization to include a pair electric machine controller 4, automatic control unit 5 and the power supply 6 being connected in series, each electric machine controller 4 is electrically connected with the drive motor 1 of corresponding side by circuit.Automatic control unit 5 includes tachogenerator, compass and the PID controller electrically connected respectively with tachogenerator, compass and electric machine controller 4.Wherein, tachogenerator is velocity sensor, and compass is gyrocompass.
Nose landing gear mechanism includes the nose landing gear 7 that can turn to, the head pulley 14 being arranged on nose landing gear 7 and the nose landing gear that is in transmission connection with nose landing gear 7 turns to servo unit 8；Tail undercarriage mechanism includes the tail undercarriage 9 that can turn to, the tail wheel 15 being arranged on tail undercarriage 9 and the tail undercarriage that is in transmission connection with tail undercarriage 9 turns to servo unit 10.
Nose landing gear turns to servo unit 8 to include nose landing gear directional drive and the nose landing gear rocker-arm link being in transmission connection respectively with nose landing gear directional drive and nose landing gear 7, and nose landing gear directional drive is hydraulic actuator；
Tail undercarriage turns to servo unit 10 to include tail undercarriage directional drive and the tail undercarriage rocker-arm link being in transmission connection respectively with tail undercarriage directional drive and tail undercarriage 9, and tail undercarriage directional drive is hydraulic actuator.
The rudder of aircraft can control nose landing gear directional drive respectively through circuit and tail undercarriage directional drive produces to move back and forth, afterwards, nose landing gear rocker-arm link is by the rotation that convert reciprocating motion is nose landing gear 7 of nose landing gear directional drive, tail undercarriage rocker-arm link is by the rotation that convert reciprocating motion is tail undercarriage 9 of tail undercarriage directional drive, and then realizes nose landing gear 7 and the rotation of tail undercarriage 9.
Drive motor 1 is fixedly installed on main landing gear 3, and main wheel 2 is directly installed in the rotating shaft of drive motor 1, to reduce structure complexity.Two drive motors 1 are by the unified power supply of power supply 6.Automatic control unit 5 can dynamically adjust the power of two drive motors 1 according to pilot command or aircraft duty by two electric machine controllers 4, and then control the power output of both sides main wheel 2, by the Acceleration Control of aircraft in rational scope, the startup stage of avoiding, acceleration is excessive, simultaneously differential by both sides main wheel 2, assisting in flying device turns to.Nose landing gear 7 and tail undercarriage 9 can turn to servo unit 8 and tail undercarriage to turn to servo unit 10 to realize turning to respectively through nose landing gear.Meanwhile, nose landing gear mechanism, tail landing gear mechanism constitute four-point undercarriage layout together with Liang Ge main landing gear mechanism.
Operation principle is: the direct driving host wheel 2 of drive motor 1, provides driving force for sliding race of aircraft, utilizes the huge advantage of drive motor 1 low speed torque, it is possible to achieve quickly accelerate, shortens the sliding distance run of aircraft.Meanwhile, automatic control unit 5 is by tachogenerator and compass, the real-time acceleration measuring aircraft horizontal direction and course, and is regulated the power output of drive motor 1 by PID controller, it is achieved steady, linear accelerating.By main wheel 2 differential control, it is possible to effectively reduce aircraft radius of turn and improve the Heading control ability in accelerator.
Embodiment 3:
In the present embodiment, compass is telecompass, and all the other are with embodiment 2.
Embodiment 4:
In the present embodiment, compass is astro-compass, and all the other are with embodiment 2.
Claims (10)
1. an electric drive Landing Gear System, this Landing Gear System is arranged at the bottom of aircraft, described aircraft includes the head (11) being sequentially connected with, fuselage (12) and tail (13), it is characterized in that, main landing gear mechanism that described Landing Gear System includes a pair being symmetricly set in fuselage (12) two bottom sides and the driving controlling organization that the frame mechanism that falls with two main starting respectively electrically connects, described main landing gear mechanism includes the main landing gear (3) being arranged at fuselage (12) bottom, it is arranged at the drive motor (1) on main landing gear (3) and the main wheel (2) being in transmission connection with drive motor (1), described drive motor (1) electrically connects with driving controlling organization.
