System and method for aircraft ground roll correction control based on braking force redistribution

Abstract

The invention belongs to the field of large-scale aircraft braking, and particularly relates to an aircraft ground roll correction control system and method based on braking force redistribution. The control structure and the distribution control structure of the lower layer, wherein the upper layer control structure is a nonlinear ground sliding dynamic model for the controlled aircraft, and the designed motion controller, and the lower layer structure is the reconfiguration and redistribution control of the wheel braking force to ensure that each wheel Obtain the optimal braking force distribution; the double-layer controller performs control calculation according to the obtained aircraft motion parameters, obtains the differential braking torque of each main engine wheel on both sides, and at the same time outputs the control command to the braking actuator of the corresponding wheel, and the brake is executed According to the control command, the mechanism independently performs differential braking on each wheel, so as to realize the deviation correction control when the aircraft is sliding on the ground, and ensure the stability and safety of the aircraft landing.

Description

technical field [0001] The invention belongs to the field of large-scale aircraft braking, and in particular relates to an aircraft ground run deviation correction control system and method based on braking force redistribution. Background technique [0002] Under the rigid demand of transportation, the aviation industry has developed rapidly, the application of aircraft has become more extensive, and aviation accidents have become more frequent. According to the authoritative statistics of the Boeing Company, more than half of the aircraft accidents occurred during the landing and landing braking process of the aircraft. Research on the brake control system to ensure the safety of the aircraft landing and landing has become a hot spot. [0003] The forces on the landing and rolling of the aircraft are relatively complex and non-linear. The complex force factors can easily lead to asymmetrical changes in the loads on the main wheels on both sides of the aircraft, which will ...

AI Technical Summary

Problems solved by technology

[0006] Judging from the published invention patents of aircraft sliding deviation correction control, the method mainly adopts the passive wheel-to-wheel cross protection control strategy, which will increase the braking distance. In terms of application objects, it is mainly aimed at single For small aircraft with wheel-train landing gear structures, these methods cannot meet the aircraft control requirements of large multi-wheel-train landing gear mechanisms

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