Multi-objective output-feedback control for microsatellite attitude control: An LMI approach

Wu, Baolin; Cao, Xi‐Ren; Li, Zhengxue

doi:10.1016/j.actaastro.2008.12.012

Cited by 21 publications

(17 citation statements)

References 16 publications

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“…A complementary approach is the design of a local linear control, for example using linear matrix inequality (LMI) based results as in [19,2,24]. Such approaches have the advantage to provide robust controllers with optimized performances that can designed for precise models including flexible modes and actuator dynamics.…”

Section: Introductionmentioning

confidence: 99%

LMI-based design of a structured direct adaptive satellite attitude control with actuator rate feedback

Leduc

Peaucelle

Pittet

2015

2015 54th IEEE Conference on Decision and Control (CDC)

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International audienceSatellite attitude control of a microsatellite of the CNES Myriade series is considered. Reduction of saturations on the angular rate of reaction wheel actua-tors is addressed by means of control gain adaptation. The proposed adaptive control design has the following features: performances of the adaptive law are the same as those of a predefined linear time-invariant control when the state is close to the equilibrium; adaptation is structured allowing to include engineering considerations in the design; asymptotic stability is guaranteed based on Lyapunov arguments; fine tuning of adaptive gains is made by linear matrix inequality based convex optimization. The novelties compared to previous results are: to include mag-netotorquer information in the adaptive scheme; to provide a simplified design procedure

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Section: Introductionmentioning

confidence: 99%

LMI-based design of a structured direct adaptive satellite attitude control with actuator rate feedback

Leduc

Peaucelle

Pittet

2015

2015 54th IEEE Conference on Decision and Control (CDC)

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“…Thus it's absolutely necessary to research on the fault-tolerant control of satellite's attitude control system. Nowadays, several different control methods, such as sliding-mode control [3] , self-adaptive control [3,4] , PD control [5] , fuzzy control [3] , backstepping control [4] , H control [6,7] , and H 2 /H control [2,8,9] , are already applied in the satellite attitude control area. However, these control methods usually don't consider the satellite rotational inertia uncertainty or the actuator fault.…”

Section: Introductionmentioning

confidence: 99%

Robust fault-tolerant attitude control of three-axis stabilized satellite

Chen

Sun

et al. 2014

The 26th Chinese Control and Decision Conference (2014 CCDC)

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The three-axis stabilized satellite's attitude control under repairable fault conditions is researched in this paper. With the consideration of rotational inertia uncertainty, a control effectiveness factor is used to describe the fault magnitude of satellite actuators.Moreover, the uncertainty of fault diagnosis results is also considered in the design of controller. And a feedforward control unit is introduced to decrease the influence of fault diagnosis uncertainty, Therefore the attitude controller's absolute dependence on fault diagnosis results is avoided ultimately. The H and H 2 norms are used to signify the performance indexes of attitude information and output torques. The robust fault-tolerant attitude control is achieved by combining the state feedback with a pole assignment method.Finally, the simulation results reveal that this controller can stabilize a three-axis stabilized satellite quickly with a high precision of stabilization and pointing.

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“…So, designing the control system for flexible satellites will be encountered with a lot of problems [6]. Three main issues in designing attitude control of satellite are the space environmental disturbance, uncertainty in flexible structure and inertia matrix of satellite as well as control input constraints [7].…”

Section: Introductionmentioning

confidence: 99%

“…Also, they demonstrate the suitable performance of this design in maneuverability by applying it to a large flexible spacecraft model. In [7], a mixed 2 H H ∞ output-feedback controller has been proposed for microsatellite attitude control with pole placement constraints against the internal uncertainty of momentof-inertia variation and space environmental disturbances. The simulation results demonstrate that the presented mixed 2 H H ∞ control system is robust stable and optimal in the sense of 2 H norm, and has good steadystate and dynamic performance against parameter uncertainties and various disturbances for the microsatellite attitude control system.…”

Section: Introductionmentioning

confidence: 99%

Attitude Control of a Flexible Satellite by Using Robust Control Design Methods

Mohsenipour¹,

Nemati²,

Nasirian³

et al. 2013

ICA

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The increase of satellite’s dimensions has caused flexibility and formation of uncertainty in their model. This is because of space missions being more complex and using light moving structures in satellites. Satellites are also encountered with various circumferential disturbance torques. This uncertainty in model and disturbance torques will cause undesirable performance of satellites’ attitude control system. So, for attitude control of these satellites, those methods should be used which are robust to uncertainty of the plant’s model and can reject the effects of disturbances and the measurement noise. One of these methods is the robust control design method. But, because of pole’s place of these satellite’s dynamics equations, the designing procedure of robust control will face difficulties. In this paper, by using an internal feedback as a novel idea, the satellite’s dynamics equations are changed in such a way that the poles will be placed in proper locations. Then, for these new equations, by regarding the effects of flexibility as uncertainty and considering the uncertainty in inertia matrix of satellite, an H_∞controller has been designed and for better performance, a μ-controller has been improved. Afterwards, these two controllers are analyzed and compared for the original dynamic equations, not for the modified ones. Also, for comparison, a classic controller has been also designed for the original plant and eventually all these three controllers are compared with each other.

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Multi-objective output-feedback control for microsatellite attitude control: An LMI approach

Cited by 21 publications

References 16 publications

LMI-based design of a structured direct adaptive satellite attitude control with actuator rate feedback

LMI-based design of a structured direct adaptive satellite attitude control with actuator rate feedback

Robust fault-tolerant attitude control of three-axis stabilized satellite

Attitude Control of a Flexible Satellite by Using Robust Control Design Methods

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