Minimum maneuver costs for attitude reorientation of spacecraft of all possible inertial distribution over a wide range of maneuver angles by use of the impulse coning method of reorientation was studied. Maneuver cost is proportional to the product of fuel consumed and time expended during a maneuver. Assumptions included impulsive external control torques, rigid-body spacecraft, rest-to-rest maneuvers, and no disturbance torques. Also, coning maneuvers were constrained to have equal initial and final cone angles. Maneuver costs are presented for general reorientations as well as for spin-axis reorientations where final attitude about the spin axis is arbitrary.
Attitude Reorientation of Spacecraft by Means of Impulse Coning
1977
52 pages
Report
No indication
English
Attitude reorientation of spacecraft by means of impulse coning
TIBKAT | 1977
|Two-Impulse Reorientation of Asymmetric Spacecraft
NTIS | 1979
|Two-impulse reorientation of asymmetric spacecraft
TIBKAT | 1979
|Two-impulse reorientation of asymmetric spacecraft
NTRS | 1979
|