International Journal of Aeronautical and Space Sciences

The Korean Society for Aeronautical and Space Sciences (한국항공우주학회)
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Optimal Design of a High-Agility Satellite with Composite Solar Panels

  • Kim, Yongha (Graduate School of Aerospace and Mechanical Engineering, Korea Aerospace University) ;
  • Kim, Myungjun (Graduate School of Aerospace and Mechanical Engineering, Korea Aerospace University) ;
  • Kim, Pyeunghwa (Graduate School of Aerospace and Mechanical Engineering, Korea Aerospace University) ;
  • Kim, Hwiyeop (Graduate School of Aerospace and Mechanical Engineering, Korea Aerospace University) ;
  • Park, Jungsun (Department of Aerospace and Mechanical Engineering, Korea Aerospace University) ;
  • Roh, Jin-Ho (Department of Aerospace and Mechanical Engineering, Korea Aerospace University) ;
  • Bae, Jaesung (Department of Aerospace and Mechanical Engineering, Korea Aerospace University)
  • Received : 2016.09.08
  • Accepted : 2016.12.05
  • Published : 2016.12.30
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Abstract

This paper defines mode shape function of a composite solar panel assumed as Kirchhoff-Love plate for considering a torsional mode of composite solar panel. It then goes on to define dynamic model of a high-agility satellite considering the flexibility of composite solar panel as well as stiffness of a solar panel's hinge using Lagrange's theorem, Ritz method and the mode shape function. Furthermore, this paper verifies the validity of dynamic model by comparing numerical results from the finite element analysis. In addition, this paper performs a dynamic response analysis of a rigid satellite which includes only natural modes for solar panel's hinges and a flexible satellite which includes not only natural modes of solar panel's hinges, but also structural modes of composite solar panels. According to the results, we confirm that the torsional mode of solar panel should be considered for the structural design of high-agility satellite. Finally, we performed optimization of high-agility satellite for minimizing mass with solar panel's area limit using the defined dynamic model. Consequently, we observed that the defined dynamic model for a high-agility satellite and result of the optimal design are very useful not only because of their optimal structural design but also because of the dynamic analysis of the satellite.

Keywords

Acknowledgement

Supported by : Korea Institute of Energy Technology Evaluation

References

  1. Thomas, P. S. and Wiley, J. L., Spacecraft Structures and Mechanisms from Concept to Launch, Space Technology Library, 1995.
  2. Lim, J. H., "Recent Trend of the Configuration Design of High Resolution Earth Observation Satellites", Current Industrial and Technological Trends in Aerospace, Vol. 8, 2010, pp. 45-54.
  3. Sedighi, M, and Mohammadi, M., "On the static and dynamic analysis of a small satellite", Acta Astronautica, Vol. 52, No. 9, 2003, pp. 1007-1012. https://doi.org/10.1016/S0094-5765(03)00083-3
  4. Bai, Z., "Modal Analysis for Small Satellite System with Finite Element Method", Systems and Control in Aerospace and Astronautics, 2008. ISSCAA 2008. 2nd International Symposium on. IEEE, 2008, pp. 1-5.
  5. Byers, R. M. and Vadali, S. R., "Quasi Closed Form Solution to the Time Optimal Rigid Spacecraft Reorientation Problem", Journal of Guidance, Control, and Dynamics, Vol. 16, No. 3, 1993, pp. 453-461. https://doi.org/10.2514/3.21031
  6. Scrivener, S. L. and Thompson, R. C., "Survey of Time Optimal Attitude Maneuvers", Journal of Guidance, Control and Dynamics, Vol. 17, No. 2, 1994, pp. 225-233. https://doi.org/10.2514/3.21187
  7. Li, F. and Bainum, P. M., "Numerical Approach for Solving Rigid Spacecraft Minimum Time Attitude Maneuvers", Journal of Guidance, Control, and Dynamics, Vol. 13, No. 1, 1997, pp. 38-45. https://doi.org/10.2514/3.20515
  8. Ebarahimi, A., "Minimum-Time Optimal Control of Flexible Spacecraft for Rotational Maneuvering", Proceedings of the 2004 IEEE, 2004.
  9. Hu, Q. L., "Flexible Spacecraft Vibration Suppression Using PWPF Modulated Input Component Command and Sliding Mode Control", Asian Journal of Control, Vol. 9, No. 1, 2007, pp. 20-29.
  10. Kim, D. K., "Dynamic Modeling of a Satellite with Solar Array Flexible Modes", Journal of the Korean Society for Aeronautical & Space Sciences, Vol. 37, No. 9, 2009, pp. 837-842. https://doi.org/10.5139/JKSAS.2009.37.9.837
  11. Augustynek, K., "Dynamic Analysis of a Satellite with Flexible Links", The Archive of Mechanical Engineering, Vol. LVI, No. 3, 2009, pp. 199-208.
  12. Malekzadeh, M., "Robust Control of Non-linear Flexible Spacecraft", Mechanical Engineering, Vol. 17, No. 3, 2010, pp. 217-228.
  13. Meng, J., Zhang, L., Li, J. and Lv, M., "Dynamic Modeling and Simulation of Tethered Stratospheric Satellite with Thermal Effects", Applied Thermal Engineering, No. 110, 2016, pp. 181-189.
  14. He, W. and Ge, S. S., "Dynamic Modeling and Vibration Control of a Flexible Satellite", IEEE Transactions on Aerospace and Electronic Systems, Vol. 51, No. 2, 2015, pp. 1422-1431. https://doi.org/10.1109/TAES.2014.130804
  15. Liu, J. and Pan, K., "Rigid-Flexible-Thermal Coupling Dynamic Formulation for Satellite and Plate Multibody System", Aerospace Science and Technology, No. 52, 2016, pp. 102-114.
  16. Hwang, D. S., "Design and Analysis of Satellite Structure", Journal of the Korean Society for Aeronautical & Space Sciences, Vol. 27, No. 2, 1999, pp. 111-121.
  17. Reddy, J. N., Theory and Analysis of Elastic Plates and Shells, CRC Press, 2007.
  18. Tsai, S. W. and Hahn, H. T., Introduction to Composite Materials, TECHNOMIC, 1980.
  19. Arthur, W. L. and Mohanmad, S. Q., Vibrations of Continuous Systems, McGraw-Hill Companies, 2011.
  20. Daniel, J. I., Engineering Vibration Third Edition, Pearson International Edition, 2007.
  21. Holland, J. H., Adaptation in Natural and Artificial System, University of Michigan Press, 1975.
  22. Goldberg, D. E., Genetic Algorithms in Search, Optimization, and Machine Learning, Pearson Education, 2013.