基于Riccati方程的导弹自适应姿态控制

doi:10.3969/j.issn.1001-506X.2020.06.20

Abstract

Abstract:

Aimed at the nonlinear missile model with parameter uncertainties, a model reference adaptive state control method based on the state-dependent Riccati equation is proposed. Firstly, based on the standard model, a Riccati equation with the special form is established and its analytic solution is obtained. The suboptimal control law which is globally asymptotically stable is acquired. Then, in view of the inferior result caused by the parameter deviation between the real model and the standard model, the closed-loop system designed under the standard model is regarded as a reference model. An adaptive control law is designed to urge the real model to approach to the standard model, and guarantees that the tracking error and the identification error are bounded. Simulation results show that the control law designed can overcome the effect caused by parameter uncertainties and track the response of the reference model well.

Key words: state-dependent Riccati equation, analytic solution, parameter uncertainty, model reference adaptive control, missile attitude control

CLC Number:

TJ765.2

Zongxing LI, Rui ZHANG. Missile adaptive attitude control based on Riccati equation[J]. Systems Engineering and Electronics, 2020, 42(6): 1358-1365.

Figures/Tables 7

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References 21

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不确定参数	第1组	第2组
θ₁	1.2	1.2+0.07sin(3πt)
θ₂	0.8	0.8+0.05sin(6πt)
θ₃	1.15	1.15+0.04sin(3πt)
θ₄	0.85	0.85+0.06sin(6πt)
θ₅	0.8	0.8+0.025sin(6πt)
θ₆	0.82	0.82+0.035sin(3πt)
θ₇	1.19	1.19+0.03sin(6πt)
θ₈	1.22	1.22+0.06sin(3πt)

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Missile adaptive attitude control based on Riccati equation

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