Active Control of a Smart Satellite under Thermal Loading

Azadi, Emad; Fazelzadeh, Seyed Ahmad; Azadi, Mohammad

Authors

¹ Faculty of Mechanical Engineering, Shiraz University, Shiraz, Iran

² Department of Mechanics, Marvdasht Branch, Islamic Azad University, Marvdasht, Iran

Abstract

In this paper, vibration suppression and maneuver control of a smart flexible satellite moving in acircular orbit are studied. The satellite is considered as a rigid hub and two flexible appendages withpiezoelectric layersattached on them as actuators. The satellite is moving in a circular orbit and has pitch angle rotation maneuver. The heat radiation effects on the appendages are considered. When the satellite is rotating around the Earth, the appendages experience periodic heating and cooling in the sunlight and shadow region of the Earth with the variation of the thermal environment.These nonlinear transient heat equations depends on the satellite maneuver angle and the panels vibrations, too. The thermally induced vibrations of the appendages and the heat transfer equation are coupled and should be solved simultaneously.Aninverse dynamic controller is proposed to control the satellite maneuver and appendage vibrations. Finally, the whole system is simulated and the effects of the heat radiation and piezoelectric actuators on the response of the system are studied. Also, the effectiveness and the capability of the controller are analyzed.

Keywords

References

[1] Kida, T. and et al., “An Optimal Slewing Maneuver Approach for a Class of Spacecraft with Flexible Appendages,” Journal of Acta Astronautica, Vol. 13,No.6, 1986, pp.311-318.

[2] Liu, X. and Onoda, J., “Controller Design for Vibration Suppression of Slewing Flexible Structures,” Journal of Computers & Structures, Vol. 70, No.1, 1999, pp. 119-128.

[3] Singh, A., “Flexible Spacecraft Maneuver: Inverse Attitude Control and Modal Stabilization,” Journal of ACTA Astronautica, Vol.17, No. 1, 1986, pp. 1-9.

[4] Qu, Z. Q. and Gao, W. B., “State Observation and Variable Structure Control of Rotational Maneuvers of a Flexible Spacecraft,” Acta Astronautica, Vol. 19, No. 8,1989, pp.657-667.

[5] Bainum, P. M. and Li, Z., “Optimal Large Angle Maneuvers of a Flexible Spacecraft,” Acta Astronautica, Vol. 25, No. 3,

1991, pp.141-148.

[6] Azadi, E., Eghtesa, M., Fazelzadeh, S.A. and Azadi, M.,“Vibration Suppression of Smart Nonlinear Flexible Appendages of a Rotating Satellite by Using Hybrid Adaptive Sliding Mode /Lyapunov Control,” Journal of Vibration and Control, Vol. 19, No. 7, 2013, pp.975-991.

[7] Azadi, M., Fazelzadeh, S.A., Eghtesad, M. and Azadi, E.,“Vibration Suppression and Adaptive-Robust Control of a Smart Flexible Satellite with Three Axes Maneuvering,”Acta Astronautica, Vol. 69, No.5, 2011, pp. 307-322.

[8] Azadi, V., Azadi, M., Fazelzadeh, S. A. and Azadi, E.,“Active Control of a FGM Beam under Follower Force with Piezoelectric Sensors/Actuators,” International Journal of Structural Stability and Dynamics, Vol. 14, No.3, 2014, pp. 1350063-1-19.

[9] Azadi، E., Eghtesad, M., Fazelzadeh, S. A. and Azadi, M.,“Active Vibration Suppression and Maneuver Control of an

Orbiting Smart Flexible Satellite,” Iranian Journal of Science & Technology, Transactions of Mechanical Engineering, Vol. 38, No. M1, 2014، pp. 119-133.

[10] Tavakkoli, A. H., Kalhor, A. and Dehghan, S. M. M.,“Esstimation of Operation of Satellite Three DOF Simulation with Appling Three Axes Controllers,” Jouranl of Space Science and Technology, Vol. 5 No. 2,Summer 1391, pp. 59-68 (In Persian).

[11] Bolandi, H., Abedi, M. and Haghparast, M., “Algorithm Design Fault Detection and Isolation of the Proposed Thresholds for Control Subsystem of a Satellite Triaxial,”Jouranl of Space Science and Technology, Vol. 6, No. 1,Spring 1392, pp. 31- 46 (In Persian).

[12] Fani Saberi, F. and Mehrjardi, A., “The Design of the Control System and Power Management for Satellite Remote Sensing with Regard to the Saturation Effect Wheels,” Jouranl of Space Science and Technology, Vol. 5, No. 4, Spring 1391, pp. 39-45 (In Persian).

[13] Shen, Q., Soudack, A. C. and Modi, V. J., “Analytical Solution of Attitude Motion for Spacecraft with a Slewing Appendage,” Nonlinear Dynamics, Vol. 6, No.2, 1994, pp.193-241.

[14] Singh, S. N. and Zhang, R., “Adaptive Output Feedback Control of Spacecraft with Flexible Appendages by Modeling Error Compensation,” Acta Astronautica, Vol.54, No. 4, 2004, pp. 229-243.

[15] Hui, L., Junfeng, L. and Baoyin, H., “Sliding Mode Control for Low-Thrust Earth-Orbiting Spacecraft Formation Maneuvering,” Aerospace Science and Technology, Vol. 10, No. 7, 2006, pp. 636-643.

[16] Maganti, G. B. and Singh, S. N., “Simplified Adaptive Control of an Orbiting Flexible Spacecraft,” Acta Astronautica, Vol. 61, No.7, 2007, pp. 575-589.

[17] Polites, M., Kalmanson, J. and Mangus, D., “Solar Sail Attitude Control using Small Reaction wheels and Magnetic

Torquers,” IMechE Aerospace Engineering Journal, Vol.222, No. 1, 2008, pp.53-62.

[18] “Wavelet Technique Applied to Dynamic Response of Thin-Walled Composite Booms Exposed to Solar Radiation,” 5th International Congress on Thermal Stresses and Related Topics, 2003.

[19] Na, S. and et al., “Dynamic Response Control of Rotating Composite Booms under Solar Radiation,” Journal of Thermal Stresses, Vol. 32, No. 1, 2009, pp. 21-40.

[20] De Xue, M., Duan, J. and Hai Xiang, Z., “Thermally- Induced Bending-Torsion Coupling Vibration of Large Scale Space Structures,” Comput Mech, Vol. 40, No. 4,2007, pp. 707-723.

[21] Jingtao, W., Shougen, Zh., Kang, Li. and Yiwu, L.,“Thermally Induced Vibration Analysis of Thin-Walled Beam Considering the Material`s Temperature Effect,”International Conference on Experimental Mechanics, Vol. 7375, 2009.

[22] Song, O., Yoon, I. and Librescu, L., “Thermally Induced Bending Vibration of Composite Spacecraft Booms Subjected to Solar Heating,” Journal of Thermal Tresses, Vol. 26, No.8, 2003, pp. 829-843.

[23] Li, J., Yan, Sh. and Cai, R., “Thermal Analysis of Composite Solar Array Subjected to Space Heat Flux,”Aerospace Science and Technology, Vol. 27, No. 1. 2013,pp. 84–94.

Active Control of a Smart Satellite under Thermal Loading

References

References

Volume 8, Issue 1 - Serial Number 22April 2015Pages 43-51

Volume 8, Issue 1 - Serial Number 22
April 2015
Pages 43-51