Aircraft attitude fault-tolerant control method based on dynamic control redistribution

Abstract

The invention discloses an aircraft attitude fault-tolerant control method based on dynamic control redistribution. The method includes the steps that firstly, an attitude angle rate loop dynamic equation of a near-space aircraft X-33 is given, and a control surface jamming and damage fault model is established; then according to the control surface damage fault model of an attitude angle rate loop, a self-adaptive sliding-mode observer is designed; the attitude angle loop and the designed observer dynamic equation are combined, and an angle loop controller and an angular speed loop controller are designed. Accurate damage fault information, interference information and the like are not needed, the information is implied in the designed self-adaptive sliding-mode observer, the implicit information is fed back to a pseudo control law and online distribution algorithm LMI in real time, and then robust fault-tolerant control is achieved. Finally, the designed method is applied to attitude stability control and tracking control of the near-space aircraft under the control surface fault condition, flight attitude robust fault-tolerant control is achieved, and good control performance and effects are achieved.

Description

technical field [0001] The invention belongs to the technical field of near-space aircraft, and in particular relates to an aircraft attitude fault-tolerant control method based on dynamic control redistribution. Background technique [0002] In terms of aerodynamic layout design of modern aircraft, traditional ailerons, rudders, and elevators have been reasonably divided, and more new control surfaces have been added, such as pitch flaps, full-motion wingtips, elevons, canards, etc. This can greatly improve the reliability and security of the system. As we all know, the prerequisite for the realization of fault-tolerant control is that the system needs redundant control force, and the addition of various new control surfaces just lays the premise foundation for the research of fault-tolerant control. However, various new control surfaces added in the design not only improve the reliability of the system, but also increase the coupling degree of various control surfaces. Th...

AI Technical Summary

Problems solved by technology

[0005] The purpose of the embodiments of the present invention is to provide an aircraft attitude fault-tolerant control method based on dynamic control redistribution, aiming to solve the problem of poor fault-tolerant tracking performance under control surface damage in an uncertain flight control system with external interference

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