2. a kind of electric drive Landing Gear System according to claim 1, it is characterized in that, described Landing Gear System also includes being arranged at the nose landing gear mechanism of head (11) bottom and being arranged at the tail landing gear mechanism of tail (13) bottom.
3. a kind of electric drive Landing Gear System according to claim 2, it is characterized in that, the described controlling organization that drives includes a pair electric machine controller (4), automatic control unit (5) and the power supply (6) being connected in series, and each electric machine controller (4) is electrically connected with the drive motor (1) of corresponding side by circuit.
4. a kind of electric drive Landing Gear System according to claim 3, it is characterized in that, described automatic control unit (5) includes tachogenerator, compass and the PID controller electrically connected respectively with tachogenerator, compass and electric machine controller (4).
5. a kind of electric drive Landing Gear System according to claim 4, it is characterised in that described tachogenerator includes the one in velocity sensor or acceleration transducer.
6. a kind of electric drive Landing Gear System according to claim 4, it is characterised in that described compass includes the one in magnetic compass, gyrocompass, telecompass or astro-compass.
7. a kind of electric drive Landing Gear System according to claim 2, it is characterised in that
Described nose landing gear mechanism includes the nose landing gear (7) that can turn to, the head pulley (14) being arranged on nose landing gear (7) and the nose landing gear that is in transmission connection with nose landing gear (7) turns to servo unit (8)；
Described tail landing gear mechanism includes the tail undercarriage (9) that can turn to, the tail wheel (15) being arranged on tail undercarriage (9) and the tail undercarriage that is in transmission connection with tail undercarriage (9) turns to servo unit (10).
8. a kind of electric drive Landing Gear System according to claim 7, it is characterised in that
Described nose landing gear turns to servo unit (8) to include nose landing gear directional drive and the nose landing gear rocker-arm link being in transmission connection respectively with nose landing gear directional drive and nose landing gear (7), and described nose landing gear directional drive includes the one in electrical servo steering wheel or hydraulic actuator；
Described tail undercarriage turns to servo unit (10) to include tail undercarriage directional drive and the tail undercarriage rocker-arm link being in transmission connection respectively with tail undercarriage directional drive and tail undercarriage (9), and described tail undercarriage directional drive includes the one in electrical servo steering wheel or hydraulic actuator.
9. a kind of electric drive Landing Gear System according to claim 1, it is characterised in that described drive motor (1) is brushless electric machine.
