General aircraft electric driving system and control method

Abstract

The invention discloses a general aircraft electric drive system and a control method, the electric drive system comprises electric drive aircraft wheels and a flight motor, and under the control of a control module, the electric drive aircraft wheels can drive an aircraft to move on the ground at a low speed and can assist propellers driven by the flight motor to take off. When the aircraft lands, the propellers and the aircraft landing gear rollers can charge the energy storage device through the corresponding motors respectively. The control method comprises the following steps: realizing low-speed movement on the ground by utilizing the electrically-driven airplane wheels; the electrically-driven airplane wheels assist the propellers to realize takeoff of the airplane; the flying motor drives the propellers to rotate to drive the aircraft to fly; in the landing process of the aircraft, the propellers are charged through the flight motors; after landing, the tires charge the energy storage device through the airplane wheel motors. The ground scheduling is linked with the take-off stage, the take-off efficiency is improved, and the effective flight time is prolonged; energy recovery is achieved in the airplane deceleration landing process.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aviation, in particular to a general aircraft. BACKGROUND

[0002] The existing general aircraft lacks the ability to move freely on the ground, such as moving between the hangar and the runway, which usually requires more than 3 ground crew to directly push or use a tow bar to tow, which brings great inconvenience to the daily operation of general aviation airports and private users, and there is a potential risk of accidental damage to the aircraft and injury to the ground crew.

[0003] In addition, the general aircraft can also use the pulling force generated by the low-speed rotation of the propeller to move before entering the runway after being pushed out of the hangar, but this method is inefficient and shortens the effective flight time. When the aircraft is stationary on the ground and the engine is working, or when it is slowly moving at the beginning of takeoff, the propeller efficiency is very low because the propeller cannot advance at full speed to achieve its maximum efficiency. At this time, each propeller blade rotates in the air at a certain angle of attack, producing less thrust relative to the power required to rotate it.

[0004] The green electric taxiing system that replaces the engine with an electric motor to tow the aircraft has become a development trend. The green electric taxiing system refers to moving on the aircraft taxiway without using the propeller, and using the auxiliary power system to drive the traction motor installed in the landing gear wheel to complete the action of the aircraft taxiing phase.

[0005] The patent document with publication number CN 107600395 A discloses a power wheel electric drive device for a civil aircraft landing gear, which is powered by an auxiliary power system to drive the motor of the power wheel of the aircraft landing gear, so that the aircraft can be pushed out autonomously without using the main engine or the wheel holder. The city ground scheduling by the propeller has many safety hazards, high noise, serious pollution and low efficiency. The green taxiing of the civil aircraft by the power wheel electric drive system is a more reasonable ground scheduling method. SUMMARY

[0006] The technical problem solved by the present application is that the green taxiing of the civil aircraft by the power wheel electric drive system is limited to a reasonable ground scheduling method, but does not effectively connect with the takeoff of the aircraft.

[0007] To solve the above technical problems, the present application provides the following technical solution: a general aircraft electric drive system, comprising an electric drive wheel, a control module, a flight control input, a flight electric motor controller, a wheel electric motor controller and a flight electric motor.

[0008] The electric drive wheel is installed on the head of the airplane, and a wheel motor is arranged in the electric drive wheel; a control module and a flight control input are installed in the airplane, and a flight motor is provided with a propeller;

[0009] The flight control input is electrically connected with the control module, the flight motor is electrically connected with the flight control input through a flight motor controller, and the wheel motor is electrically connected with the control module through a wheel motor controller.

[0010] During the low-speed moving stage of the airplane on the ground, the control module controls the wheel motor controller to supply power to the wheel motor, and the wheel motor drives the airplane to move forward or backward, and the moving speed is less than or equal to V1.

[0011] The control module controls the flight motor controller to supply power to the flight motor, the flight motor drives the propeller to rotate, and then drives the airplane to accelerate, and the speed of the accelerated airplane is V2, when V2>V1, the control module 300 controls the wheel motor controller to cut off the power supply of the wheel motor.

