Reusable vehicle reentry section robust fault-tolerant guidance system and working method

Abstract

The invention discloses a reusable vehicle reentry section robust fault-tolerant guidance system and a working method, relates to the technical field of aerospace, can avoid the problems of partial failure, saturation and uncertainty of an actuator control surface in a reusable vehicle reentry gliding process, and has good robust fault-tolerant performance and control precision. According to the system and method, a nonlinear disturbance observer of an attitude angle loop and an angular rate loop and an improved prediction correction guidance law are adopted, the observer is based on the principle of a fast arc tangent tracking differentiator, and the prediction correction guidance law introduces a gain compensation term into a quasi-balanced gliding condition. Besides, an anti-saturationauxiliary structure suitable for a multiple-input-multiple-output system is adopted, variables in the auxiliary structure are introduced into a backstepping method to design a robust fault-tolerant control strategy, and finally closed-loop stability of the system is guaranteed through a Lyapunov method.

Description

technical field [0001] The invention relates to the field of aerospace technology, in particular to a robust fault-tolerant guidance 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 use of ...

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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