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Free Vibration Analysis of Micro-Satellite Structure
Technical Paper
2004-01-3131
ISSN: 0148-7191, e-ISSN: 2688-3627
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English
Abstract
In recent years satellites of small sizes have been in development. Since electronic components are miniaturized and efficient, it is possible to develop satellite of small dimensions. The spirit of development of the small satellite in the world has been encompassed by the slogan “faster, better, smaller, cheaper”. The classes of satellite, which have the mass ranging from 10–100 kg, is called the micro-satellite. There are number of analysis like sensitivity analysis, vibration analysis, dynamic analysis and thermal analysis to be carried out in the development of the micro satellite both theoretically and experimentally. This paper discusses the free vibration analysis of a micro-satellite of mass less than 60kg. The micro satellite considered for this analysis is a spinning cuboids structure of 600mmx600mmx600mm dimensions with 18 subsystems positioned so as to meet the C.G and M.I. constraints. Aluminium honeycomb sandwich panels are considered as the primary type of construction for the analysis with aluminium alloy angles as the joining members between various structural elements. To model the micro-satellite structure and to analyze the commercially available FEM software NASTRAN was used. Analysis was carried out for basic structure as well as for the satellite with subsystems to find whether the configuration satisfies the frequency constraints. The effect of subsystem locations and natural frequencies were studied. Also the effect of deck plate thickness on the natural frequency of the satellite structure was studied to arrive at a configuration with desirable vibration characteristics. These results can be used in performing the detailed static and dynamic analysis of the micro satellite structure in the future.
Authors
Citation
Suresh*, K., Jayaraman, K., Baskar, V., and Ilangovan, S., "Free Vibration Analysis of Micro-Satellite Structure," SAE Technical Paper 2004-01-3131, 2004, https://doi.org/10.4271/2004-01-3131.Also In
References
- Nair P.S. Das Gupta S. Samuel R. Bande D.H. 1994 The Journal of Spacecraft Technology 4 4
- Weeks G.E. 1986 The Journal of Spacecraft Technology 23 1 102 107
- Bernaerts, F. Teston, J. Bermijn 2000 “PROBA (Project for on-board autonomy)” Proceedings of the 5 th International Symposium on Small Satellites Systems and Services La Baule June 19 – 23
- Bermyn Jo Bernaerts Dirk “PROBA (Project for on-board autonomy)” May 2001
- Shen M.H.H. Grady J.E. 1992 AIAA Journal 30 5 1361 1375
- Patel H.G. Ganapathy M. Patel B.P. 1998 Journal of Aeronautical Society of India 54 3 289 303
- Kumar V. Singh A.V. 1998 AIAA Journal 30 7 1929 1944
- McTavish Hughes P.C. 2000 AIAA Journal 30 5 1392 1410
- Badri Narayana K. Ramanath K.S. Bonde D.H. 1995 The Journal of Spacecraft Technology 5 3 33 45
- Onoda Junjiro 1988 Journal of Spacecraft Technology 25 2 “Two-Dimensional Deployable Truss Structure for Space Application” 109 118
- Somnath S. Balakrishnan S.S. 2002
- Krumweide G.C. 1995 th “Affordable polymer composite structures for various spacecraft structural components”
- Greathouse J et al 1992 th “The ISOSAT small satellite. Design in isogrid technology”
- Haber, R.B. Tortorelli, D.A. Vidal, C.A. Phelan, D.G. “Design Sensitivity Analysis of Nonlinear Structures - I: Large-Deformation Hyper elasticity and History-Dependent Material Response” Kamat M.P. Structural Optimization: Status & Promise, AIAA Progress is Astronautics and Aeronautics series, AIAA New York 369 405 1993
- Moore, Gregory J. “User’s Guide –MSC/Nastran – Design Sensitivity and Optimization” 1994
- Ravetti Fernando. M.N. Filho Mario Kataoka Vidal Creto.A. 1999