[0012] According to the above technical scheme, the electric drive wheel can not only move the airplane at low speed to realize the ground scheduling, but also assist the airplane to take off, and the maximum speed can reach V1. At the same time, the flight motor drives the propeller to accelerate the airplane, when the speed V2 of the airplane is greater than V1, the power supply of the wheel motor is cut off to prevent the wheel motor from being dragged in reverse and damaged when the speed exceeds the designed speed. Therefore, the electric drive wheel of the present application not only has a reasonable ground scheduling mode, but also effectively connects with the take-off of the airplane, so that the take-off efficiency is improved and the effective flight time is prolonged.

[0013] The general airplane electric drive system of the present application further comprises an energy storage device, the energy storage device is installed in the airplane, and the energy storage device is electrically connected with the control module. During the deceleration and landing process of the airplane, the propeller drives the flight motor to rotate, and the flight motor acts as a generator to charge the energy storage device through the flight motor controller. After the airplane lands, the speed of the airplane is V3, when V3>V1, the electric drive wheel drives the wheel motor to rotate through the tire in contact with the ground, at this time, the wheel motor acts as a generator to charge the energy storage device through the wheel motor controller. When V3 decreases to V1, the control module controls the wheel motor controller to supply power to the wheel motor, and the wheel motor drives the airplane to move forward or backward. During the deceleration and landing process and the landing sliding process, the flight motor and the wheel motor charge the energy storage device in reverse, so that the energy is recovered. When the speed V3 of the airplane decreases to V1, the airplane enters the ground scheduling state, and the airplane is driven to move forward or backward by the wheel motor. Therefore, the effective connection between the landing of the airplane and the ground scheduling is realized.

[0014] The general aircraft electric drive system of the application further comprises a taxiing control input and a wheel clutch controller, the taxiing control input and the wheel clutch controller are electrically connected with the control module, and the electric drive wheel is internally provided with a wheel clutch. During the low-speed moving stage of the aircraft on the ground, the pilot inputs the forward / reverse instruction to the control module through the taxiing control input, the control module controls the wheel clutch controller to supply power to the wheel clutch, the wheel clutch links the electric motor with the hub of the electric drive wheel, and the control module controls the electric motor controller to supply power to the electric motor. During the take-off stage, when the aircraft speed V2>V1, the control module controls the electric motor controller to cut off the power supply to the electric motor, and controls the wheel clutch controller to cut off the power supply to the wheel clutch. After landing, when the aircraft speed V3>V1, the control module controls the wheel clutch controller to supply power to the wheel clutch, the wheel clutch links the electric motor with the hub of the electric drive wheel, the hub drives the electric motor to rotate, and the electric motor functions as a generator to charge the energy storage device through the electric motor controller.

[0015] The electric drive wheel comprises a landing gear wheel fork, a hub, a tire, a speed reducer and an axle. The landing gear wheel fork is provided with oppositely arranged left and right fork arms, and coaxial left and right shaft holes are formed in the left and right fork arms respectively. The hub is an integral structure, comprising an annular rim, a tubular hollow shaft sleeve and a wheel disc connecting the two at one end, the rim, the wheel disc and the hollow shaft sleeve surround to form a first installation space with an opening, and the hollow shaft sleeve has a second installation space penetrating through both ends. The tire is sleeved on the outside of the hub. The speed reducer, the wheel clutch and the electric motor are sequentially arranged in the first installation space, the output end of the speed reducer is fixedly connected with the wheel disc, the electric motor is fixed on the right fork arm, and the electric motor is connected / disconnected with the torque input end of the speed reducer through the wheel clutch. The axle supports the hub on the landing gear wheel fork by penetrating through the left shaft hole, the second installation space and the right shaft hole.

