Design of the Deployment Mechanism of Solar Array on a Small Satellite

M. G. El-Sherbiny¹, A. Khattab¹ and M.K. Kassab^2,

¹Mechanical Design and Production Eng., Cairo University, Giza, Egypt

²Structure Department, National authority for Remote Sensing & Space Sciences (NARSS), Cairo, Egypt

Cite this paper:
M. G. El-Sherbiny, A. Khattab and M.K. Kassab. Design of the Deployment Mechanism of Solar Array on a Small Satellite. American Journal of Mechanical Engineering. 2013; 1(3):66-72. doi: 10.12691/ajme-1-3-2

Abstract

Abstract This paper presents analytical simulation of drag braking during deployment of a solar array system of a small satellite within the space environment, and helps the designer to detect problems during ground testing. The deployment mechanism (DM) is modeled by using Mechanical Desktop (MDT) software and analyzed by using Finite Element Analysis Package (ANSYS 11). Design and Stress analysis of DM is performed at the most critical points during its functioning. Several finite element analysis models were considered to verify the DM integrity. These analyses were correlated with static, modal and random vibration testing. The present work can help in checking the survival of the mechanism under realistic operating conditions and makes sure that it will perform well after an orbit insertion of the satellite.

Keywords:
satellite deployment mechanism shoe brake solar Array finite element modal analysis

This work is licensed under a Creative Commons Attribution 4.0 International License. To view a copy of this license, visit http://creativecommons.org/licenses/by/4.0/

Figures

References:

[1]	Heylen W., Lammens S., Sas P.,: Modal Analysis Theory and Testing, Katholieke Universiteit, , 1997.
[2]	Egypt Sat-1 Project, Satellite Preliminary Design. Album of Drawings. Doc. No. EGS YZH RPT 01801, NARS, EGYPT, 2007.
[3]	Kassab, M. “Design, Analysis, Manufacturing, and Testing of a Deployment Mechanism for Solar Panel of a Small Satellite“; Ph.D. thesis, Faculty of Engineering, Cairo University, Egypt, December 2011.
[4]	Friswell, M. I., Mottershead J. E., “ Finite Element Model Updating in Structural Dynamics” Dept. of Mechanical Engineering, University of Swansea, Swansea, U.K. Springer, Solid Mechanics and Its Applications, Vol. 38, P292. 1996.
[5]	Shibabrat N., Wrik M., “Experimental Modal Testing for Estimating the Dynamic Properties of a Cantilever Beam” , Department of Civil Engineering , Jadavpur University, Kolkato-700 032. http://fosonlietne.org/Thought/CA-77.pdf.
[6]	Bart B. Wim H. and Jan D.; “Modern Solutions for Ground Vibration Testing of Large Aircraft”; LMS International, Leuven, Belgium, SAE International Journal of Aerospace, April, 2009, Vol. 1, No. 1, pp. 732-742, 2009.
[7]	EgyptSat-1 Project, Satellite Preliminary Design. Composition and main Characteristics, Doc. No. EGS YZH RPT 01400 issue 2. 2007.
[8]	ANSYS, Inc. Release 11.0 Documentation for ANSYS.
[9]	Sudharsan, M; “Structural Design and Analysis of a lightweight Composite Sandwich Space Radiator Panel” Msc. Thesis, Office of Graduate Studies of Texas A&M University, USA, December 2003.
[10]	Neville F. Rieger; “the Relation between Finite Element Analysis and Modal Analysis”; Stress Technology Incorporated, Rochester, New York. 2008.
[11]	Fufa, B.; Zaho, C.; and Wensheag, M.; “Modeling and Simulation of Satellite Solar Panel Deployment and Locking” Information Technology Journal 9 (3): pp. 600-604, 2010.