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.

Inactive Publication Date: 2015-09-30
BEIJING INSTITUTE OF TECHNOLOGYGY
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  • Abstract
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  • Claims
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Problems solved by technology

However, it should be pointed out that the use of boundary layer debounce technology will lead to a decrease in control accuracy. Therefore, some scholars have introduced the integral term of the error into the traditional proportional-derivative (PD) sliding mode to form a proportional-integral-derivative ( PID) type sliding mode function has achieved the purpose of improving the control accuracy
At this time, another problem has to be considered, that is, the introduction of the integral term will lead to the problem of overshooting of the system response, and in severe cases, the system will appear integral saturation.

Method used

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

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Embodiment 1

[0091] Using the hypersonic model of the Winged-Cone configuration announced by NASA as the simulation platform, the numerical simulation is carried out for its re-entry flight process. The simulation conditions are: the initial altitude is 30km, the initial flight speed is 2800m / s, and the initial attitude angle y(0)=[0°,1°,0°] T , the attitude angle given command y c =[3°,0°,5°] T , initial attitude angular velocity p(0)=q(0)=r(0)=0deg / s. The deflection angle of the rudder surface is limited to ±30°.

[0092] Since the flight conditions of the re-entry vehicle vary widely, and often have uncertainties such as aerodynamic parameter perturbation, for the problem of attitude control of the re-entry vehicle, it is necessary not only to test the control performance under nominal conditions, but also to test the control performance of the controller in the environment. In the case of drastic changes in parameters and strong uncertainties in the system, whether robust and precis...

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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.

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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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B13/04
Inventor 盛永智金震刘向东
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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