An aircraft wheel braking system based on electric braking

Abstract

The invention discloses an aircraft wheel brake system based on electric braking, comprising a brake disc, an electromagnetic coil, a power control unit, a brake control unit, a wheel speed sensor and a temperature sensor, wherein the brake control unit is connected to the electromagnetic coil, the power control unit, the wheel speed sensor and the temperature sensor, and the power control unit is connected to the electromagnetic coil. During normal braking, the brake control unit sends a control signal to the power control unit according to the brake disc temperature and the wheel speed. After receiving the control signal, the power control unit adjusts the electromagnetic field generated by the electromagnetic coil to change the magnetic field passing through the brake disc and generate an induced current so that the brake disc is subjected to electromagnetic damping in the magnetic field to decelerate the wheel. The invention is an aircraft wheel brake system using electricity as the only power source, and a cable is used instead of a high-pressure hydraulic pipe, thereby reducing the weight of the system and the risk of hydraulic oil leakage, and there is no need to regularly replace the brake assembly, which is convenient for the maintenance of the wheel brake system and has low maintenance costs.

Description

Technical Field

[0001] The invention relates to an aircraft wheel brake system, in particular to an aircraft wheel brake system based on electric braking. Background Art

[0002] At present, most civil aircraft use multi-disc mechanical friction wheel brake systems that are electrically controlled and hydraulically driven. The more advanced Boeing 787 aircraft uses multi-disc mechanical friction wheel brake systems that are electrically controlled and electrically driven. The multi-disc mechanical friction wheel brake system is mainly composed of multiple discs and static discs. When the wheel is running, the dynamic disc is driven. When the brake is not applied, the dynamic disc is separated from the static disc, and no friction is generated between the dynamic disc and the static disc. When braking, the hydraulic pressure or electricity provides the brake pressure to make the dynamic disc contact with the static disc, and the friction between the two is generated to stop the rotation of the wheel.

[0003] The current mainstream aircraft wheel braking methods have the following problems:

[0004] ⑴ The brake system is heavy: In order to reduce the weight of the wheel brake assembly, more and more dynamic and static discs are using carbon / carbon composite materials, but the weight of such wheel brake assemblies is still relatively large. Taking the common Airbus A320 aircraft as an example, the weight of a single wheel brake assembly can reach about 70kg.

[0005] ⑵ High maintenance cost, and the brake components need to be replaced regularly: Due to the use of contact friction braking, the wear of the brake components needs to be checked and replaced as appropriate for each flight. Currently, for most civil aircraft, the brake components need to be replaced after about two thousand flight cycles due to excessive wear of the brake disc. If a hydraulically driven brake disc is used, there is also the possibility of leakage of high-pressure hydraulic oil.

[0006] ⑶ Low energy utilization rate: Brake components that use contact friction braking will generate a lot of heat when working. This excess heat will eventually be released into the air, causing a lot of energy waste. Summary of the invention

[0007] The object of the present invention is to provide an aircraft wheel brake system based on electric braking, which is light in weight, does not require regular replacement of brake components, has low maintenance costs, and does not have the risk of oil leakage.

[0008] The object of the present invention is achieved through the following technical measures: an aircraft wheel brake system based on electric braking, characterized in that it includes a brake disc installed on a hub assembly and rotating with the wheel, an electromagnetic coil installed on an axle assembly, a power control unit, a brake control unit, a wheel speed sensor installed on the hub assembly for measuring the wheel speed, and a temperature sensor installed on the hub assembly for measuring the brake disc temperature, the brake control unit is respectively connected to the electromagnetic coil, the power control unit, the wheel speed sensor and the temperature sensor, the power control unit is connected to the electromagnetic coil, when the aircraft brakes normally, the brake control unit sends a control signal to the power control unit according to the brake disc temperature and the wheel speed, and after receiving the control signal, the power control unit adjusts the electromagnetic field generated by the electromagnetic coil to change the magnetic field passing through the brake disc and generate an induced current so that the brake disc is subjected to electromagnetic damping in the magnetic field, thereby slowing down the wheel.

