dc.contributor.author |
N. E. Ives |
en_US |
dc.date.accessioned |
2014-10-21T15:55:41Z |
|
dc.date.available |
2014-10-21T15:55:41Z |
|
dc.date.issued |
1959 |
en_US |
dc.identifier.other |
ARC/R&M-3276 |
en_US |
dc.identifier.uri |
https://reports.aerade.cranfield.ac.uk/handle/1826.2/3852 |
|
dc.description.abstract |
The equations of attitude motion are derived for small angular displacements from the equilibrium position of an earth-pointing satellite employing reaction-flywheel damping. This is followed by a discussion on the attitude control of a space-stabilised satellite, with particular reference to attitude control against the gravitational torque due to the earth and the use of reaction-jets for the control of a spherical satellite configuration; finally a single-plane analytical account is given, of a method of eliminating any undesirable angular momentum which the satellite may possess immediately it leaves the carrier missile for its future orbit. |
en_US |
dc.relation.ispartofseries |
Aeronautical Research Council Reports & Memoranda |
en_US |
dc.title |
Principles of attitude control of artificial satellites |
en_US |