[0016] The speed reducer is a planetary reducer, comprising a gear ring, a planetary wheel assembly and a sun gear, the gear ring is the output end and the sun gear is the input end. The wheel clutch is an electromagnetic clutch, comprising a clutch body, a driving disc and a driven disc, the driving disc and the driven disc can rotate relative to the axis of the clutch body, and the clutch body attracts the driven disc to the driving disc by generating electromagnetic force to make the two rotate synchronously. The electric motor comprises a motor shell, a stator assembly, a rotor assembly and a motor shaft. The motor shell is fixed on the right fork arm, the motor shaft is in transmission connection with the driving disc of the wheel clutch, and the driven disc of the wheel clutch is in transmission connection with the sun gear of the speed reducer; when the clutch body is electrified, the electromagnetic force attracts the driven disc to the driving disc, the motor shaft drives the driving disc, the driven disc and the sun gear to rotate in sequence, and the hub is driven to rotate after the torque is increased by the planetary wheel assembly and the gear ring.

[0017] The motor housing has a front end surface and a rear end surface, the rear end surface is fixedly connected with the right fork arm, and the front end surface is fixedly connected with the clutch body.

[0018] The motor shaft is provided with a groove on the outer side, the driving disc of the wheel clutch has a disc-shaped transmission end and a tubular transmission rod, the transmission rod is provided with a flange matched with the groove of the motor shaft, and the motor shaft and the driving disc transmit torque through the groove and the flange.

[0019] The reducer comprises an end cover and an elastic member, the elastic member is arranged between the sun gear and the end cover, so that the sun gear has a tendency to move away from the end cover. The driven disc of the wheel clutch is fixed on the sun gear, the driven disc and the driving disc are oppositely arranged and have a certain gap, when the clutch body is powered, the electromagnetic force drives the driven disc to move towards the driving disc to connect the two, and after power-off, the elastic member pushes the driven disc away from the driving disc to disconnect the two. Specifically, the driven disc is fixedly connected with the sun gear through a connecting piece, the sun gear is pivotally connected with a planet carrier, a planet gear is installed on the planet carrier, the planet gear is engaged with the ring gear and can slide along the axial direction of the ring gear. The elastic member is arranged between the planet carrier and the end cover, and the end cover is fixedly connected with the ring gear. Therefore, under the action of the elastic member, the planet carrier has a tendency to move away from the end cover, the planet carrier drives the sun gear to have a tendency to move away from the end cover, and the sun gear drives the driven disc to have a tendency to move away from the driving disc. Under the action of the electromagnetic force, the driven disc moves towards the driving disc, the driven disc drives the sun gear to axially displace, the sun gear drives the planet carrier to axially displace, the planet carrier drives the planet gear to axially displace, and the planet gear slides axially relative to the ring gear, but does not affect the transmission of torque between the planet gear and the ring gear.

[0020] At least two supporting bearings are arranged in the second mounting space of the hollow shaft sleeve, the supporting bearings are sleeved on the outer side of the wheel shaft, so that the hub can freely rotate around the axis of the wheel shaft. The wheel shaft comprises a long shaft and a short shaft sleeve, and the long shaft has a heat dissipation channel penetrating through both ends.

[0021] A control method of a general aircraft electric drive system, the control method comprising the following steps performed in sequence:

[0022] 1) Ground low-speed moving stage, the pilot inputs forward / reverse command to the control module through the taxi control input, the control module controls the wheel clutch controller to supply power to the wheel clutch, the wheel clutch connects the wheel motor with the reducer in transmission, the control module controls the wheel motor controller to supply power to the wheel motor, the motor drives the tire to rotate through the wheel clutch, the reducer and the hub, and then drives the aircraft to move forward / reverse, and the moving speed is ≤V1.

[0023] 2) During takeoff, the pilot inputs flight commands to the control module through the flight control input. The control module controls the flight motor controller to supply power to the flight motor. The motor drives the propeller to rotate, which in turn drives the aircraft to accelerate. The speed of the aircraft after acceleration is V2. When V2 > V1, the control module controls the wheel motor controller to cut off the power to the wheel motor and controls the wheel clutch controller to cut off the power to the wheel clutch.

[0024] 3) During the flight phase, the pilot inputs flight commands to the control module through the flight control input. The control module controls the flight motor controller to supply power to the flight motors, which drive the propellers to rotate, thereby propelling the aircraft into flight.

