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Aircraft electronic brake system and braking method using automatic brake switch

A technology of automatic braking and braking system, which is applied in the direction of aircraft braking arrangement, braking transmission device, brake, etc., can solve the problems of difficulty in troubleshooting and positioning, low reliability of use, potential safety hazards, etc., and improve the utilization of airport runways. efficiency and equipment utilization, high reliability, flexible and convenient use

Active Publication Date: 2021-01-05
XIAN AVIATION BRAKE TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] In order to overcome the shortcomings of the existing braking system, such as complex automatic braking design and configuration, frequent failures, difficult troubleshooting and positioning, low reliability, multiple logical relationships at the first level and even potential safety hazards, the present invention proposes an automatic Aircraft fly-by-wire braking system and braking method for brake switch

Method used

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  • Aircraft electronic brake system and braking method using automatic brake switch
  • Aircraft electronic brake system and braking method using automatic brake switch

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Embodiment 1

[0035] see figure 1 . The front landing gear wheels of modern aircraft generally do not have brakes, and brake devices are equipped on the wheels of the two main landing gears. The two aircraft main landing gears are usually arranged symmetrically on both sides of the aircraft fuselage. In this embodiment, one of the main landing gear and one wheel is installed as an example to illustrate an aircraft fly-by-wire hydraulic braking system with automatic braking capability.

[0036] This embodiment is a first-level automatic brake; the automatic brake anti-skid valve adopts a shared anti-skid valve, and an electro-hydraulic servo valve is used as the anti-skid valve.

[0037] In this embodiment, the braking command sensor 1, the control box 3, the electro-hydraulic servo valve 2 and the speed sensor 4 form a conventional braking system. The control box 3, the electro-hydraulic servo valve 2 and the speed sensor 4 form a conventional anti-skid control system.

[0038] This emb...

Embodiment 2

[0062] see figure 2 . This embodiment is an aircraft fly-by-wire hydraulic braking system with automatic braking capability. The difference from the technical solution in Embodiment 1 is that the aircraft fly-by-wire hydraulic braking system of this embodiment is a two-stage automatic braking system.

[0063]This embodiment includes a brake command sensor 1 , a control box 3 , an electro-hydraulic servo valve 2 , a first automatic brake switch K1 , a second automatic brake switch K2 , a throttle 7 , a one-way valve 6 and a speed sensor 4 . The brake command sensor 1, the control box 3, the electro-hydraulic servo valve 2 and the speed sensor 4 form a conventional brake system. The control box 3, the electro-hydraulic servo valve 2 and the speed sensor 4 form a conventional anti-skid control system. Automatic brake switch K, electro-hydraulic servo valve 2, throttle 7, check valve 6, speed sensor 4 and control box 3 form an automatic brake system. Electro-hydraulic servo va...

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Abstract

The invention discloses an aircraft telex braking system using an automatic brake switch and a braking method. A conventional braking system is formed by a brake instruction sensor, a control box, anelectro-hydraulic servo valve and a speed sensor. A conventional antiskid control system is formed by a control box, an electro-hydraulic servo valve and a speed sensor. An automatic braking system iscomposed of an automatic brake switch K or a first automatic brake switch K1, a second automatic brake switch K2, an electro-hydraulic servo valve, a throttle device, a one-way valve, a speed sensorand a control box. The aircraft telex braking system conducts braking at 75-125% of the maximum braking pressure of a normal braking system, overspeed rising of the automatic braking initial hydraulicpressure is inhibited through a throttling device or the control box, the combined torque provided by a runway is fully and maximally facilitated, the landing sliding distance is shortened by about 35% compared with conventional braking, taking-off and landing safety of the aircraft is ensured, the airport runway utilization and equipment utilization are improved, and the economic, social and military benefits are obvious.

Description

technical field [0001] The invention relates to an aircraft wheel fly-by-wire braking system, in particular to an aircraft fly-by-wire braking system with automatic braking capability. Background technique [0002] The aircraft wheel brake system is a component of modern aircraft landing gear, and is the basic guarantee equipment for the safe operation of aircraft take-off, landing roll and ground taxi control. Prevent punctured tires. Experimental research and use have shown that under certain conditions, the use of automatic braking can effectively shorten the landing roll distance of the aircraft. Automatic braking has also been long-awaited to relieve the driver of the load during safety-critical landings. At present, general aircraft do not have the ability to automatically brake, including aircraft using fly-by-wire brakes. When braking, the driver needs to step on the brake pedal or control the brake handle to manipulate the brake valve or brake command sensor. Only...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C25/44B60T13/74
CPCB60T13/74B64C25/44
Inventor 何永乐何文静丛晨
Owner XIAN AVIATION BRAKE TECH
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