Asymptotic Stability of Quaternion-based Attitude Control System with Saturation Function

In the design of attitude control, rotational motion of the spacecraft is usually considered as a rotation of rigid body. Rotation matrix parameterization using quaternion can represent globally attitude of a rigid body rotational motions. However, the representation is not unique hence implies difficulties on the stability guarantee. This paper presents asymptotically stable analysis of a continuous scheme of quaternion-based control system that has saturation function. Simulations run show that the designed system applicable for a zero initial angular velocity case and a non-zero initial angular velocity case due to utilization of deadzone function as an element of the defined constraint in the stability analysis.

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Dynamic Modeling and Analysis of Spacecraft With Variable Tilt of Flexible Appendages

Journal of Dynamic Systems Measurement and Control ◽

10.1115/1.4025998 ◽

2014 ◽

Vol 136 (2) ◽

Cited By ~ 9

Author(s):

Nicolas Guy ◽

Daniel Alazard ◽

Christelle Cumer ◽

Catherine Charbonnel

Keyword(s):

Control System ◽

Attitude Control ◽

Solar Panel ◽

Physical Parameters ◽

Attitude Control System ◽

Multibody Modeling ◽

Modeling And Analysis ◽

Complete Revolution ◽

The Stability ◽

Flexible Appendages

This article describes a general framework to generate linearized models of satellites with large flexible appendages. The obtained model is parameterized according to the tilt of flexible appendages and can be used to validate an attitude control system over a complete revolution of the appendage. Uncertainties on the characteristic parameters of each substructure can be easily considered by the proposed generic and systematic multibody modeling technique, leading to a minimal linear fractional transformation (LFT) model. The uncertainty block has a direct link with the physical parameters avoiding nonphysical parametric configurations. This approach is illustrated to analyze the attitude control system of a spacecraft fitted with a tiltable flexible solar panel. A very simple root locus allows the stability of the closed-loop system to be characterized for a complete revolution of the solar panel.

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On the stability analysis of a discontinuous quaternion attitude control system

2012 International Conference on System Engineering and Technology (ICSET) ◽

10.1109/icsengt.2012.6339363 ◽

2012 ◽

Author(s):

Harry Septanto ◽

Bambang Riyanto Trilaksono ◽

Arief Syaichu-Rohman ◽

Ridanto Eko Poetro

Keyword(s):

Control System ◽

Stability Analysis ◽

Attitude Control ◽

Attitude Control System ◽

The Stability

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Vibration Suppression of an Underactuated Dynamic System Using Virtual Actuators

Journal of Vibration and Acoustics ◽

10.1115/1.4034082 ◽

2016 ◽

Vol 138 (6) ◽

Cited By ~ 3

Author(s):

A. M. Khoshnood ◽

I. Azad ◽

S. M. Hasani

Keyword(s):

Control System ◽

Dynamic System ◽

Attitude Control ◽

Vibration Suppression ◽

Nonlinear Dynamic Model ◽

Attitude Control System ◽

Suppression Technique ◽

A New Technique ◽

And Performance ◽

The Stability

Sloshing is one of the critical problems in aerospace vehicles with liquid containers. Motion of the liquid in resonance situations can degrade the stability and performance of attitude control systems. Two important characteristics of this time varying phenomenon are sensorless and underactuated properties which lead to difficulty of attitude control system design. In this paper, a new technique based on soft sensor and virtual actuator is used to suppress the effects of fuel sloshing in an aerospace launch vehicle (ALV). For this purpose, a nonlinear dynamic model of the vehicle with mechanical model of the fuel sloshing is considered as a multibody dynamic system. The preliminary attitude control system of the vehicle is extended using the new vibration suppression technique and a numerical simulation of the nonlinear model is carried out. Results of the simulation show that the undesired effects of the fuel sloshing are effectively decreased using the proposed vibration suppression technique.

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Derived-Rate Increment Stabilization: Its Application to the Attitude Control Problem

Journal of Basic Engineering ◽

10.1115/1.3657269 ◽

1962 ◽

Vol 84 (1) ◽

pp. 54-60 ◽

Cited By ~ 14

Author(s):

J. C. Nicklas ◽

H. C. Vivian

Keyword(s):

Control System ◽

Angular Velocity ◽

Control Problem ◽

Limit Cycle ◽

Attitude Control ◽

Dead Zone ◽

The Other ◽

Feedback Signal ◽

Attitude Control System ◽

Jet Actuators

A gyro-free nonlinear attitude control system for a spacecraft is analyzed. On-off jet actuators are used. Hysteresis and a dead zone are intentionally put into the system. Under certain conditions the feedback signal in the control system is proportional to an angular velocity increment of the system. This is called the derived-rate increment feedback signal. The analysis for a single axis of the attitude control system is given in two parts. One part is concerned with the performance of the system in a limit cycle. The other part discusses the convergence to a limit cycle after a disturbance has occurred. Experimental results verify the results of the analysis. Typical results show the performance of the system during convergence to and operation in a limit cycle. Although the technique is described for use in an attitude control system, it can be successfully employed in other applications.

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