Finite-time attitude stabilization of an output-constrained rigid spacecraft

Jianjun Ma,Peng Li

doi:10.1177/1729881420907416

Abstract

This article concentrates on the study of finite-time attitude stabilization for a rigid spacecraft with output constraints. The dynamics of the spacecraft are expressed by modified Rodrigues parameters, so that the singularity of covariance matrix owing to quaternion’s redundancy is eliminated. Based on the backstepping technique in combination with adding a power integrator technique, the attitude stabilization control law is constructed. Rigorous mathematical proof shows that the closed-loop system is finite time stable and all the outputs remain bounded by using a barrier Lyapunov function technique. The effectiveness of the proposed finite-time stabilization scheme is verified by a simulation example.

Highlights

As is well-known, all practical systems are subject to physical constraints
We present the basic idea of the detailed implementation of an adaptive finite-time control for a spacecraft with output constraints
Consider the rigid spacecraft system model defined by equations (1) and (2), the proposed state feedback control law (41) can ensure the global finite-time stabilization of the closed-loop system at the origin and without violation of the output constraints, that is, jyj < kb, 8t > 0

Summary

Introduction

As is well-known, all practical systems are subject to physical constraints. Ignoring these constraints’ effects may result in undesirable performance degradation, safety matters, and even the instability of the system. There have been relatively few works on finite-time attitude stabilization for spacecrafts with output constraints in the literature. Finite-time stabilization by considering states constraints can improve the control performance. In the study by Xia et al.,[48] an adaptive fuzzy controller is designed to address the finite-time tracking control problem for a class of strict feedback nonlinear systems with full state constraints. The problem of finite-time attitude stabilization of a rigid spacecraft in the face of output constraints is investigated inspired by above discussion. 2. The output-constrained problems are considered in the finite-time control design process, which is more general for applications in practical engineering. 0. The main objective of this work is to design a finite-time attitude stabilizer for an output-constrained spacecraft described by systems (1) and (2). @@Txxh1ip1ei Árx_e1fiore,@@wxxe1ip1ihÁajxv_ 1eij j iðÁÞjÁðjl1ijp þjl2ijp ÁjiðÁÞjÞ ð35Þ ðjl1ijp þ jl2ijpÞÁ Fi

PD Method FPD Method Proposed Method

Conclusion