Robust control and distribution method applied to fault-tolerant flight control system

Abstract

The invention relates to a robust control and distribution method applied to a fault-tolerant flight control system and belongs to the technical field of aerospace fault-tolerant flight control. The robust control and distribution method includes linearizing an aircraft model to generate a control efficiency matrix, determining efficiency coefficient of each rudder side influencing three-axis posture control of the aircraft, building a fault model, converting fault parameter estimation problems into linear regression problems so as to estimate fault parameters by a least square linear regression method, calculating uncertainties of estimated fault parameter results corresponding to each rudder side by a fault projection method and weighting and smoothing; considering difference of the uncertainties of the fault parameters corresponding to the rudder sides, solving the problem about optimization of the minimum control distribution error under the worst condition, controlling and distributing robust, equivalently converting the problem of optimization into the problem of convex optimization, and solving to obtain the robust control and distribution results by a primal dual interior point method. Robustness of control and distribution is improved.

Description

technical field [0001] The invention belongs to the technical field of aerospace fault-tolerant flight control, in particular to a robust control distribution method applied to a fault-tolerant flight control system. Background technique [0002] In recent years, with the continuous improvement of aircraft safety and control performance requirements, fault-tolerant flight control technology has been paid more and more attention. The aircraft relies on the flight control system to achieve stable flight. The traditional flight control system can only work normally when the aircraft is in good condition, and cannot work when the rudder surface that controls the aircraft's movement fails. The fault-tolerant flight control system can solve the above problems to a certain extent, so that the aircraft can still fly stably when the rudder surface fails. The earlier fault-tolerant flight control systems used the fault isolation method to isolate the failed rudder surfaces and no lon...

AI Technical Summary

Problems solved by technology

[0026] The purpose of the present invention is to solve the problem that inaccurate fault parameter estimation affects the accuracy of control allocation in an active fault-tolerant flight control system, and proposes a robust control allocation method applied to a fault-tolerant flight control system

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