Abstract A problem of optimal turn of a spacecraft is considered. The time of turn is minimized, as well as the functional having a meaning of the propellant consumption. An analytical solution to the problem stated is derived. It is demonstrated that the solution optimal in this sense belongs to a class of two-impulse controls, under which a spacecraft executes the turn along the trajectory of its free motion. The solution obtained in this paper differs from earlier available solutions considerably. The estimations of the propellant consumption for a realization of the programmed turn are made.
Optimal Control of a Programmed Turn of a Spacecraft
Cosmic Research ; 41 , 2 ; 178-192
2003-03-01
15 pages
Article (Journal)
Electronic Resource
English
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