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

A control system and vehicle technology, applied in the aerospace field, can solve problems such as ignoring the coupling effect of guidance and attitude control systems, and achieve the effects of ensuring mission requirements, enhancing performance, and improving control accuracy

Active Publication Date: 2021-06-22
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Abstract
  • Description
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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

Method used

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

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Embodiment Construction

[0058] In order to enable those skilled in the art to better understand the technical solutions of the present invention, the present invention will be further described in detail below in conjunction with specific embodiments.

[0059] The embodiment of the present invention provides a robust fault-tolerant guidance control system and a working system for the re-entry section of a reusable vehicle. This embodiment uses the Horus-2B model of the German MBB company as the research object.

[0060] Firstly, the twelve state equations of the reusable vehicle under the spherical earth are established, and its specific expression is as follows:

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[0073] Among them, h, θ, φ, V, γ and ψ represent the aircraft altitude, sub-satellite point longitude, sub-satellite point latitude, speed, track inclination and track azimuth, respectively, Ω=[α β ...

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Abstract

The invention discloses a robust fault-tolerant guidance control 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 Uncertainty problems, with good robust fault tolerance and control accuracy. 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...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05D1/08
CPCG05D1/0808
Inventor 林海兵都延丽刘武项凯张鹏
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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