Nose-wheel steering system of aircraft

A front wheel turning and aircraft technology, applied in the field of aeronautical engineering, can solve the problems of large size, unstable turning control, poor scalability, etc., and achieve the effect of small size, high safety and compact structure

Inactive Publication Date: 2014-01-22
HARBIN
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

At present, most of the aircraft in our country adopt the analog fly-by-wire front wheel steering system, which has the disadvantages of large volume, poor scalability, and unstable turning control.

Method used

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  • Nose-wheel steering system of aircraft
  • Nose-wheel steering system of aircraft
  • Nose-wheel steering system of aircraft

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Embodiment Construction

[0017] The present invention is a kind of digital fly-by-wire front wheel steering system, which will be described in further detail below.

[0018] Functional block diagram and composition connection diagram of the present invention are respectively as figure 1 and figure 2 shown. The system includes: a turning control box 1, a command sensor 2, a combined hydraulic valve 3, a turning actuator 4, a feedback sensor 5 and auxiliary components such as cable connecting lines and hydraulic pipelines.

[0019] The turning control box 1 is fixed in the electrical equipment cabin of the aircraft with bolts, and is connected with the command sensor 2, the combined hydraulic valve 3 and the feedback sensor 5 through cable lines, and introduces power switch, turning button and wheel load switch signals. One end of the command sensor 2 is fixed under the floor of the aircraft cockpit with bolts, and the other end is hinged with the pedals by bolts to ensure that the command sensor and...

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Abstract

The invention belongs to the field of aircraft engineering, and provides a nose-wheel steering system of an aircraft. According to the nose-wheel steering system, a steering control box is connected with an instruction sensor, a combined hydraulic valve and a feedback sensor through cables; one end of the instruction sensor is fixedly arranged below a floor of a cockpit of the aircraft by using bolts, and the other end of the instruction sensor is hinged to a foot pedal through bolts; the combined hydraulic valve is fixedly arranged on a bulkhead plate of a nose landing gear through bolts; the feedback sensor is arranged on a steering actuator; one end of the feedback sensor is fixedly arranged on a steering actuator shell through a hoop, and the other end of the feedback sensor is connected with a piston rod of the steering actuator through a clamping piece; the steering actuator is arranged on the nose landing gear of the aircraft; a piston rod of the steering actuator is hinged to a rotary sleeve of the nose landing gear through a joint bearing and a bolt. The nose-wheel steering system of the aircraft is used for steering at a low-speed stage and swing prevention at a high-speed stage during sliding of the aircraft, and has good operation flexibility and anti-swing stability.

Description

technical field [0001] The invention belongs to the field of aeronautical engineering and relates to an aircraft nose wheel steering system. Background technique [0002] The nose wheel steering system is widely used in aircraft design as a device to improve aircraft taxiing maneuverability and landing safety. The front wheel steering system has experienced mechanical, mechanical-hydraulic, analog fly-by-wire, digital fly-by-wire and other stages in the development process. At present, most of the aircraft in our country adopt the analog fly-by-wire front wheel steering system, which has the disadvantages of large volume, poor scalability, and unstable turning control. Contents of the invention [0003] The technical problem to be solved by the present invention: the purpose of the present invention is to provide a digital fly-by-wire aircraft nose wheel steering system, which is used for directional control in the low-speed taxiing phase of the aircraft, and provides the...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C25/50B64C25/34
Inventor 王永和黄刚徐继红季茂龄刁飞萌宋宪龙刘双
Owner HARBIN
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