10. the aircraft containing the electric drive Landing Gear System described in any one of claim 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610243547.3A CN105752322A (en) | 2016-04-19 | 2016-04-19 | Electrically-driven undercarriage system and aircraft comprising same |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610243547.3A CN105752322A (en) | 2016-04-19 | 2016-04-19 | Electrically-driven undercarriage system and aircraft comprising same |
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| CN105752322A true CN105752322A (en) | 2016-07-13 |
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| CN201610243547.3A Pending CN105752322A (en) | 2016-04-19 | 2016-04-19 | Electrically-driven undercarriage system and aircraft comprising same |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107651186A (en) * | 2017-08-29 | 2018-02-02 | 深圳市华力航空科技有限公司 | A kind of electric power aerodone |
| CN109515693A (en) * | 2018-11-26 | 2019-03-26 | 张连营 | Aircraft electric pushing-aid wheel and undercarriage |
| CN113998096A (en) * | 2021-12-06 | 2022-02-01 | 西安航空制动科技有限公司 | Comprehensive control method and system for airplane electric drive system |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5984229A (en) * | 1997-06-02 | 1999-11-16 | Boeing North American, Inc. | Extremely short takeoff and landing of aircraft using multi-axis thrust vectoring |
| CN201030944Y (en) * | 2007-01-26 | 2008-03-05 | 北京昭阳科技文化有限公司 | Light seed-prohibiting drug-spading unmanned observation plane |
| CN101238031A (en) * | 2005-06-13 | 2008-08-06 | 波音公司 | Powered nose aircraft wheel system |
| CN101941524A (en) * | 2009-04-24 | 2011-01-12 | 梅西耶-布加蒂公司 | The method of aircraft taxi |
| CN101998921A (en) * | 2008-04-11 | 2011-03-30 | 空中客车操作有限公司 | An aircraft landing gear arrangement and a nose landing gear assembly |
| CN102267563A (en) * | 2010-05-07 | 2011-12-07 | 梅西耶-布加蒂公司 | Method for controlling a yaw axis movement of a taxiing aircraft |
| CN103158856A (en) * | 2013-04-12 | 2013-06-19 | 北京航空航天大学 | Light airscrew flying wing aircraft capable of taking off and landing in short distance |
| CN203094436U (en) * | 2012-12-25 | 2013-07-31 | 天津三爻航空航天科技发展有限公司 | Tail-wheel steering apparatus of fixed wing aircraft |
| CN203528811U (en) * | 2013-08-14 | 2014-04-09 | 天津三爻航空航天科技发展有限公司 | Module structure for fixing tail wheel and machine body |
-
2016
- 2016-04-19 CN CN201610243547.3A patent/CN105752322A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5984229A (en) * | 1997-06-02 | 1999-11-16 | Boeing North American, Inc. | Extremely short takeoff and landing of aircraft using multi-axis thrust vectoring |
| CN101238031A (en) * | 2005-06-13 | 2008-08-06 | 波音公司 | Powered nose aircraft wheel system |
| CN201030944Y (en) * | 2007-01-26 | 2008-03-05 | 北京昭阳科技文化有限公司 | Light seed-prohibiting drug-spading unmanned observation plane |
| CN101998921A (en) * | 2008-04-11 | 2011-03-30 | 空中客车操作有限公司 | An aircraft landing gear arrangement and a nose landing gear assembly |
| CN101941524A (en) * | 2009-04-24 | 2011-01-12 | 梅西耶-布加蒂公司 | The method of aircraft taxi |
| CN102267563A (en) * | 2010-05-07 | 2011-12-07 | 梅西耶-布加蒂公司 | Method for controlling a yaw axis movement of a taxiing aircraft |
| CN203094436U (en) * | 2012-12-25 | 2013-07-31 | 天津三爻航空航天科技发展有限公司 | Tail-wheel steering apparatus of fixed wing aircraft |
| CN103158856A (en) * | 2013-04-12 | 2013-06-19 | 北京航空航天大学 | Light airscrew flying wing aircraft capable of taking off and landing in short distance |
| CN203528811U (en) * | 2013-08-14 | 2014-04-09 | 天津三爻航空航天科技发展有限公司 | Module structure for fixing tail wheel and machine body |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107651186A (en) * | 2017-08-29 | 2018-02-02 | 深圳市华力航空科技有限公司 | A kind of electric power aerodone |
| CN109515693A (en) * | 2018-11-26 | 2019-03-26 | 张连营 | Aircraft electric pushing-aid wheel and undercarriage |
| WO2020108341A1 (en) * | 2018-11-26 | 2020-06-04 | Lianying Zhang | Aircraft power booster wheel and landing gear |
| CN113998096A (en) * | 2021-12-06 | 2022-02-01 | 西安航空制动科技有限公司 | Comprehensive control method and system for airplane electric drive system |
| CN113998096B (en) * | 2021-12-06 | 2023-02-10 | 西安航空制动科技有限公司 | Comprehensive control method and system for airplane electric drive system |
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Application publication date: 20160713 |
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