AbstractThe problem of minimum time low-thrust transfer between arbitrary elliptic orbits in the central gravitational field is under investigation. The rocket engine is assumed to produce constant in magnitude and controllable in direction thrust, which is essentially smaller than the gravity force. Approximate solution is obtained with the use of the averaging method. Averaged optimal motion equations are written in analytical form. Using both known and the new first integrals allows to reduce the order of the differential system of optimal motion equations down to fourth. The analytical solutions are obtained for a number of maneuvers. Since any transfer between elliptic orbits can be presented as a combination of those, allowing analytical solution, rapid estimation of the characteristic velocity requirements is possible. Control algorithms more simple for practical realization are proposed, and their efficiency is compared with that of the optimal control.
Minimum time transfers of a low-thrust rocket in strong gravity fields
Acta Astronautica ; 52 , 8 ; 601-611
2002-03-11
11 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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