[0025] 4) During the deceleration and landing phase, the propeller drives the flight electric motor to rotate, and the flight electric motor acts as a generator to charge the energy storage device through the flight electric motor controller.

[0026] 5) During the landing taxiing phase, after landing, the aircraft speed is V3. When V3 > V1, the control module controls the wheel clutch controller to supply power to the wheel clutch. The wheel clutch connects the wheel motor to the reducer. The tire drives the wheel motor to rotate through the wheel hub, reducer and wheel clutch. At this time, the wheel motor acts as a generator and charges the energy storage device through the wheel motor controller.

[0027] The present invention has the following technical effects:

[0028] First, the electric-driven front wheel system enables general aviation aircraft to move autonomously on the ground without the need for ground crew assistance. Pilots can control the aircraft to enter and exit the hangar from the cockpit or remotely from the ground, which greatly improves the work efficiency of general aviation airports and solves the problem of insufficient manpower for private aircraft users.

[0029] Second, during the low-speed ground movement phase, electric-driven wheels are used for movement, which is highly efficient and extends the effective flight time.

[0030] Third, the connection between ground control and takeoff phase shortens the aircraft's ground travel distance and time during takeoff, improves takeoff efficiency, and helps extend effective flight time.

[0031] Fourth, the electric drive wheels assist the aircraft in accelerating to V2 before disengaging the wheel clutch. This not only shortens the takeoff distance but also prevents the wheel motors from dragging and being damaged after exceeding the design speed.

[0032] Fifth, during the deceleration and descent phase, the flight motor's reverse energy storage device is charged, thus achieving energy recovery;

[0033] Sixth, during the landing and taxiing phase, the wheel motors are charged by the reverse energy storage device, thus achieving energy recovery;

[0034] Seventh, the coordination between landing taxiing and ground control helps improve aircraft operational efficiency and achieve seamless transitions between different phases of the aircraft's operation. Attached Figure Description

[0035] Figure 1 A frontal view of a general aviation aircraft;

[0036] Figure 2 This is a schematic diagram of an electric drive system;

[0037] Figure 3 This is a schematic diagram of the electrically driven wheel 100;

[0038] Figure 4 An exploded view of the electric drive wheel 100;

[0039] Figure 5 This is a cross-sectional view of the electric drive wheel 100;

[0040] Figure 6 for Figure 5 A magnified view of a portion of the image;

[0041] Figure 7 This is a schematic diagram of the turbine motor 6;

[0042] Figure 8 This is a schematic diagram of reducer 5;

[0043] Figure 9 This is a schematic diagram of clutch 4.

[0044] Explanation of symbols in the diagram:

[0045] 100 Electric drive wheels, 200 Energy storage device, 300 Control module, 400 Flight control input, 500 Taxiing control input, 600 Flight motor controller, 700 Wheel motor controller, 800 Wheel clutch controller;

[0046] 1. Landing gear wheel fork, 11. Left fork arm, 12. Right fork arm, 111. Left axle hole, 121. Right axle hole;

[0047] 2. Wheel hub, 21. Wheel rim, 22. Wheel disc, 23. Hollow axle sleeve, 210. First mounting space, 230. Second mounting space;

[0048] 3. Tires;

[0049] 4 Clutch, 41 Clutch body, 42 Driving plate, 43 Driven plate, 44 Clutch bearing, 421 Transmission end, 422 Transmission rod, 423 Flange;

[0050] 5. Reducer, 51. Ring gear, 52. Planetary gear assembly, 53. Sun gear, 54. End cap, 55. Elastic component;

[0051] 6. Wheel motor, 61. Motor housing, 62. Stator assembly, 63. Rotor assembly, 64. Motor shaft, 611. Front end face, 612. Rear end face, 641. Shaft through hole, 642. Groove;

[0052] 7. Wheel axle, 71. Long axle, 72. Short axle sleeve, 710. Heat dissipation channel;

[0053] 8. Support bearings;

