State dependent Riccati equation based spacecraft attitude control

2002 ◽  
Author(s):  
M. Xin ◽  
S. Balakrishnan
Keyword(s):  
Riccati Equation ◽  
Attitude Control ◽  
Spacecraft Attitude ◽  
Spacecraft Attitude Control ◽  
State Dependent

Retrospective cost adaptive spacecraft attitude control using control moment gyros

2014 ◽  
Author(s):  
Marc Camblor ◽  
Gerardo Cruz ◽  
Sergio Esteban ◽  
Fred A. Leve ◽  
Dennis S. Bernstein
Keyword(s):  
Attitude Control ◽  
Spacecraft Attitude ◽  
Spacecraft Attitude Control ◽  
Control Moment

Spacecraft attitude control with mutating orbital rate and actuator fading under Markovian jump framework

2021 ◽  
Vol ahead-of-print (ahead-of-print) ◽  
Author(s):  
Chengxi Zhang ◽  
Hui-Jie Sun ◽  
Jin Wu ◽  
Zhongyang Fei ◽  
Yu Jiang ◽  
...  
Keyword(s):  
Control Problem ◽  
Attitude Control ◽  
Algorithm Design ◽  
Control Policy ◽  
Spacecraft Attitude ◽  
Actuator Faults ◽  
Spacecraft Attitude Control ◽  
Dynamics Model ◽  
Markovian Jump ◽  
Content Type

Purpose This paper aims to study the attitude control problem with mutating orbital rate and actuator fading. Design/methodology/approach To avoid malicious physical attacks and hide itself, the spacecraft may irregularly switch its orbit altitude within a specific range, which will bring about variations in orbital rate, thereby causing mutations in the attitude dynamics model. The actuator faults will also cause changes in system dynamics. Both factors affect the control performance. First, this paper determines the potential switching orbits. Then under different conditions, design controllers that can accommodate actuator faults according to the statistical law of actuator fading. Findings This paper, to the best of the authors’ knowledge, for the first time, introduces the Markovian jump framework to model the possible unexpected mutating of orbital rate and actuator fading of spacecraft and then designs a novel control policy to solve the attitude control problem. Practical implications This paper also provides the algorithm design processes in detail. A comparative numerical simulation is given to verify the effectiveness of the proposed algorithm. Originality/value This is an early solution for spacecraft attitude control with dynamics model mutations.

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