A hypersonic vehicle re-entry attitude fault-tolerant control method

A hypersonic, fault-tolerant control technology, applied in attitude control and other directions, can solve catastrophic, economic loss and other problems, and achieve the effect of ensuring stability

Active Publication Date: 2017-10-31
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

Once a failure occurs, it will often cause economic losses or even catastrophic consequences

Method used

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  • A hypersonic vehicle re-entry attitude fault-tolerant control method
  • A hypersonic vehicle re-entry attitude fault-tolerant control method
  • A hypersonic vehicle re-entry attitude fault-tolerant control method

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Embodiment Construction

[0058] In order to facilitate the understanding of those skilled in the art, the present invention will be further described below in conjunction with the embodiments and accompanying drawings, and the contents mentioned in the embodiments are not intended to limit the present invention.

[0059] refer to Figures 1 to 4D As shown, a hypersonic vehicle re-entry attitude fault-tolerant control method of the present invention, firstly, the controller designed by Backstepping is used to obtain the desired control torque:

[0060] Define the state variable x 1 =Ω,x 2 = ω, select the reentry attitude model

[0061]

[0062]

[0063] y=x 1

[0064] Among them, h 1 (x 1 )=R(·), h 2 (x 2 )=-J -1 ΞJω,h 3 =J -1 .

[0065] Step 1: Define z 1 =x 1 -Ω d , then z 1 Differentiation of :

[0066]

[0067] where x 2 As the virtual control quantity, choose the Lyapunov function The derivative is:

[0068]

[0069] Design Virtual Control Quantities make

[0...

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Abstract

The invention discloses a hypersonic vehicle reentry attitude fault-tolerant control method. Firstly, the backstepping method is used to design the controller to obtain the desired control torque; The control torque is distributed to the actuators, with the pneumatic rudder surface as the first actuator and the RCS as the second actuator; when the control torque provided by the pneumatic rudder surface is insufficient, the RCS is activated. A fault-tolerant control strategy is designed to make the closed-loop system stable, and it is verified in simulation.

Description

technical field [0001] The invention belongs to the technical field of automatic control, and in particular relates to a hypersonic vehicle reentry attitude fault-tolerant control method which integrates an aerodynamic rudder surface and an RCS. Background technique [0002] Compared with ordinary aircraft, the unique characteristics of hypersonic aircraft such as high-order nonlinearity, strong coupling, and uncertainty, as well as the complex and changeable external flight environment have brought challenges to the design of the controller. The purpose of re-entry control is to design an attitude control strategy so that the attitude angle can track the reference command and ensure the stability of the entire aircraft control system. [0003] In the initial stage of reentry of a hypersonic vehicle, due to the thin air, low dynamic pressure and low efficiency of aerodynamic control surfaces, it is necessary to use a reaction control system (reaction control system, RCS) to ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05D1/08
Inventor 齐瑞云钱佳淞姜斌何晶晶
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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