[0054] 9. Flight electric motor. Detailed Implementation

[0055] Combination Figure 1 , Figure 2 A general-purpose aircraft electric drive system includes an electric drive wheel 100, an energy storage device 200, a control module 300, a flight control input 400, a taxiing control input 500, a flight motor controller 600, a wheel motor controller 700, a wheel clutch controller 800, and a flight motor 9. The electric drive wheel 100 is mounted on the nose of the aircraft and houses the wheel motor 6 and a wheel clutch 4. The energy storage device 200, control module 300, flight control input 400, and taxiing control input 500 are installed inside the aircraft. The motor 9 is equipped with a propeller. The energy storage device 200, flight control input 400, and taxiing control input 500 are electrically connected to the control module 300. The flight motor 9 is electrically connected to the flight control input 400 via the flight motor controller 600. The wheel motor 6 and wheel clutch 4 are electrically connected to the control module 300 via the wheel motor controller 700 and wheel clutch controller 800, respectively.

[0056] Combination Figures 3 to 6The electric drive wheel 100 also includes a landing gear wheel fork 1, a wheel hub 2, a tire 3, a reducer 5, and a wheel axle 7. The landing gear wheel fork 1 has a left fork arm 11 and a right fork arm 12 arranged opposite each other, with a left axle hole 111 and a right axle hole 121 coaxially formed on the left fork arm 11 and right fork arm 12, respectively. The wheel hub 2 is a one-piece structure, having an annular rim 21, a tubular hollow bushing 23, and a wheel disc 22 connecting the two at one end. The rim 21, wheel disc 22, and hollow bushing 23 enclose a first mounting space 210 with an opening, and the hollow bushing 23 has a second mounting space 230 extending through both ends. The tire 3 is fitted onto the outside of the wheel hub 2. The reducer 5, wheel clutch 4, and wheel motor 6 are sequentially arranged within the first mounting space 210. The output end of the reducer 5 is fixedly connected to the wheel disc 22, and the wheel motor 6 is fixed to the right fork arm 12. The wheel motor 6 connects / disconnects from the torque input of the reducer 5 via the wheel clutch 4. The axle 7 passes through the left axle hole 111, the second mounting space 230, and the right axle hole 121 to support the wheel hub 2 on the landing gear wheel fork 1.

[0057] Combination Figure 6 , Figure 8 The reducer 5 is a planetary reducer, including a ring gear 51, a planetary gear assembly 52, and a sun gear 53. The ring gear 51 is the output end, and the sun gear 53 is the input end. The wheel clutch 4 is an electromagnetic clutch, including a clutch body 41, a driving plate 42, and a driven plate 43. Both the driving plate 42 and the driven plate 43 can rotate relative to the axis of the clutch body 41. The clutch body 41 generates electromagnetic force to attract the driven plate 43 onto the driving plate 42, so that the two rotate synchronously. The wheel motor 6 includes a motor housing 61, a stator assembly 62, a rotor assembly 63, and a motor shaft 64. The motor housing 61 is fixed on the right fork arm 12. The motor shaft 64 is driven by the drive plate 42 of the wheel clutch 4. The driven plate 43 of the wheel clutch 4 is driven by the sun gear 53 of the reducer 5. When the clutch body 41 is energized, the electromagnetic force attracts the driven plate 43 to the drive plate 42. The motor shaft 64 drives the drive plate 42, the driven plate 43 and the sun gear 53 to rotate in sequence. After the planetary gear assembly 52 and the ring gear 51 reduce the speed and increase the torque, the hub 2 is driven to rotate.

[0058] Combination Figure 6 , Figure 7 The motor housing 61 has a front end face 611 and a rear end face 612. The rear end face 612 is fixedly connected to the right fork arm 12, and the front end face 611 is fixedly connected to the clutch body 41.

[0059] Combination Figure 7 , Figure 9The motor shaft 64 has a groove 642 on its outer side. The drive disc 42 of the wheel clutch 4 has a disc-shaped transmission end 421 and a tubular transmission rod 422. The transmission rod 422 has a flange 423 for matching the groove 642 of the motor shaft 64. The motor shaft 64 and the drive disc 42 transmit torque through the groove 642 and the flange 423.

