Robust Fault Tolerant Guidance Control System and Working Method for Re-entry Section of Reusable Vehicle

Abstract

The invention discloses a robust fault-tolerant guidance system and a working method for the re-entry section of a reusable vehicle, relates to the field of aerospace technology, and can avoid partial failure, saturation, and failure of the actuator rudder surface during the re-entry gliding process of the reusable vehicle. It is a deterministic problem with good robust fault tolerance and control precision. The present invention adopts the nonlinear disturbance observer of the attitude angle loop and the angular rate loop and the improved predictive correction guidance law. The observer is based on the principle of the fast arctangent tracking differentiator, and the predictive correction guidance law introduces the Gain compensation term. In addition, the present invention also adopts an anti-saturation auxiliary structure suitable for multiple input and multiple output systems, and designs a robust fault-tolerant control strategy by introducing the variables in the auxiliary structure into the backstepping method, and finally ensures the closed loop of the system through the Lyapunov method Stablize.

Description

technical field [0001] The invention relates to the field of aerospace technology, in particular to a robust fault-tolerant guidance control system and a working method of a re-entry section of a reusable vehicle. Background technique [0002] Reusable Launch Vehicle (RLV) is cheap, safe, fast, and highly maneuverable, so it has broad application prospects in civil and military fields. It can not only be used as a reusable space-to-ground load transport It can also be used as an air-space combat weapon platform to complete combat tasks such as high-point reconnaissance and precision strikes. However, the re-entry of reusable vehicles has the characteristics of complex flight environment, large flight envelope, flight mission change, strong coupling and strong nonlinearity, which increases the difficulty of joint design of guidance and control. If offline trajectory planning is adopted, it will not be able to It is well adapted to the needs of flight mission changes, and the...

AI Technical Summary

Problems solved by technology

In view of the above problems, it is assumed that the attitude control system has a sufficiently fast response speed, and the coupling effect between the guidance and attitude control system is ignored

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