Use Of Precession Modulation For Nutation Control Spin-stabilized Spacecraft
Abstract
This paper derives relations for nutation induced in a spinning spacecraft by periodic precession thrust pulses. By using the idea that nutation need only be observed just before each precession thrust pulse, a tedious continuous-time derivation reduces to a simple discrete-time derivation which can be easily solved through the use of z-transforms. The derived results are used to develop two precession control laws which use the precession maneuver to control nutation. © American Institute of Aeronautics and Astronautics, Inc., 1975, All rights reserved.
Recommended Citation
J. M. Taylor et al., "Use Of Precession Modulation For Nutation Control Spin-stabilized Spacecraft," Journal of Spacecraft and Rockets, vol. 12, no. 5, pp. 259 - 260, American Institute of Aeronautics and Astronautics, Jan 1975.
The definitive version is available at https://doi.org/10.2514/3.56971
Department(s)
Electrical and Computer Engineering
Keywords and Phrases
Earth Satellite Systems, Unmanned; Spacecraft Attitude Dynamics and Control
International Standard Serial Number (ISSN)
0022-4650
Document Type
Article - Journal
Document Version
Citation
File Type
text
Language(s)
English
Rights
© 2023 American Institute of Aeronautics and Astronautics, All rights reserved.
Publication Date
01 Jan 1975
Comments
National Aeronautics and Space Administration, Grant NGR26-003-069