[0060] like Figure 6 The reducer 5 also includes an end cover 54 and an elastic element 55. The elastic element 55 is disposed between the sun gear 53 and the end cover 54 to make the sun gear 53 tend to move away from the end cover 54. The driven plate 43 of the gear clutch 4 is fixed on the sun gear 53. The driven plate 43 and the driving plate 42 are arranged opposite each other with a certain gap. When the clutch body 41 is energized, the electromagnetic force drives the driven plate 43 to move towards the driving plate 42 to connect the two. After the power is turned off, the elastic element 55 pushes the driven plate 43 away from the driving plate 42 to disengage the two.

[0061] like Figure 6 The hollow bushing 23 has at least two support bearings 8 in its second mounting space 230. The support bearings 8 are sleeved on the outside of the axle 7 so that the hub 2 can rotate freely around the axis of the axle 7. The axle 7 includes a long shaft 71 and a short bushing 72. The long shaft 71 has a heat dissipation channel 710 that extends through both ends.

[0062] refer to Figure 2 A control method for a general-purpose aircraft electric drive system includes the following steps performed in sequence:

[0063] First, during the low-speed ground movement phase, the pilot inputs forward / reverse commands to the control module 300 via the taxiing control input 500. The control module 300 controls the wheel clutch controller 800 to supply power to the wheel clutch 4. The wheel clutch 4 connects the wheel motor 6 to the reducer 5. The control module 300 controls the wheel motor controller 700 to supply power to the wheel motor 6. The motor 6 drives the tire 3 to rotate after being transmitted through the wheel clutch 4, reducer 5, and wheel hub 2, thereby driving the aircraft forward / reverse. The movement speed is ≤V1.

[0064] Second, during takeoff, the pilot inputs flight commands to the control module 300 via the flight control input 400. The control module 300 controls the flight motor controller 600 to supply power to the flight motor 9. The motor 9 drives the propeller to rotate, thereby accelerating the aircraft. The aircraft speed is V2. When V2 > V1, the control module 300 controls the wheel motor controller 700 to de-energize the wheel motor 6 and controls the wheel clutch controller 800 to de-energize the wheel clutch 4.

[0065] Third, during the flight phase, the pilot inputs flight commands to the control module 300 through the flight control input 400. The control module 300 controls the flight motor controller 600 to supply power to the flight motor 9. The motor 9 drives the propeller to rotate, thereby driving the aircraft to fly.

[0066] Fourth, during the deceleration and landing phase, the propeller drives the flight motor 9 to rotate during the aircraft's deceleration and landing. The flight motor 9 acts as a generator and charges the energy storage device 200 via the flight motor controller 600.

[0067] Fifth, during the landing taxiing phase, after landing, the aircraft speed is V3. When V3 > V1, the control module 300 controls the wheel clutch controller 800 to supply power to the wheel clutch 4. The wheel clutch 4 connects the wheel motor 6 with the reducer 5. The tire 3 drives the wheel motor 6 to rotate through the hub 2, reducer 5 and wheel clutch 4. At this time, the wheel motor 6 acts as a generator and charges the energy storage device 200 through the wheel motor controller 700.

[0068] Sixth, when V3=V1, the control module 300 controls the wheel motor controller 700 to supply power to the wheel motor 6. The motor 6 drives the tire 3 to rotate after being transmitted through the wheel clutch 4, reducer 5 and wheel hub 2, thereby driving the aircraft to move forward / backward. The moving speed is ≤V1.

[0069] The above description is only a preferred embodiment of the present invention. For those skilled in the art, there will be changes in the specific implementation and application scope based on the ideas of the present invention. The content of this specification should not be construed as a limitation of the present invention.

