Electric motor wheel hybrid power system in airplane ground operation stage and control method

Abstract

The invention discloses an electric motor wheel hybrid power system and a control method for an aircraft ground operation stage. The system comprises an energy module, a power module, a power transmission and distribution module and a motor wheel hybrid power system controller. The energy module comprises an auxiliary power device and an energy storage device; the power module comprises a motor / generator controller, a motor / generator and a speed reducer; the power transmission and distribution module comprises an AC-DC converter, a bidirectional DC-DC converter and a DC bus. The APU, the energy storage device, the micro power distribution module, the driving motor and the generator system are integrated, power cooperation is achieved, and autonomous reversing and advancing movement of an aircraft are achieved in the gallery bridge pushing-out stage; fuel consumption and pollutant emission are reduced in the sliding stage; in the takeoff taxiing stage, traction generated by driving main landing gear wheels through a motor / generator compensates thrust of the aero-engine, so that the rotating speed of the aero-engine is reduced, the turbine temperature is reduced, and the service life of the engine is prolonged; the motor / generator shares braking force in the landing and skating stage, energy recovery is achieved, and abrasion of brake pads is reduced.

Description

Technical Field

[0001] The present invention belongs to the technical field of aircraft power systems, and particularly relates to an electric motor-wheel hybrid power system and a control method for the ground operation stage of an aircraft, including the stages of pushback from the jet bridge, taxiing, takeoff roll, and landing roll. Background Art

[0002] When a civil aviation aircraft taxis on the ground, the propulsion efficiency provided by the main engine is low, and a large amount of pollutants are emitted. If a tow truck is used to push the aircraft back from the jet bridge, it takes a long time, which will affect flight schedules; the high total temperature before the turbine of the engine during takeoff also has a great impact on the engine cycle count. However, the existing electric green taxiing systems fail to solve the problem of loss of the hot-end components of the engine caused by high thrust during the takeoff stage; the existing electric taxiing systems only solve the problems of pushback from the jet bridge and taxiing, and do not involve coordinated control during the takeoff stage. Therefore, there is an urgent need for a hybrid power system that integrates power optimization during the taxiing and takeoff stages, reduces the engine load, and can further achieve the energy-saving goal and reduce the wear of the braking components by partially recovering energy during the landing roll stage. Summary of the Invention

[0003] In order to solve the above problems, the purpose of the present invention is to provide an electric motor-wheel hybrid power system for the ground operation stage of an aircraft.

[0004] To achieve the above object, the electric motor-wheel hybrid power system for the ground operation stage of an aircraft provided by the present invention is installed on the aircraft. The ground operation stage of the aircraft includes the stages of pushback from the jet bridge, taxiing, takeoff roll, and landing roll. The electric motor-wheel hybrid power system includes an energy module, a power module, a power transmission and distribution module, and an electric motor-wheel hybrid power system controller. Among them, the energy module includes an auxiliary power unit (APU) and an energy storage device; the power module includes a plurality of electric / generator controllers, a plurality of electric / generators, and a plurality of speed reducers; each electric / generator is mechanically coupled to each main landing gear wheel of the aircraft through a speed reducer; the electric / generator is connected to the electric / generator controller through a cable; the power transmission and distribution module includes an AC-DC converter, a bidirectional DC-DC converter, and a DC bus; the auxiliary power unit is connected to the AC-DC converter through a cable; the energy storage device is connected to the bidirectional DC-DC converter through a cable; the AC-DC converter and the bidirectional DC-DC converter are electrically connected to the electric / generator controller through the DC bus; the electric motor-wheel hybrid power system controller is electrically connected to the energy module, the power module, and the power transmission and distribution module respectively, thereby forming a complete energy transmission route.

[0005] The electric / generator and the speed reducer are installed on the main landing gear wheel.

[0006] The control method of the motor-wheel hybrid power system during the ground operation stage of an aircraft provided by the present invention includes the following steps carried out in sequence:

[0007] 1) The driver issues corresponding driver commands to the motor-wheel hybrid power system controller according to different states of the aircraft. After receiving the driver commands, the motor-wheel hybrid power system controller controls the operation of each module;

[0008] 2) During the apron push-out stage and the taxiing stage, the energy module transmits direct current to the DC bus and issues commands to the motor / generator controller. The motor / generator controller converts the direct current into alternating current to drive the motor / generator to work. The motor / generator outputs energy in the motor mode to drive the reducer, and then drives the main landing gear wheels to move;

[0009] 3) During the takeoff roll stage, let T0 be the initial moment of takeoff roll and T1 be the moment when the front wheels leave the ground. From T0 to T1, the energy module starts to supply power. The direct current is transmitted to the motor / generator controller through the DC bus and converted into alternating current to drive the motor / generator to work, and then drives the main landing gear wheels to move through the reducer, assisting the aviation engine to accelerate the aircraft;

[0010] 4) During the landing roll stage, after the main landing gear wheels touch the ground, they rotate at high speed due to inertia, driving the reducer and the motor / generator to rotate. The speed of the motor / generator is controlled by the motor / generator controller. At this time, the motor / generator is in the generator mode and outputs alternating current, which is converted into direct current through the motor / generator controller. The direct current is transmitted through the DC bus, and the two-way DC-DC converter transfers the energy to the energy storage device to achieve energy recovery during the landing roll stage and decelerate the wheels.

