Article Sidebar

Submitted
August 2, 2023
Published
August 2, 2023
Download
PDF
Statistic
Read Counter : 31 Download : 19

Downloads

Download data is not yet available.

Metrics

Metrics Loading ...

Main Article Content

Abstract

Most present day spacecrafts have large interconnected deployed solar panels having very low natural frequencies. The control torque applied to maneuver the spacecraft sets up transient oscillations in the spacecraft. The present work studies the nature of these interactions. The spacecraft in orbit can be modeled as a free rigid mass with flexible elements attached to it. It is shown that the oscillations of the spacecraft body are characterized by the dynamic characteristics of the flexible panel even if the mass and mass moment of inertia of the body is signifcantly higher than that of the flexible panels. A simple model consisting of an Euler-Bernoulli beam attached to a mass can represents such a system. The infuence of various parameters of the Euler-Bernoulli beam and the rigid element on the disturbances caused in the rigid element are investigated. The characteristics are determined for a step and also for a torque input. The responses are obtained in terms of nondimensionalised quantities. It is demonstrated that using the simple model developed the responses of spacecraft body can be easily obtained.

Keywords

Vibration, Transient response, On-orbit, Spacecraft

Article Details

How to Cite
Joseph, T. K., Renji, K., & Venkatraman, K. (2023). Simple Mathematical Models for the Dynamics Of Spacecraft With Deployed Solar Panels. Journal of Aerospace Sciences and Technologies, 66(2), 84–95. https://doi.org/10.61653/joast.v66i2.2014.444
Download Citation
Endnote/Zotero/Mendeley (RIS)
BibTeX

References

  1. Nohmi, M. and Uchiyama, M., "Dynamics and 3- Axes Control of a Spacecraft with Flexible Structures", Decision and Control, Proceedings of the 35th Conference on Decision and Control, Kobe, Japan, 1996, pp.2695-2700.
  2. Silva, A.R. and De Souza, L.C.G., "Control System Flexible Satellite Interaction During Orbit Transfer Maneuver", Advances in the Astronautical Sciences, American Astronautical Society (AAS), 1998.
  3. Trigolo, A., Kuga, H.K. and De Souza, L.C.G., "Parameter Identification of a Rigid-flexible Satellite Using Kalman Filter", Proceedings of the 17th International Congress of Mechanical Engineering.
  4. Bhat, R. and Kulkarni, M.A., "Natural Frequencies of a Cantilever with Slender Tip Mass", AIAA Journal, 14, 1976, pp.536-537.
  5. Register, A.H., "A Note on the Vibrations of Generally Restrained, End Loaded Beams", Journal of Sound and Vibration, 172, 1994, pp.561-571.
  6. Rao, C.K. and Mirza, S., "A Note on Vibrations of Generally Restrained Beams", Journal of Sound and Vibration, 130, 1989, pp.453-465.
  7. Bhat, B.R. and Wagner, H., "Natural Frequencies of a Cantilever with Tip Mass Slender in the Axial Direction", Journal of Sound and Vibration, 45, 1976, pp.304-307.
  8. Goel, R.P., "Free Vibrations of a Beam-mass System with Elastically Restrained Ends", Journal of Sound and Vibration, 47, 1976, pp.9-14.
  9. To, C.W.S., "Vibration of a Cantilever Beam with a Base Excitation and Tip Mass", Journal of Sound and Vibration, 83, 1982, pp.445-460.
  10. Timoshenko, S., "Vibration Problems in Engineering", D Van Nostrand, 1964.
  11. Clough, R.W. and Penzien, J., "Dynamics of Structures", McGraw-Hill, New York, U.S.A., 1993.
  12. Meirovich, L., "Elements of Vibration Analysis", McGraw-Hill, New York, U.S.A., 1984. 13. Gere, J.M. and Timoshenko, S.P., "Mechanics of Materials", PWS Publishers, Boston, U.S.A., pp.389- 405.