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Brake system architecture for aircraft

A braking system and aircraft technology, applied in the direction of aircraft braking arrangement, braking actuator, brake, etc., can solve the problem that the filter circuit increases the weight, complexity and cost of the computer, and increases the weight, complexity and cost of the braking system. And other issues

Active Publication Date: 2021-07-06
SAFRAN LANDING SYSTEMS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The filtering circuit increases the weight, complexity and cost of the computer 3, and thus the braking system,

Method used

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  • Brake system architecture for aircraft
  • Brake system architecture for aircraft
  • Brake system architecture for aircraft

Examples

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Embodiment Construction

[0023] In this example, the invention is implemented on an aircraft with multiple main landing gears, each carrying multiple "brake" wheels, that is, multiple wheels each equipped with a brake for braking the aircraft. wheel. The description refers to a single braked wheel, but the invention naturally applies in the same way to all or part of braked wheels of an aircraft.

[0024] refer to figure 2 , the brake system architecture for an aircraft in the first embodiment of the present invention includes a brake 100 for braking wheels of an aircraft, a computer 101 and a junction box 102 .

[0025] Brake 100 includes four electromechanical brake actuators 103 ( figure 2 Only two electromechanical actuators 103 are shown in .

[0026] The computer 101 integrated in the avionics network is located in a cabin located in the fuselage of the aircraft.

[0027] The junction box 102 sits on the landing gear next to the brakes. In this example, junction box 102 includes electrica...

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PUM

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Abstract

A braking system architecture for an aircraft comprising: a brake (100) comprising friction members and an electromechanical actuator (103) for applying a braking torque on a wheel, seated in the fuselage of the aircraft and a computer (101) arranged to generate a first control signal; and a junction box (102) located on the landing gear, the junction box being connected to the computer and the electromechanical actuator, the junction box being arranged to receive the first Control signals, the junction box comprising electrical processor means arranged to use the first control signal to generate a second control signal for application to the electromechanical actuator for controlling the electromechanical actuator.

Description

technical field [0001] The invention relates to the field of braking system architectures for aircraft. Background technique [0002] refer to figure 1 , a known centralized architecture for electric aircraft braking systems comprises a plurality of brakes 1 each for braking a wheel of the aircraft's landing gear. [0003] Each brake 1 has four electromechanical brake actuators 2 which are grouped together in two different groups of two electromechanical actuators 2 . [0004] The two electromechanical actuators 2 in each different group are connected to the same computer 3 situated in the fuselage of the aircraft above the landing gear. [0005] The motor of each electromechanical actuator 2 receives three-phase power from a computer 3 to which the electromechanical actuator 2 is connected, and each electromechanical actuator 2 will servo control the measurement of a parameter (e.g., the angular position of the motor's rotor measurement) to the computer 3. The computer ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C25/42
CPCB64C25/44B60T8/1703B60T13/741B60T8/172B60T8/325F16D65/18F16D2121/24
Inventor B·戈耶兹D·恩夫罗伊O·弗雷
Owner SAFRAN LANDING SYSTEMS