Reentry vehicle PID (proportion, integration and differentiation) type sliding mode posture control method based on self-adaptive fuzziness

A re-entry aircraft, adaptive fuzzy technology, applied in the field of aircraft control, can solve the problems of control accuracy reduction, system response overshoot, system integral saturation, etc.
CN104950671AInactive Publication Date: 2015-09-30BEIJING INSTITUTE OF TECHNOLOGYGY
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
BEIJING INSTITUTE OF TECHNOLOGYGY
Publication Date
2015-09-30
Estimated Expiration
Not applicable · inactive patent

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Abstract

The invention discloses a reentry vehicle PID (proportion, integration and differentiation) type sliding mode posture control method based on self-adaptive fuzziness, relates to a PID type sliding mode posture control method of reentry vehicles and belongs to the technical field of vehicle control. Aiming at parameter adjusting characteristics of a PID type sliding mode function, PID type sliding mode parameters are enabled to have time-variant characteristics, so that a system is ensured to output tracking instruction information quickly while the problems of system overshoot and control input saturation of the system are avoided. A global sliding mode algorithm is introduced to improve a PID type sliding mode dynamic equation, so that robustness of a conventional PD sliding mode is enhanced. By applying a self-adaptive fuzzy logic system, the system is ensured to output the tracking instruction information quickly, response overshoot and control input saturation of the system are avoided, tracking errors can be reduced, and robustness of the conventional PD sliding mode can be improved.
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Description

technical field

[0001] The invention relates to a PID type sliding mode attitude control method of a reentry aircraft, belonging to the technical field of aircraft control. Background technique

[0002] During the unpowered re-entry flight, the aircraft will experience changes from supersonic flight conditions to subsonic flight conditions, and the flight airspace is also large, environmental interference is serious, and there is coupling between channels, so this process will show serious abnormal linear characteristics. Not only that, but the aerodynamic characteristics of the aircraft cannot be accurately obtained. These factors have caused the attitude control of the aircraft to become extremely complicated. Therefore, a robust attitude controller that can suppress system nonlinearities, channel coupling, and uncertainties is critical.

[0003] The sliding mode control (Sliding Mode Control, SMC) method provides a systematic solution to the control problem of the model...

Claims

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