Satellite, with inertia properties within specific range of values, is assumed to be in orbit of small eccentricity; cold-gas jets that are bounded in thrust level supply torques for attitude control; performance criterion in minimum-fuel consumption for reaching desired attitude in given time; Pontryagin's maximum principle is employed to determine characteristics of minimum-fuel, optimal control for linearized motion, and suboptimal, feedback, attitude-control system is developed that is simple and efficient.
Attitude control of satellite in elliptic orbit
J Spacecraft Rockets
Journal of Spacecraft and Rockets ; 4 , n 4
1967
7 pages
Aufsatz (Zeitschrift)
Englisch
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Attitude control of a satellite in an elliptic orbit.
NTRS | 1967
|Attitude control of a satellite in an elliptic orbit.
AIAA | 1967
|