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Aircraft electric braking system

一种飞行器、电动制动的技术，应用在制动控制系统、飞机制动安排、制动器等方向，能够解决制动控制丧失、丧失等问题，达到减轻重量、增强可靠性、节约成本的效果

Active Publication Date: 2015-06-03
AIRBUS OPERATIONS GMBH
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AI Technical Summary

Problems solved by technology

Thus there is the potential for several EMACs to fail simultaneously resulting in partial or total loss of brake control, which is undesirable

Method used

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  • Aircraft electric braking system
  • Aircraft electric braking system
  • Aircraft electric braking system

Examples

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Embodiment Construction

[0044] exist figure 1 The illustrated first embodiment electric aircraft braking system 100 is configured for use with an aircraft having two braked main landing gear, one of which is on either side of the centerline of the aircraft. However, it will be appreciated that the invention described herein relates to any aircraft configuration having braked wheels, including aircraft having more than two main landing gear and / or braked nose landing gear. The braking system 100 features fully distributed avionics.

[0045] Braking system 100 includes aircraft cockpit controls and avionics 110, which communicate via data buses 111, 112 and routers 131 to 138 with "fully intelligent" electromechanical brake actuators (EMA) 151a-d, 152a-d , 153a-d, and 154a-d (described in detail below), the "fully intelligent" electromechanical brake actuators (EMA) 151a-d, 152a-d, 153a-d, and 154a-d communicate with the wheel and brake sets 161 to 164 are associated. In this example, there are four...

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PUM

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Abstract

An electrically actuated braking system for an aircraft, comprising: an electro-mechanical brake actuator (EMAbrake) proximate a wheel of the aircraft, the EMAbrake including a motor; an electro-mechanical actuator controller (EMAC) including a motor controller for generating a drive signal for the EMAbrake; and a braking control unit for generating a braking force command signal for the EMAC; wherein the braking control unit and the EMAC are disposed together with the EMAbrake in a common line replaceable unit (LRU).

Description

technical field [0001] The invention relates to an electric braking system for an aircraft. Background technique [0002] Electric systems are gradually replacing hydraulic systems on many commercial and military aircraft. Current "brake-by-wire" aircraft systems may have an overall centralized architecture where pilot inputs are interpreted and command and monitoring signals are communicated via a data bus as analog / discrete signals to the Brake Control Unit (BCU). An exemplary centralized architecture is described in US 2008 / 0030069A1. [0003] The BCU interprets commands from the aircraft cockpit controls and avionics, and calculates braking force commands for each actuated landing gear wheel of the aircraft. This can include quick cycle skid control. [0004] Each brake wheel will have at least one electromechanical actuator (EMA) for providing a clamping force to the brakes for that wheel, which brake wheel converts the clamping force into a braking torque. An elect...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C25/42B60T13/74
CPCB60T8/1703B60T2270/413B64C25/44B64C25/46B60T8/325B60T13/741B60T2270/404
Inventor 乔治·约尔扎尼季斯约翰·里斯
Owner AIRBUS OPERATIONS GMBH
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