Large angle attitude maneuver control for rigid spacecraft with delayed inputs and disturbances

2015 ◽  
Author(s):  
Alireza Safa ◽  
Mehdi Baradaran-nia ◽  
Hamed Kharrati ◽  
Sohrab Khanmohammadi
Keyword(s):  
Large Angle ◽  
Attitude Maneuver ◽  
Rigid Spacecraft

Robust Control of Flexible Spacecraft During Large-Angle Attitude Maneuver

2014 ◽  
Vol 37 (3) ◽  
pp. 1027-1033 ◽  
Author(s):  
Ya’nan Yu ◽  
Xiuyun Meng ◽  
Keyong Li ◽  
Fenfen Xiong
Keyword(s):  
Robust Control ◽  
Large Angle ◽  
Flexible Spacecraft ◽  
Attitude Maneuver

Optimization of Control Parameters Based on Multi-Objective Genetic Algorithms for Spacecraft Large Angle Attitude

2014 ◽  
Vol 538 ◽  
pp. 470-475 ◽  
Author(s):  
Qiang Huang ◽  
Jian Xin Zhang ◽  
Qiang Zhang ◽  
Xiao Peng Wei
Keyword(s):  
Optimization Design ◽  
Design Method ◽  
Large Angle ◽  
Weight Coefficient ◽  
Control Parameters ◽  
Multi Objective ◽  
Novel Approach ◽  
Attitude Maneuver ◽  
Nonlinear Dynamics Model ◽  
Optimizing Control

Based on multi-objective generic algorithms, a novel approach to optimizing control parameters for large angle spacecraft attitude was proposed. The large angle attitude maneuver controller was designed by taking the spacecraft nonlinear dynamics model and Lyapunov method. To optimize the controller parameters, the alterable weight coefficient method was adopted. Optimal value of time and power consumption acted as fitness goals of the algorithm. Simulation results showed that the algorithm proposed in this paper was superior to the traditional single-objective optimization design method.

Attitude Active Disturbance Rejection Control of Agile Satellite

2013 ◽  
Vol 419 ◽  
pp. 673-681
Author(s):  
Xiao Xiao Cai ◽  
Jin Jie Wu ◽  
Kun Liu
Keyword(s):  
Disturbance Rejection ◽  
Control Method ◽  
Large Angle ◽  
Control Moment ◽  
Active Disturbance Rejection ◽  
Disturbance Rejection Control ◽  
Attitude Maneuver ◽  
Agile Satellite ◽  
Nonlinear Extended State Observer ◽  
Pseudo Spectral Method

Based on the mission requirements of agile satellite, the control method of large angle maneuver was investigated in this paper. The single gimbal control moment gyroscope (sgcmg) of pyramid configuration is taken as the executor of the satellite. In order to avoid the singularity of sgcmgs, robust pseudo-inverse steering logic is used. An attitude active disturbance rejection controller (adrc) was designed. The expected attitude maneuver information that got by gauss pseudo-spectral method (gpm) took the place of that got by tracking differentiator (td). The constraints of satellite and sgcmgs are considered. Dynamics decoupling and disturbance observation of satellite were realized by using nonlinear extended state observer (neso). Then based on neso, nonlinear error feedback controller (nlsef) effectively suppresses the disturbance. The simulation results show that the attitude active disturbance rejection controller has steady control performance and can reject the disturbance better.

scholarly journals Finite-Time Controller for Flexible Satellite Attitude Fast and Large-Angle Maneuver

Symmetry ◽  
2021 ◽  
Vol 14 (1) ◽  
pp. 45
Author(s):  
You Li ◽  
Haizhao Liang ◽  
Lei Xing
Keyword(s):  
Finite Time ◽  
Sliding Mode ◽  
Large Angle ◽  
System Stability ◽  
Satellite Attitude ◽  
Attitude Maneuver ◽  
Mode Parameter ◽  
Mode Method ◽  
Dynamic Sliding Mode ◽  
Flexible Appendages

In order to deal with the fast, large-angle attitude maneuver with flexible appendages, a finite-time attitude controller is proposed in this paper. The finite-time sliding mode is constructed by implementing the dynamic sliding mode method; the sliding mode parameter is constructed to be time-varying; hence, the system could have a better convergence rate. The updated law of the sliding mode parameter is designed, and the performance of the standard sliding mode is largely improved; meanwhile, the inherent robustness could be maintained. In order to ensure the system’s state could converge along the proposed sliding mode, a finite-time controller is designed, and an auxiliary term is designed to deal with the torque caused by flexible vibration; hence, the vibration caused by flexible appendages could be suppressed. System stability is analyzed by the Lyapunov method, and the superiority of the proposed controller is demonstrated by numerical simulation.

A Hybrid Scheme of Synthesized Sliding Mode/Strain Rate Feedback Control Design for Flexible Spacecraft Attitude Maneuver Using Time Scale Decomposition

2016 ◽  
Vol 16 (02) ◽  
pp. 1450101 ◽  
Author(s):  
Morteza Shahravi ◽  
Milad Azimi
Keyword(s):  
Strain Rate ◽  
Sliding Mode ◽  
Large Angle ◽  
Flexible Spacecraft ◽  
Singular Perturbation Theory ◽  
Control Approach ◽  
Rate Feedback ◽  
Attitude Maneuver ◽  
Flexible Body Dynamics ◽  
Parameter Interactions

Presented herein is a new control approach for large angle attitude maneuver of flexible spacecraft. The singular perturbation theory (SPT) provides a useful tool for two time rate scale separation (mapping) of rigid and flexible body dynamics. The resulting slow and fast subsystems, enabling the use of two control approach for attitude (Modified Sliding Mode) and vibration Strain Rate Feedback (SRF) control of flexible spacecraft, respectively. An attractive feature of the present control approach is that the global stability of the entire system has been guaranteed while the controllers accomplished their tasks in coupled rigid/flexible dynamic domain without parasitic parameter interactions. Numerical simulations show the effectiveness of the present approach.

FUZZY CONTROL OF RIGID SPACECRAFT ATTITUDE MANEUVER WITH DECAY RATE AND INPUT CONSTRAINTS

2011 ◽  
Vol 19 (06) ◽  
pp. 1033-1046 ◽  
Author(s):  
XIHAI ZHANG ◽  
MING ZENG ◽  
XIAO YU
Keyword(s):  
Decay Rate ◽  
Linear Matrix Inequalities ◽  
Fuzzy Model ◽  
Linear Matrix ◽  
Spacecraft Attitude ◽  
Input Constraints ◽  
Matrix Inequalities ◽  
Attitude Maneuver ◽  
Rigid Spacecraft ◽  
Fuzzy State

The spacecraft attitude control systems are becoming more and more sophisticated with the increasing complex system configurations. This paper investigates the problem of three-axis rigid spacecraft maneuver control. The rigid spacecraft model consisting of the dynamic and kinematics equation is firstly provided. This nonlinear model is converted into a Takagi-Sugeno fuzzy model. Then, based on the parallel distributed compensation scheme, a fuzzy state feedback controller is designed for the obtained T-S fuzzy model with considering the decay rate and input constraints. Next, sufficient conditions for the existence of such a controller are derived in terms of linear matrix inequalities and the controller design is cast into a convex optimization problem subject to linear matrix inequalities constraints, which can be readily solved via Matlab LMI toolbox. At last, a design example shows that the time of spacecraft attitude maneuver is shortened and the input constraint is realized. The simulation results show the effectiveness of the proposed methods.

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