Analytical Quasi-Optimal Algorithm for the Time-Minimal Reorientation of a Spacecraft under Arbitrary Boundary Conditions

The time-optimal attitude maneuver problem of a spacecraft as a rigid body of an arbitrary dynamic configuration under arbitrary boundary conditions is considered. In the class of generalized conical motions, the optimal attitude maneuver problem is modified, which makes it possible to obtain its analytical solution. The analytical solution to the modified problem can be considered as an approximate (quasi-optimal) solution to the classical optimal problem. The report presents a theoretically and numerically sound and ready-to-use-onboarda-spacecraft compact analytical quasi-optimal algorithm of the program attitude maneuver, which is very close to optimal according to the results.