Braking system for a dual landing gear aircraft

A braking system, landing gear technology, applied in the direction of aircraft braking arrangements, brakes, fluid pressure actuation devices, etc., can solve problems such as complexity, increased pilot workload, expensive redundancy and monitoring systems

Pending Publication Date: 2020-01-03
THE BOEING CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Failures in these conventional systems result in asymmetrical loss of brakes that apply braking only along one side of the aircraft
This results in increased pilot workload and may also hamper subsequent dispatch of the aircraft
These conventional systems also often include complex and expensive redundancy and monitoring systems

Method used

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  • Braking system for a dual landing gear aircraft
  • Braking system for a dual landing gear aircraft
  • Braking system for a dual landing gear aircraft

Examples

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Embodiment approach

[0066] Clause 1. A braking system (10) for a dual landing gear aircraft comprising a left landing gear and a right landing gear each having a forward inboard wheel and rear inner wheels and front outer wheels and rear outer wheels, said braking system comprising:

[0067] an outboard braking system control unit (20), the outboard braking system control unit including at least a first processing circuit (21) that generates a braking control signal responsive to pilot input to symmetrically control only braking of a first wheel pair comprising said front outer wheels (69) and a second wheel pair comprising only said rear outer wheels (69);

[0068] an inboard braking system control unit (30), the inboard braking system control unit including at least a second processing circuit (21), the second processing circuit generating a braking control signal responsive to the pilot input to symmetrically controlling the braking of a third wheel pair comprising only said front inner wheel...

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Abstract

The present invention provides a braking system for use with a dual landing gear aircraft. The braking system pairs outboard brake control into an outboard brake system control unit (BSCU) and inboardbrake control into a second inboard brake system control unit (BSCU). Each BSCU is designed with two independent control lanes in which the forward wheel set is paired in one control lane and the aftwheels are paired onto the other. Alternate braking is provided via an alternate brake module installed in a fore-aft wheel pairing.

Description

technical field [0001] The present disclosure relates generally to aircraft braking systems and, more particularly, to a braking pairing scheme for a dual landing gear aircraft that creates a direct and robust braking system. Background technique [0002] The aircraft may include a dual undercarriage architecture including multiple wheelsets. Each wheel set includes a plurality of wheels arranged in two or more inner wheels and two or more outer wheels. The wheels are also arranged as a front set of wheels closer to the front of the aircraft and a rear set of wheels towards the rear of the aircraft. [0003] The conventional braking system divides the aircraft into a left braking system and a right braking system. Failures in these conventional systems result in an asymmetrical loss in which the brakes apply braking only along one side of the aircraft. This results in increased pilot workload and may also hamper subsequent dispatch of the aircraft. These conventional sys...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C25/42B64C25/34
CPCB64C25/42B64C25/34B60T8/1703Y02T50/80B60T13/12B60T2270/40F15B13/028F15B13/0401F15B13/042F15B2211/3052
Inventor T·R·哈伯德D·T·山本
Owner THE BOEING CO
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