Authors

Abstract

Solar panels are used in satellites to absorb solar energy and supply the power needed for space missions. Mission definition and satellite lifetime is restricted by the way and the amount of energy that can be supplied for satellite subsystems. Therefore, the design of satellite solar panels as a unique source for power supply in satellites is very sensitive and important. In this paper, an efficient design for solar panels of a GEO communication satellite is proposed considering the maximum strength to weight ratio and minimum deflection. For this purpose different space structures including Iso Grid structures, honeycomb and composite plates are studied. Several structural analyses are performed on the models in order to assurance from the strength and durability of the model in space working environments. The design according to composite-honeycomb is introduced as the best model for solar panel structure. The proper configuration of layers is also presented by developing a code based on an optimization algorithm.

Keywords

[1] Shahrabi, H. “Introduction to Locate Satellite Subsystems,” Graduate Seminar, 2000 (In Persian).
[2] Bolandi, H. et al. Introduction to Design principles of Satellite, Iran University of Science and Technology, 2000 (In Persian).
[3] Ley, W. and Wittmann, K. and Hallmann, W., Handbook of Space Technology, United Kingdom, 2009.
[4] Griffin, M. D. and French, J. R., Space Vehicle Design,
[5] Agrawal, B. N., Design of Geosynchoronous Spacecraft, rentice-Hall, 1986.
[6] European Cooperation for Space Standardization, ECSS-E-ST-32C, ECSS Secretariat, ESA-ESTEC, Requirements & Standards Division, Noordwijk, The Netherlands, 2008.
[7] Primary Design Report of Power Subsystem of the Satellite, Space Research Institute, ZRH/CD/SRI/007, 2011.
[8] Morozov, E. V., Lopatin, A. V., “Analysis and Design of the Flexible Composite Membrane Stretched on the Spacecraft Solar Array Frame,” Composite Structures, 94, No, 10, 2012, pp. 3106–3114.
[9] Morozov, E.V., Lopatin, A.V., “Design and Analysis of the Composite Lattice Frame of a Spacecraft Solar Array,” Composite Structures, 93, No. 7, 2011, pp. 1640–1648.
[10] Raziramandi, J., “Study of Isogrid Structures and their Applications in the Industries of Aerospace,” Graduate Seminar, Department of Mechanical Engineering, Iran University of Science and Technology, 2005 (In Persian).
[11] Noor, A. K., Burton, W. S., “Computational Models for Sandwich Panels and Shells,” Applied Mechanics Reviews, 49, No. 3, 1996, pp. 155–199.
[12] Frostig, Y., “Classicaland High-Order Computational Models in the Analysis of Modern Sandwich Panels,” Journal of Composit Part B: Engineering, 34, No 1, 2003, pp. 83–100.
[13] He, L. and Cheng, Y. Sh. and Liu, J., “Precise Bending Stress Analysis of Corrugated-Core, Honeycomb-Core and X-Coresandwich Panels,” Journal of Composite Structures, 94, No, 5, 2012, pp. 1656–1668.
[14]  ANSYS12.0 Help.
[15] Paik, J. K. and Thayamballi, A. K. and Sung Kim, G., “The Strength Characteristics of Aluminum Honeycomb Sandwich Panels,” Thin-Walled Structures, Vol. 35, No. 3, 1999, pp. 205–231,
[16] Jen, Y. and Chang, L. Y., “Effect of Thickness of Face Sheet on the Bending Fatigue Strength of Aluminum Honeycomb Sandwich Beams,” Journal of Engineering Failure Analysis, Vol. 16, No. 4, 2009, pp. 1282–1293.
[17] Abbadi, A. and et. al.,, “Experimental and Numerical Characterization of Honeycomb Sandwich Composite Panels,” Journal of Simulation Modelling Practice and Theory, Vol. 17, No. 10, 2009, pp. 1533–1547.
[18] Tsai, S. W. and Hahn, H. Th., Introduction to Composite Material, Published in the Western Hemisphere by Technomic Publishing Company, 1980.