[0009] The present invention is an aircraft wheel brake system that uses electricity as the sole power source, and uses cables instead of high-pressure hydraulic pipes, thereby reducing the weight of the system and the risk of hydraulic oil leakage. In addition, there is no need to regularly replace the brake components, which facilitates the maintenance of the wheel brake system and has low maintenance costs.

[0010] In order to improve the reliability of the electromagnetic coil, the electromagnetic coil of the present invention is composed of multiple parallel coils.

[0011] In order to prevent the magnetic field from having adverse effects on other systems outside the system of the present invention, electromagnetic shielding materials are installed on both the hub assembly and the axle assembly of the present invention.

[0012] In order to reduce the temperature rise of the brake disc in the wheel hub assembly caused by the thermal effect of the induced current, the brake disc of the present invention is composed of stacked metal sheets that are insulated from each other and have high resistivity.

[0013] In order to provide a braking function when an aircraft is parked to prevent the aircraft from moving unexpectedly, the aircraft wheel brake system of the present invention includes a moving disc and a static disc, the power control unit is connected to the static disc, the moving disc and the static disc are both installed on the wheel axle assembly through bearings, the moving disc is driven by the spline on the wheel hub assembly and rotates with the wheel hub assembly, when the parking brake is working, the brake control unit receives the brake signal and controls the static disc actuator through the power control unit to drive the static disc to contact the moving disc to brake.

[0014] The aircraft wheel brake system described in the present invention includes a rotor assembly formed by winding wires and an energy storage unit. The rotor assembly is installed on the wheel hub to cut the magnetic field generated by the electromagnetic coil. The rotor assembly is connected to the power control unit. The energy storage unit is connected to the power control unit and the brake control unit. The power control unit converts the current generated in the rotor assembly into electrical energy suitable for storage and stores it in the energy storage unit. The energy storage unit supplies power to the brake control unit and the aircraft power system. Therefore, the energy utilization rate of the present invention is higher. The energy storage unit also receives power provided by the aircraft power system.

[0015] Compared with the prior art, the present invention has the following significant effects:

[0016] (1) The present invention is an aircraft wheel brake system that uses electricity as the only power source. Cables are used instead of high-pressure hydraulic pipes, which reduces the weight of the system while reducing the risk of hydraulic oil leakage. In addition, there is no need to regularly replace the brake components, which facilitates the maintenance of the wheel brake system and has low maintenance costs.

[0017] (2) The power source used in the present invention comes directly from the energy storage unit, which not only improves the reliability of the system of the present invention, but also has a higher energy utilization rate.

[0018] ⑶ The invention has a simple structure, low cost, strong practicability, and is suitable for wide promotion and use. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] The present invention is further described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0020] Figure 1 It is a structural diagram of the composition of the present invention;

[0021] Figure 2 It is a working principle diagram of the present invention. DETAILED DESCRIPTION

[0022] The present invention is further illustrated below through the description of specific implementation methods, but this is not a limitation of the present invention. Those skilled in the art can make various modifications or improvements based on the basic idea of ​​the present invention, but as long as they do not deviate from the basic idea of ​​the present invention, they are all within the protection scope of the present invention.

[0023] like Figure 1 and Figure 2As shown, the present invention is an aircraft wheel brake system based on electric braking, including a brake disc installed on a hub assembly and rotating with the wheel, an electromagnetic coil installed on an axle assembly, a power control unit, a brake control unit, a wheel speed sensor installed on the hub assembly for measuring the wheel speed, and a temperature sensor installed on the hub assembly for measuring the brake disc temperature. The brake control unit is respectively connected to the electromagnetic coil, the power control unit, the wheel speed sensor and the temperature sensor. The power control unit is connected to the electromagnetic coil. When the aircraft is operating normally, the brake control unit sends a control signal to the power control unit according to the brake disc temperature and the wheel speed. After receiving the control signal, the power control unit adjusts the electromagnetic field generated by the electromagnetic coil to change the magnetic field passing through the brake disc and generate an induced current so that the brake disc is subjected to electromagnetic damping in the magnetic field, thereby decelerating the wheel.

