Finite-time fault tolerant attitude stabilization control for rigid spacecraft

2014 ◽  
Vol 53 (2) ◽  
pp. 241-250 ◽  
Author(s):  
Xing Huo ◽  
Qinglei Hu ◽  
Bing Xiao
Keyword(s):  
Finite Time ◽  
Fault Tolerant ◽  
Attitude Stabilization ◽  
Stabilization Control ◽  
Rigid Spacecraft

scholarly journals Finite-Time Stabilization Control for a Rigid Spacecraft under Parameter Uncertainties

2014 ◽  
Vol 2014 ◽  
pp. 1-11 ◽  
Author(s):  
Aihua Zhang ◽  
Jianfei Ni ◽  
Xing Huo
Keyword(s):  
Finite Time ◽  
Parameter Uncertainties ◽  
External Disturbances ◽  
Attitude Stabilization ◽  
Stabilization Control ◽  
Time Control ◽  
Control Scheme ◽  
Lyapunov Stability Analysis ◽  
Homogeneous Method ◽  
Rigid Spacecraft

A novel finite-time control scheme is investigated for a rigid spacecraft in present of parameter uncertainties and external disturbances. Firstly, the spacecraft mathematical model is transformed into a cascading system by introducing an adaptive variable. Then a novel finite-time attitude stabilization control scheme for a rigid spacecraft is proposed based on the homogeneous method. Lyapunov stability analysis shows that the resulting closed-loop attitude system is proven to be stable in finite time without parameter uncertainties and asymptotically stable with parameter uncertainties. Finally, numerical simulation examples are also presented to demonstrate that the control strategy developed is feasible and effective for spacecraft attitude stabilization mission.

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

2020 ◽  
Vol 17 (1) ◽  
pp. 172988142090741
Author(s):  
Jianjun Ma ◽  
Peng Li
Keyword(s):  
Finite Time ◽  
Mathematical Proof ◽  
Function Technique ◽  
Attitude Stabilization ◽  
Adding A Power Integrator ◽  
Stabilization Control ◽  
Modified Rodrigues Parameters ◽  
Output Constraints ◽  
Rigid Spacecraft ◽  
Power Integrator

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.

Sign in / Sign up

Export Citation Format

Share Document