Claims

1. A general aircraft electric drive system, comprising an electric drive wheel (100), a control module (300), a flight control input (400), a flight motor controller (600), a wheel motor controller (700) and a flight motor (9); The electric drive wheel is installed on the head of the aircraft, and a wheel motor (6) is arranged in the electric drive wheel; the control module and the flight control input are installed in the interior of the aircraft, and the flight motor is provided with a propeller; The flight control input is electrically connected with the control module respectively; the flight motor is electrically connected with the flight control input through the flight motor controller; the wheel motor is electrically connected with the control module through the wheel motor controller; characterized in that In the low-speed moving stage of the aircraft on the ground, the control module (300) controls the wheel motor controller (700) to supply power to the wheel motor (6), and the wheel motor drives the aircraft to move forward or backward, and the moving speed is less than or equal to V1; The control module controls the flight motor controller (600) to supply power to the flight motor (9), the flight motor drives the propeller to rotate, and then drives the aircraft to accelerate, and the speed of the accelerated aircraft is V2, when V2>V1, the control module controls the wheel motor controller (700) to cut off the power supply of the wheel motor (6).

2. The electrically powered system for general aviation aircraft of claim 1, wherein: Further comprising an energy storage device (200), which is installed in the interior of the aircraft and is electrically connected with the control module (300); In the deceleration and landing process of the aircraft, the propeller drives the flight motor (9) to rotate, and the flight motor acts as a generator to charge the energy storage device through the flight motor controller (600); After the aircraft lands, the speed of the aircraft is V3, when V3>V1, the electric drive wheel (100) drives the wheel motor (6) to rotate through the tire (3) in contact with the ground, at this time, the wheel motor acts as a generator to charge the energy storage device (200) through the wheel motor controller (700); When V3 decreases to V1, the control module (300) controls the wheel motor controller (700) to supply power to the wheel motor (6), and the wheel motor drives the aircraft to move forward or backward.

3. The electrically powered system for general aviation aircraft of claim 2, wherein: Further comprising a taxi control input (500) and a wheel clutch controller (800), the taxi control input and the wheel clutch controller are electrically connected with the control module (300), and the electric drive wheel (100) is provided with a wheel clutch (4) therein; In the low-speed moving stage of the aircraft on the ground, the pilot inputs forward or backward instructions to the control module through the taxi control input (500), the control module controls the wheel clutch controller (800) to supply power to the wheel clutch, the wheel clutch links the wheel motor (6) with the hub of the electric drive wheel, and the control module (300) controls the wheel motor controller (700) to supply power to the wheel motor (6); In the take-off stage, when the speed of the aircraft V2>V1, the control module controls the wheel motor controller (700) to cut off the power supply of the wheel motor (6) at the same time, and controls the wheel clutch controller (800) to cut off the power supply of the wheel clutch (4). After landing, when the aircraft speed V3>V1, the control module controls the wheel clutch controller to supply power to the wheel clutch, the wheel clutch connects the wheel motor (6) with the hub of the electric drive wheel, the hub (2) drives the wheel motor to rotate, at this time the wheel motor as a generator charges the energy storage device through the wheel motor controller (700).

4. The electrically powered system for general aviation aircraft of claim 3, wherein: The electric drive wheel (100) comprises a landing gear fork (1), a hub (2), a tire (3), a speed reducer (5) and an axle (7); The landing gear fork has oppositely arranged left and right fork arms (11) and (12), and coaxial left and right shaft holes (111) and (121) are respectively formed in the left and right fork arms; The hub is an integral structure, has an annular rim (21), a tubular hollow shaft sleeve (23) and a disc (22) connecting the two at one end, and the rim, the disc and the hollow shaft sleeve surround to form a first installation space (210) with an opening, and the hollow shaft sleeve has a second installation space (230) penetrating through both ends; The tire (3) is sleeved on the outside of the hub (2); The speed reducer (5), the wheel clutch (4) and the wheel motor (6) are sequentially arranged in the first installation space (210), the output end of the speed reducer is fixedly connected with the disc, the wheel motor (6) is fixed on the right fork arm (12), and the wheel motor is connected / disconnected with the torque input end of the speed reducer through the wheel clutch; The axle (7) supports the hub (2) on the landing gear fork by penetrating through the left shaft hole (111), the second installation space (230) and the right shaft hole (121).