[0011] The motor-wheel hybrid power system and control method during the ground operation stage of the aircraft provided by the present invention have the following beneficial effects:

[0012] 1. The system integrates the APU, energy storage device, micro power distribution module, drive motor and generator system, realizing power coordination. During the apron push-out stage, the aircraft can achieve autonomous reverse and forward movement, improving the apron push-out speed.

[0013] 2. Reduces fuel consumption and pollutant emissions during the taxiing stage.

[0014] 3. During the takeoff roll stage, the traction force generated by driving the main landing gear wheels in the motor mode by the motor / generator compensates for part of the thrust of the aviation engine, reducing the rotational speed of the aviation engine, thereby reducing the turbine temperature, extending the service life of the aviation engine, and reducing emissions to a certain extent.

[0015] 4. During the landing roll phase, through the energy conversion of the main landing gear wheels, energy is stored in the energy storage device, achieving partial energy recovery. During this phase, the motor-generator shares the braking force, reducing brake pad wear, extending the maintenance cycle, and eliminating the need for on-station charging, thus increasing the takeoff and landing frequency density.

[0016] 5. This hybrid power system can also be used for the takeoff of ordinary aircraft models at high altitudes, assisting the aviation engine to push non-high-altitude models to take off at high-altitude airports or at short runway airports. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a schematic diagram of the installation position of the motor-wheel hybrid power system provided by the present invention on an aircraft.

[0018] Figure 2 It is a schematic diagram of the structure of the motor-wheel hybrid power system provided by the present invention.

[0019] Figure 3 It is a flowchart of the control method of the motor-wheel hybrid power system provided by the present invention. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0020] The present invention will be described in detail below with reference to the accompanying drawings.

[0021] As Figure 1 、 Figure 2 shown, the motor-wheel hybrid power system 1 during the ground operation phase of the aircraft provided by the present invention is installed on the aircraft 2, and includes an energy module, a power module, a power transmission and distribution module, and a motor-wheel hybrid power system controller 3; wherein, the energy module includes an auxiliary power unit 4 and an energy storage device 6; the power module includes multiple motor / generator controllers 9, multiple motor / generators 10, and multiple speed reducers 11; each motor / generator 10 is mechanically coupled to each main landing gear wheel 12 on the aircraft 2 through a speed reducer 11; the motor / generator 10 is connected to the motor / generator controller 9 through a cable; the power transmission and distribution module includes an AC-DC converter 5, a bidirectional DC-DC converter 7, and a DC bus 8; the auxiliary power unit 4 is connected to the AC-DC converter 5 through a cable; the energy storage device 6 is connected to the bidirectional DC-DC converter 7 through a cable; the AC-DC converter 5 and the bidirectional DC-DC converter 7 are electrically connected to the motor / generator controller 9 through the DC bus 8; the motor-wheel hybrid power system controller 3 is electrically connected to the energy module, the power module, and the power transmission and distribution module respectively, thus forming a complete energy transmission route.

[0022] The motor / generator 10 and the speed reducer 11 are installed on the main landing gear wheel 12.

[0023] The control method of the above-mentioned motor-wheel hybrid power system during the ground operation phase of the aircraft includes the following steps carried out in sequence:

[0024] 1) The driver issues corresponding driver commands to the motor-wheel hybrid system controller 3 according to different states of the aircraft 2. After receiving the driver commands, the motor-wheel hybrid system controller 3 controls the operation of each module.

[0025] 2) During the apron push-out stage and the taxiing stage, the motor-wheel hybrid system controller 3 uses the energy module to transmit direct current to the DC bus 8 and issues commands to the motor / generator controller 9. The motor / generator controller 9 converts the direct current into alternating current to drive the motor / generator 10 to operate. The motor / generator 10 outputs energy in the motor mode to drive the reduction gear 11, and then drives the main landing gear wheels 12 to move.

[0026] 3) During the takeoff roll stage, let T0 be the initial moment of takeoff roll and T1 be the moment when the front wheel leaves the ground. From T0 to T1, the energy module starts to supply power. The direct current is transmitted through the DC bus 8 to the motor / generator controller 9 and converted into alternating current to drive the motor / generator 10 to operate, and then drives the main landing gear wheels 12 to move through the reduction gear 11, and the auxiliary aviation engine pushes the aircraft 2 to accelerate.