[0024] In order to improve the reliability of the electromagnetic coil, the electromagnetic coil is composed of multiple parallel coils.

[0025] In order to prevent the magnetic field from having adverse effects on other systems outside this system, electromagnetic shielding materials are installed on both the hub assembly and the axle assembly.

[0026] In order to reduce the temperature rise of the brake disc in the wheel hub assembly caused by the thermal effect of the induced current, the brake disc is made of stacked metal sheets that are insulated from each other and have high resistivity. For example, the metal sheets are made of silicon steel, and metal sheets made of other materials can also be used. The higher resistivity can effectively reduce the size of the eddy current, thereby reducing the eddy current loss.

[0027] In order to provide a braking function for an aircraft when it is parked to prevent the aircraft from moving unexpectedly, the present invention also includes a moving disc and a static disc, the power control unit is connected to the static disc, the moving disc and the static disc are both mounted on the wheel axle assembly through bearings, the moving disc is driven by the spline on the wheel hub assembly and rotates with the wheel hub assembly, when the parking brake is working, the brake control unit receives the brake signal and controls the static disc actuator through the power control unit to drive the static disc to contact the moving disc to brake.

[0028] The present invention also includes a rotor assembly and an energy storage unit formed by winding wires. The rotor assembly is installed on the wheel hub for cutting the magnetic field generated by the electromagnetic coil. The rotor assembly is connected to the power control unit. The energy storage unit is connected to the power control unit, the brake control unit and the aircraft power system. The power control unit converts the current generated in the rotor assembly into electrical energy suitable for storage and stores it in the energy storage unit. The energy storage unit supplies power to the brake control unit and the aircraft power system, and the energy storage unit also receives power provided by the aircraft power system.

[0029] The brake disc (brake assembly), electromagnetic coil (electromagnetic coil assembly), power control unit (power control assembly), brake control unit (brake control assembly), wheel speed sensor, temperature sensor and energy storage unit (energy storage assembly) constitute a normal brake module; the dynamic disc (dynamic disc assembly), static disc (static disc assembly), energy storage unit (energy storage assembly), brake control unit (brake control assembly) and power control unit (power control assembly) constitute a parking brake module; the rotor assembly, electromagnetic coil (electromagnetic coil assembly), brake control unit (brake control assembly), power control unit (power control assembly) and energy storage unit (energy storage assembly) constitute a brake energy recovery and utilization module.

[0030] The normal brake module is used to brake the aircraft wheels when the aircraft is in motion. During normal braking, the electromagnetic coil installed on the wheel axle assembly generates a changing electromagnetic field. The brake control unit controls the magnitude, direction and frequency of the current in the electromagnetic coil through the power control unit. The brake control unit comprehensively analyzes parameters such as the wheel speed and the temperature of the brake disc installed on the hub assembly to generate a control signal for the power control unit. The power control unit adjusts the intensity and direction of the electromagnetic field generated by the electromagnetic coil on the wheel axle assembly. The brake disc on the hub assembly rotates continuously relative to the wheel axle, and the magnetic field through the brake disc changes continuously and generates an induced current due to electromagnetic induction. The presence of the induced current in the brake disc causes the brake disc to be electromagnetically damped in the magnetic field, thereby causing the wheel to slow down.

[0031] When the aircraft needs to brake normally during movement, the brake control unit receives input signals and controls the voltage, current and other parameters of the electromagnetic coil through the power control unit. Due to the presence of current, the electromagnetic coil generates an electromagnetic field, and the strength and direction of the electromagnetic field are determined by the current in the electromagnetic coil. When the aircraft moves, the brake disc rotates relative to the aircraft with the wheel and generates an induced current. The magnetic field generated by the electromagnetic coil generates a braking force that hinders the brake disc and slows down the wheel. The temperature sensor installed on the hub assembly measures the brake disc and transmits the temperature parameter to the brake control unit. The wheel speed sensor installed on the hub assembly measures the wheel speed and transmits the speed signal to the brake control unit. At the same time, the brake control unit also receives the power signal from the power control unit. The brake control unit adjusts the size of the brake force through the power signal in the electromagnetic coil according to the temperature of the brake disc, the wheel speed and the power signal of the power control unit until the aircraft stops moving. In order to improve the reliability of the system of the present invention, the power supply of the normal brake module comes directly from the energy storage unit in the energy recovery module of the system.

