Decentralized electric brake system

• US 9,227,608 B2
• Filed: 08/12/2009
• Issued: 01/05/2016
• Est. Priority Date: 08/12/2009
• Status: Active Grant

• Current Assignee: Meggitt Aircraft Braking Systems Incorporated (Meggitt PLC)
• Original Assignee: Meggitt Aircraft Braking Systems Incorporated (Meggitt PLC)
• Inventors: Hill, James L., Burkhalter, Kurt
• Primary Examiner(s): MUSTAFA, IMRAN K
• Application Number:
  US12/539,884
• Publication Number:
  US 20110040466A1
• Time in Patent Office: 2,337 Days
• Field of Search: 701/71
• US Class Current: 1/1
• CPC Class Codes: B60T 2270/402 Back-up
• CPC Class Codes: B60T 2270/413 Plausibility monitoring, cross check, redundancy
• CPC Class Codes: B60T 8/1703 for aircrafts
• CPC Class Codes: B60T 8/325 Systems specially adapted for aircraft
• CPC Class Codes: B60T 8/885 using electrical circuitry

Abstract

An electric aircraft brake control system has a plurality of wheel and brake assemblies, each having a wheel, wheel speed transducer, brake assembly and a brake actuator. Electromechanical control units are uniquely associated with and connected to certain of the wheel and brake assemblies, and each of the electromechanical control units is provided with an antiskid system as an integral portion thereof. Brake data concentrators are provided for receiving data corresponding to various aircraft operational parameters, including brake pedal position, and provide operational signals to the electromechanical control unit as a function thereof. A controller for emergency and park braking is connected to the electromechanical actuator controllers through one of the brake data concentrators to effect emergency braking action on the brake assemblies, such emergency braking action having incident antiskid control. The system allows for a redundency in brake control circuitry and operation, which increases the dispatchability of an associated aircraft by ensuring continued effective operation of the aircraft even in view of a failure of one of the redundant circuits or systems. A reduction in weight is also achieve by reducing lengthy cable runs.

Claims

1. An electric aircraft brake control system, comprising:

a plurality of wheel and brake assemblies, each assembly having a wheel, wheel speed transducer, brake assembly, and a brake actuator;

pairs of electromechanical control units uniquely associated with and connected to certain actuator controllers of said wheel and brake assemblies, said actuator controllers having antiskid systems as a part thereof connected to specific actuators of associated wheel and brake assemblies;

said actuator controllers configured independently of each other, such that a failure of any one or more controllers allows the remaining controllers to continue to operate unimpeded with antiskid capability such that the aircraft brake control system experiences only the partial loss of functionality associated with the failed controller or controllers to thereby ensure aircraft dispatchability; and

at least two brake data concentrators receiving data corresponding to various aircraft operational parameters, including brake pedal position, and providing operational signals to said electromechanical control units as a function thereof.

2. The electric aircraft brake control system according to claim 1, wherein said wheel speed transducer provide signals to said associated electromechanical control units corresponding to instantaneous wheel speed.

3. The electric aircraft brake control system according to claim 2, wherein each said electromechanical control unit comprises an electromechanical actuator controller connected and providing drive to an associated brake actuator.

4. The electric aircraft brake control system according to claim 3, wherein various of said electromechanical actuator controllers are connected to, and share wheel speed data with, each other.

5. The electric aircraft brake control system according to claim 3, further comprising a controller for emergency and park braking.

6. The electric aircraft brake control system according to claim 5, wherein said controller for emergency and park braking is connected to said electromechanical actuator controller through one of said brake data concentrators to effect emergency braking action on said brake assemblies, with antiskid control.

7. The electric aircraft brake control system according to claim 6, wherein said controller for emergency and park braking comprises a differential transformer for providing a pilot-controlled output signal.

8. The electric aircraft brake control system according to claim 5, wherein said electromechanical control units further comprise automatic braking control systems for associated wheel and brake assemblies.

9. The electric aircraft brake control system according to claim 8, wherein said electromechanical control units further comprise brake temperature monitoring systems, taken from the group of brake temperature and tire pressure, for associated wheel and brake assemblies.

10. The electric aircraft brake control system according to claim 5, wherein said electromechanical control units are in closer proximity to said associated wheel and brake assemblies than said brake data concentrators are to said wheel and brake assemblies.

11. An electric aircraft brake control system, comprising:

a plurality of wheel and brake assemblies, each assembly having a wheel, wheel speed transducer, brake assembly, and a brake actuator;

electromechanical control units uniquely associated with and connected to certain actuator controllers of said wheel and brake assemblies, said actuator controllers having antiskid systems as a part thereof connected to specific actuators of associated wheel and brake assemblies such that the failure of any control unit results in only the partial loss of functionality for the brake control system associated with the failed control unit;

first and second brake data concentrators receiving data corresponding to various aircraft operational parameters, including brake pedal position, and providing operational signals to said electromechanical control units as a function thereof; and

a controller for emergency and park braking connected to said electromechanical actuator controllers through one of said brake data concentrators to effect emergency braking action on said brake assemblies, with antiskid control.

12. The electric aircraft brake control system according to claim 11, wherein said controller for emergency and park braking comprises a variable transformer for effecting a pilot-controller output signal.

13. The electric aircraft brake control system according to claim 11, wherein said first brake data concentrator provides operations signals to said electromechanical control units during normal operation, and said second brake concentrator provides operational signals to said electromechanical control units upon failure of said first brake data concentrator and upon need of operator of said controller for emergency and park braking.

14. The electric aircraft brake control system according to claim 11, wherein said electromechanical control units contain redundant circuits and provide redundant connections with said wheel and brake assemblies.

15. The electric aircraft brake control system according to claim 11, wherein each said electromechanical control unit comprises a power generation circuit interconnected between an aircraft power supply source and an associated pair of motors of a brake actuator.

16. The electric aircraft brake control system according to claim 15, wherein each said power generation circuit comprises a pair of power supplies connected in series to the pair of motors.