Abstract
The implications of flexible appendages on the attitude dynamics of a space vehicle are examined in general terms. Two families of natural vibration modes, referred to as ‘constrained’ and ‘unconstrained’, are discussed and the relationships between them derived. The incorporation of either set of modes into a simulation of the general attitude motion (under the influence of perturbing torques and control torques) is explained. The influence of rotors on these results is also explored.
Article PDF
Similar content being viewed by others
Avoid common mistakes on your manuscript.
References
Bolotin, V. V.: 1964,The Dynamic Stability of Elastic Systems, Holden-Day.
Likins, P. W.: 1970, ‘Dynamics and Control of Flexible Space Vehicles’, JPL Tech. Report 32-1329, Rev. 1.
Likins, P. W.: 1971,J. Spacecraft Rockets 8, 264–273.
Likins, P. W. and Bouvier, H. K.: 1971,Astronaut. Aeronaut. 00, 64–71.
NASA: 1969, ‘Effects of Structural Flexibility on Spacecraft Control Systems’ NASA SP-8016.
Zienkiewicz, O. C.: 1971,The Finite Element Method in Engineering Science, McGraw-Hill.
Author information
Authors and Affiliations
Rights and permissions
About this article
Cite this article
Hughes, P.C. Dynamics of flexible space vehicles with active attitude control. Celestial Mechanics 9, 21–39 (1974). https://doi.org/10.1007/BF01236162
Received:
Revised:
Issue Date:
DOI: https://doi.org/10.1007/BF01236162