[0032] The parking brake module provides a braking function when the aircraft is parked to prevent the aircraft from accidentally sliding. When the aircraft is stationary and the parking brake is working, the brake control unit drives the static disc installed on the axle assembly through the actuator, and the static disc contacts the dynamic disc installed on the axle assembly to generate parking brake force.

[0033] The brake energy recovery module is used to recover and utilize the electrical energy generated when the wheels are braked. When the wheels are braked, the electromagnetic field generated by the electromagnetic coil of the rotor assembly cutting the wheel axle installed on the hub assembly generates an induced electromotive force, which generates an induced current in a closed loop. The induced current passes through the power control unit via a wire to store the electrical energy in the energy storage unit in the energy recovery module. The energy in the energy storage unit can provide power to the aircraft power system through the power control unit, and can also provide power to the aircraft wheel brake system. At the same time, the energy storage unit also receives power provided by the aircraft power system.

[0034] The above embodiments are merely illustrative of the principles and effects of the present invention, and are not intended to limit the present invention. Anyone familiar with the technology may modify or change the above embodiments without violating the spirit and scope of the present invention. Therefore, all equivalent modifications or changes made by a person with ordinary knowledge in the technical field without departing from the spirit and technical ideas disclosed by the present invention shall still be covered by the claims of the present invention.

Claims

1. An aircraft wheel brake system based on electric braking, characterized in that: The invention comprises a brake disc installed on a wheel hub assembly and rotating with the wheel, an electromagnetic coil installed on an axle assembly, a power control unit, a brake control unit, a wheel speed sensor installed on the wheel hub assembly for measuring the wheel speed, and a temperature sensor installed on the wheel hub assembly for measuring the brake disc temperature. The brake control unit is respectively connected to the electromagnetic coil, the power control unit, the wheel speed sensor and the temperature sensor. The power control unit is connected to the electromagnetic coil. When the aircraft brakes normally, the brake control unit sends a control signal to the power control unit according to the brake disc temperature and the wheel speed. After receiving the control signal, the power control unit adjusts the electromagnetic field generated by the electromagnetic coil to change the magnetic field passing through the brake disc and generate an induced current so that the brake disc is subjected to electromagnetic damping in the magnetic field, thereby decelerating the wheel.

2. The aircraft wheel brake system based on electric braking according to claim 1, characterized in that: The electromagnetic coil is composed of a plurality of parallel coils.

3. The aircraft wheel brake system based on electric braking according to claim 2, characterized in that: Electromagnetic shielding materials are installed on both the hub assembly and the axle assembly.

4. The aircraft wheel brake system based on electric braking according to claim 3, characterized in that: The brake disc is formed by stacking mutually insulated metal sheets with high resistivity.

5. The aircraft wheel brake system based on electric braking according to claim 4, characterized in that: The aircraft wheel brake system includes a moving disc and a static disc, the power control unit is connected to the static disc, the moving disc and the static disc are both mounted on the wheel axle assembly through bearings, the moving disc is driven by the spline on the wheel hub assembly and rotates with the wheel hub assembly, when the parking brake is working, the brake control unit receives the brake signal and controls the static disc actuator through the power control unit to drive the static disc to contact the moving disc to brake.

6. The aircraft wheel brake system based on electric braking according to claim 5, characterized in that: The aircraft wheel brake system includes a rotor assembly formed by winding wires and an energy storage unit. The rotor assembly is installed on the wheel hub to cut the magnetic field generated by the electromagnetic coil. The rotor assembly is connected to the power control unit. The energy storage unit is connected to the power control unit, the brake control unit and the aircraft power system. The power control unit converts the current generated in the rotor assembly into electrical energy suitable for storage and stores it in the energy storage unit. The energy storage unit supplies power to the brake control unit and the aircraft power system, and the energy storage unit also receives power provided by the aircraft power system.

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