Adaptive output feedback sliding-mode manoeuvring and vibration control of flexible spacecraft with input saturation

2008 ◽  
Vol 2 (6) ◽  
pp. 467-478 ◽  
Author(s):  
Q. Hu
Keyword(s):  
Vibration Control ◽  
Output Feedback ◽  
Sliding Mode ◽  
Input Saturation ◽  
Flexible Spacecraft

scholarly journals Output Feedback Sliding Mode Control for Bending and Torsional Vibration Control of 6-story Flexible Structure

2002 ◽  
Vol 45 (1) ◽  
pp. 150-158 ◽  
Author(s):  
Kosuke IWAMOTO ◽  
Yuji KOIKE ◽  
Kenzo NONAMI ◽  
Koji TANIDA ◽  
Itaru IWASAKI
Keyword(s):  
Sliding Mode Control ◽  
Vibration Control ◽  
Torsional Vibration ◽  
Output Feedback ◽  
Sliding Mode ◽  
Flexible Structure ◽  
Mode Control

scholarly journals Attitude and Vibration Control of Flexible Spacecraft Using Singular Perturbation Approach

2014 ◽  
Vol 2014 ◽  
pp. 1-13 ◽  
Author(s):  
Morteza Shahravi ◽  
Milad Azimi
Keyword(s):  
Singular Perturbation ◽  
Vibration Control ◽  
Time Scale ◽  
Attitude Control ◽  
Sliding Mode ◽  
Flexible Spacecraft ◽  
Perturbation Approach ◽  
Elastic Mode ◽  
Sliding Manifold ◽  
Slow Subsystem

This paper addresses a composite two-time-scale control system for simultaneous three-axis attitude maneuvering and elastic mode stabilization of flexible spacecraft. By choosing an appropriate time coordinates transformation system, the spacecraft dynamics can be divided into double time-scale subsystems using singular perturbation theory (SPT). Attitude and vibration control laws are successively designed by considering a time bandwidths separation between the oscillatory flexible parts motion describing a fast subsystem and rigid body attitude dynamics as a slow subsystem. A nonlinear quaternion feedback control, based on modified sliding mode (MSM), is chosen for attitude control design and a strain rate feedback (SRF) scheme is developed for suppression of vibrational modes. In the attitude control law, the modification to sliding manifold for slow subsystem ensures that the spacecraft follows the shortest possible path to the sliding manifold and highly reduces the switching action. Stability proof of the overall closed-loop system is given via Lyapunov analysis. The proposed design approach is demonstrated to combine excellent performance in the compensation of residual flexible vibrations for the fully nonlinear system under consideration, as well as computational simplicity.

Fuzzy Sliding Mode Control of a Flexible Spacecraft With Input Saturation

2009 ◽  
Author(s):  
Shengjian Bai ◽  
Pinhas Ben-Tzvi ◽  
Qingkun Zhou ◽  
Xinsheng Huang
Keyword(s):  
Sliding Mode Control ◽  
Sliding Mode ◽  
Input Saturation ◽  
Flexible Spacecraft ◽  
Body Motion ◽  
Control Input ◽  
Local Domain ◽  
Fuzzy Sliding Mode Control ◽  
Mode Control ◽  
Fuzzy Sliding Mode

This paper presents the dynamic modeling and fuzzy sliding mode control (FSMC) for a spacecraft with flexible appendages. A first-order approximate model (FOAM) of the flexible spacecraft system is formulated by using Hamilton’s principles and assumed mode method (AMM), taking into account the second-order term of the coupling deformation field. The use of classical Sliding Mode Control (SMC) presents a major problem that appears in the form of chattering. For highly flexible structural models, ideal sliding surface producing pure rigid body motion may not be achievable. In this paper, the discontinuity in the sliding mode controller is smoothened inside a thin boundary layer by using fuzzy logic (FL) techniques so that the chattering phenomenon is effectively reduced. The robustness of SMC only holds in the sliding mode domain (SMD). However, when the amplitude of the actuators is limited, SMD will be restricted to some local domain near zero on the switching surface. Control input saturation is also explicitly considered in the FSMC approach. The new features and advantages of the proposed approach are the use of new dynamic equations of motion of flexible spacecraft systems, and the design of FSMC by taking into account the control input saturation. To study the effectiveness of the corresponding control scheme, the classical SMC case is also developed for the control system. Numerical simulations are performed to show that rotational maneuvers and vibration suppression are accomplished in spite of the presence of disturbance torques, model uncertainty and control saturation nonlinearity.

Adaptive Vibration Control of Flexible Structure With Sliding Mode Compensator

2005 ◽  
Author(s):  
J. Fei ◽  
C. Batur
Keyword(s):  
Adaptive Control ◽  
Vibration Control ◽  
Output Feedback ◽  
Sliding Mode ◽  
Flexible Structure ◽  
Output Tracking ◽  
Control Scheme ◽  
Simulation Results ◽  
Adaptive Vibration Control ◽  
Adaptive Control Scheme

This paper presents the adaptive control scheme with sliding mode compensator for vibration control problem in the presence of disturbance. The dynamic model of the flexible cantilever beam using finite element modeling is derived. The adaptive control with sliding mode compensator using output feedback for output tracking is developed to reject the disturbance, and to improve the tracking performance. Satisfactory simulation results verify that the effectiveness of adaptive control scheme with sliding mode compensator.

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