5. The electrically powered system for general aviation aircraft of claim 4, wherein: The speed reducer (5) is a planetary reducer, comprising a gear ring (51), a planetary wheel assembly (52) and a sun gear (53), the gear ring is an output end, and the sun gear is an input end; The wheel clutch (4) is an electromagnetic clutch, comprising a clutch body (41), a driving disc (42) and a driven disc (43), the driving disc and the driven disc can rotate relative to the axis of the clutch body, the clutch body attracts the driven disc to the driving disc by generating electromagnetic force to make them rotate synchronously; The wheel motor (6) comprises a motor shell (61), a stator assembly (62), a rotor assembly (63) and a motor shaft (64); The motor shell is fixed on the right fork arm (12), the motor shaft is in transmission connection with the driving disc (42) of the wheel clutch (4), the driven disc (43) of the wheel clutch is in transmission connection with the sun gear (53) of the speed reducer (5), the electromagnetic force of the clutch body (41) attracts the driven disc to the driving disc when the clutch body is electrified, the motor shaft (64) drives the driving disc, the driven disc and the sun gear to rotate in turn, and drives the hub (2) to rotate after the speed is reduced and the torque is increased through the planetary wheel assembly (52) and the gear ring (51).

6. A generic electrically driven aircraft system as claimed in claim 5, characterised in that: The speed reducer (5) comprises an end cover (54) and an elastic member (55), the elastic member is arranged between the sun gear (53) and the end cover, so that the sun gear has a tendency to move away from the end cover; The driven disc (43) of the wheel clutch (4) is fixed on the sun gear, the driven disc and the driving disc (42) are oppositely arranged and have a certain gap, when the clutch body (41) is powered, the electromagnetic force drives the driven disc to move towards the driving disc to connect the two, and after power off, the elastic member (55) pushes the driven disc away from the driving disc to disconnect the two.

7. A control method for a general aircraft electric drive system, characterized by: The control method comprises the following steps in sequence: 1) Ground low-speed moving stage, the pilot inputs forward / reverse instruction to the control module (300) through the taxi control input (500), the control module controls the wheel clutch controller (800) to supply power to the wheel clutch (4), the wheel clutch connects the wheel motor (6) and the speed reducer (5), the control module controls the wheel motor controller (700) to supply power to the wheel motor, the wheel motor drives the tire (3) to rotate through the wheel clutch, the speed reducer and the hub (2), and then drives the aircraft to move forward / reverse, and the moving speed is less than or equal to V1; 2) Take-off stage, the pilot inputs flight instruction to the control module through the flight control input (400), the control module controls the flight motor controller (600) to supply power to the flight motor (9), the motor drives the propeller to rotate, and then drives the aircraft to accelerate, and the speed of the accelerated aircraft is V2, when V2>V1, the control module controls the wheel motor controller (700) to cut off the power supply of the wheel motor (6), and controls the wheel clutch controller (800) to cut off the power supply of the wheel clutch (4); 3) Flight stage, the pilot inputs flight instruction to the control module (300) through the flight control input (400), the control module controls the flight motor controller (600) to supply power to the flight motor (9), the motor drives the propeller to rotate, and then drives the aircraft to fly; 4) Deceleration and landing stage, during the deceleration and landing process of the aircraft, the flight motor (9) is driven by the propeller to rotate, and the flight motor functions as a generator to charge the energy storage device (200) through the flight motor controller (600); 5) Landing taxi stage, after landing, the speed of the aircraft is V3, when V3>V1, the control module controls the wheel clutch controller (800) to supply power to the wheel clutch (4), the wheel clutch connects the wheel motor (6) and the speed reducer (5), and the tire (3) drives the wheel motor to rotate through the hub (2), the speed reducer and the wheel clutch, at this time, the wheel motor functions as a generator to charge the energy storage device (200) through the wheel motor controller (700).

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