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

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.

Dynamic Modeling for a Flexible Spacecraft With Solar Arrays Composed of Honeycomb Panels and Its Proportional–Derivative Control With Input Shaper

2016 ◽  
Vol 138 (8) ◽  
Author(s):  
Lun Liu ◽  
Dengqing Cao
Keyword(s):  
Dynamic Model ◽  
Vibration Suppression ◽  
Hybrid Control ◽  
Flexible Spacecraft ◽  
Solar Array ◽  
Pd Controller ◽  
Pd Control ◽  
Solar Arrays ◽  
Attitude Maneuver ◽  
The One

A high-precision dynamic model of a flexible spacecraft installed with solar arrays, which are composed of honeycomb panels, is established based on the nonconstrained modes of flexible appendages (solar arrays), and an effective cooperative controller is designed for attitude maneuver and vibration suppression by integrating the proportional–derivative (PD) control and input shaping (IS) technique. The governing motion equations of the system and the corresponding boundary conditions are derived by using Hamiltonian Principle. Solving the linearized form of those equations with associated boundaries, the nonconstrained modes of solar arrays are obtained for deriving the discretized dynamic model. Applying this discretized model and combining the IS technique with the PD controller, a hybrid control scheme is designed to achieve the attitude maneuver of the spacecraft and vibration suppression of its flexible solar arrays. The numerical results reveal that the nonconstrained modes of the system are significantly influenced by the spacecraft flexibility and honeycomb panel parameters. Meanwhile, the differences between the nonconstrained modes and the constrained ones are growing as the spacecraft flexibility increases. Compared with the pure PD controller, the one integrating the PD control and IS technique performs much better, because it is more effective for suppressing the oscillation of attitude angular velocity and the vibration of solar array during the attitude maneuver, and reducing the residual vibration after the maneuver process.

scholarly journals Adaptive Backstepping Attitude Control Law with L2-Gain Performance for Flexible Spacecraft

2019 ◽  
Vol 2019 ◽  
pp. 1-11
Author(s):  
Rui-Qi Dong ◽  
Yu-Yao Wu ◽  
Ying Zhang ◽  
Ai-Guo Wu
Keyword(s):  
Attitude Control ◽  
External Disturbance ◽  
Performance Criterion ◽  
Lyapunov Theory ◽  
Flexible Spacecraft ◽  
Control Law ◽  
Adaptive Backstepping ◽  
Unknown Parameters ◽  
Inertia Matrix ◽  
Attitude Maneuver

In this paper, an observer-based adaptive backstepping attitude maneuver controller (briefly, OBABC) for flexible spacecraft is presented. First, an observer is constructed to estimate the flexible modal variables. Based on the proposed observer, a backstepping control law is presented for the case where the inertia matrix is known. Further, an adaptive law is developed to estimate the unknown parameters of the inertia matrix of the flexible spacecraft. By utilizing Lyapunov theory, the proposed OBABC law can guarantee the asymptotical convergence of the closed-loop system in the presence of the external disturbance, incorporating with the L2-gain performance criterion constraint. Simulation results show that the attitude maneuver can be achieved by the proposed observer-based adaptive backstepping attitude control law.

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