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Reentry vehicle full-order non-singular terminal sliding mode posture control method

A technology for re-entry aircraft and non-singular terminal, which is applied in the field of aircraft control and can solve the problem of singularity in the output of the terminal sliding mode controller.

Inactive Publication Date: 2015-09-30
BEIJING INSTITUTE OF TECHNOLOGYGY
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  • Summary
  • Abstract
  • Description
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AI Technical Summary

Problems solved by technology

However, there are still two main problems with the terminal sliding mode control method
First, the output of the terminal sliding mode controller will have a singular problem

Method used

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  • Reentry vehicle full-order non-singular terminal sliding mode posture control method
  • Reentry vehicle full-order non-singular terminal sliding mode posture control method
  • Reentry vehicle full-order non-singular terminal sliding mode posture control method

Examples

Experimental program
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Effect test

Embodiment 1

[0086] 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°.

[0087] 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 full-order non-singular terminal sliding mode posture control method, relates to a reentry vehicle full-order non-singular terminal sliding mode posture control method based on a robust differentiator, and belongs to the technical field of vehicle control. The method includes the steps: generating the state vector of a vehicle; building a mathematical model of a reentry vehicle; simplifying the model of the reentry vehicle by feedback linearization; giving command information yc=(alpha c, beta c and mu c) T of a progressive tracking system for posture angles alpha, beta and mu of the vehicle when external interference exists in the system and parameters are uncertain; controlling allocation to obtain a rudder reflection angle command delta=(delta e, delta a and delta r) T; inputting the obtained rudder reflection angle command to the vehicle and controlling the posture of the vehicle. Tracking errors can be converged into zero within limited time, singular problems of controller output can be avoided, measuring noise generated by a traditional differentiator is suppressed by estimating error second-order derivatives, and buffeting of control quantity is eliminated by boundary layer and low-pass filtering techniques.

Description

technical field [0001] The invention relates to a sliding mode attitude control method of a re-entry aircraft, in particular to a full-order non-singular terminal sliding mode attitude control method of a re-entry aircraft based on a robust differentiator, and belongs 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, it is critical to design a robust attitude controller that can suppress system nonlinearity, channel coupling and s...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D1/08
Inventor 盛永智金震刘向东
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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