Front wheel turning anti-swing system with medium speed correction function

Abstract

The invention discloses a front wheel turning anti-swing system with a medium speed correction function. The system comprises an instruction sensor, a hydraulic valve, a turning actuator, a feedback sensor and a front wheel turning control box. The system is normally at an anti-swing state; the hydraulic valve is at a power-off state, and when a front airplane wheel sways, oil is forced to flow the other cavity from one cavity of the turning actuator through a two-way damping valve of the hydraulic valve; when a nose landing gear of an airplane is put down and a power switch is connected, an on-plane power supply supplies power for the front wheel turning control box, and the front wheel turning control box automatically controls the system to be switched into a turning state from the anti-swing state when receiving the instruction value of the instruction sensor. The medium speed correction function of the front wheel turning anti-swing system is fulfilled, the maximum autonomous manipulation ability of a pilot is rendered under the premise of ensuring the manipulation safety of the airplane, and the ground maneuver performance of the airplane is improved; automatic switching of the system states and gain scheduling manipulation of turning are realized, the manipulation load of the pilot is decreased, and man-machine comfort is enhanced.

Description

technical field [0001] The invention relates to an anti-sway system, in particular to a front wheel turning anti-sway system with a medium-speed deviation correction function. Background technique [0002] Front wheel direction control technology is the core technology of aircraft ground control. It can improve the service life of brakes, correct the course of aircraft in anti-crosswind take-off and landing, and prevent tire accidents. It has incomparable excellence in reducing aircraft take-off and landing accidents. Effect. At present, the anti-swing system of the front wheel of the aircraft mostly adopts the fly-by-wire control system. The fly-by-wire control is controlled by the pilot in the cockpit by manipulating the switch, transmitting the control command through the electric wire, and processing the transmitted electric signal through the control control box to control the control action. A booster (hydraulic booster) telescopically deflects the front wheels. Sinc...

AI Technical Summary

Problems solved by technology

According to the kinematics and stability analysis of the aircraft's ground control, the deflection angle of the aircraft's front wheels is too large, which may cause the aircraft to overturn around the line connecting the ground contact points of the front wheels and one side of the main wheel, and cause the aircraft to lose control ability

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