[0027] 4) During the landing roll stage, after the main landing gear wheels 12 touch the ground, they rotate at high speed due to inertia, driving the reduction gear 11 and the motor / generator 10 to rotate. The motor / generator controller 9 is used to control the rotation speed of the motor / generator 10. At this time, the motor / generator 10 is in the generator mode and outputs alternating current, which is converted into direct current through the motor / generator controller 9. The direct current is transmitted through the DC bus 8, and the bidirectional DC-DC converter 7 transfers the energy to the energy storage device 6 to achieve energy recovery during the landing roll stage and decelerate the wheels.

[0028] The inventor of the present invention uses the MATLAB / Simulink simulation platform to conduct emission benefit prediction and engine life analysis on the motor-wheel hybrid system provided by the present invention for the apron push-out stage, taxiing stage, takeoff roll stage, and landing roll stage. The results show that the motor-wheel hybrid system of the present invention successfully reduces fuel consumption, and emissions such as CO, HC, and NOx are also reduced to varying degrees; while the EGT margin is improved, the life of the aviation engine is also extended, thereby reducing the maintenance cost of the aviation engine. The energy recovery during the landing roll stage also reduces the wear of the brake pads and extends the maintenance cycle.

Claims

1. A motor-wheel hybrid power system during the ground operation phase of an aircraft. The ground operation phase of the aircraft includes the phase of being pushed out by a jet bridge, the taxiing phase, the takeoff roll phase, and the landing roll phase. It is characterized in that: The motor-wheel hybrid power system (1) is installed on an aircraft (2), and includes an energy module, a power module, a power transmission and distribution module, and a motor-wheel hybrid power system controller (3); wherein, the energy module includes an auxiliary power unit (4) and an energy storage device (6); the power module includes multiple electric / generator controllers (9), multiple electric / generators (10), and multiple speed reducers (11); each electric / generator (10) is mechanically coupled to each main landing gear wheel (12) on the aircraft (2) through a speed reducer (11); the electric / generator (10) is connected to the electric / generator controller (9) through a cable; the power transmission and distribution module includes an AC-DC converter (5), a bidirectional DC-DC converter (7), and a DC bus (8); the auxiliary power unit (4) is connected to the AC-DC converter (5) through a cable; the energy storage device (6) is connected to the bidirectional DC-DC converter (7) through a cable; the AC-DC converter (5) and the bidirectional DC-DC converter (7) are electrically connected to the electric / generator controller (9) through the DC bus (8); the motor-wheel hybrid power system controller (3) is electrically connected to the energy module, the power module, and the power transmission and distribution module respectively, thereby forming a complete energy transmission route.

2. The motor-wheel hybrid power system during the ground operation stage of an aircraft according to claim 1, wherein: The electric / generator (10) and the speed reducer (11) are installed on the main landing gear wheel (12).

3. A control method for an electric motor-wheel hybrid power system during the ground operation stage of an aircraft according to any one of claims 1 to 2, characterized in that: The control method includes the following steps carried out in sequence: 1) The driver issues corresponding driver commands to the motor-wheel hybrid power system controller (3) according to different states of the aircraft (2). After receiving the driver commands, the motor-wheel hybrid power system controller (3) controls the operation of each module. 2) During the apron push-out stage and the taxiing stage, the energy module transmits direct current to the DC bus (8) and issues commands to the electric / generator controller (9). The electric / generator controller (9) converts the direct current into alternating current to drive the electric / generator (10) to operate. The electric / generator (10) outputs energy in the motor mode to drive the speed reducer (11), and then drives the main landing gear wheel (12) to move. 3) During the takeoff roll stage, let T0 be the initial moment of takeoff roll and T1 be the moment when the front wheels leave the ground. From T0 to T1, the energy module starts to supply power. The direct current is transmitted to the electric / generator controller (9) through the DC bus (8) and converted into alternating current to drive the electric / generator (10) to operate, and then drives the main landing gear wheel (12) to move through the speed reducer (11). The auxiliary aeroengine pushes the aircraft (2) to accelerate. 4) During the landing roll phase, after the main landing gear wheels (12) touch the ground, they rotate at high speed due to inertia, driving the reducer (11) and the electric / generator (10) to rotate. The speed of the electric / generator (10) is controlled by the electric / generator controller (9). At this time, the electric / generator (10) is in the generator mode and outputs alternating current, which is converted into direct current through the electric / generator controller (9). The direct current is transmitted to the energy storage device (6) by the bidirectional DC-DC converter (7) through the DC bus (8) to achieve energy recovery during the landing roll phase and decelerate the wheels.

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