Geostationary orbit transfers of a spacecraft with low-thrust electric propulsion systems (EPSs) that use the energy of solar batteries are considered. The influence of such disturbing factors as the gravitational effect of the Sun and Moon, geopotential variations, and switching off of the EPS thrust when the spacecraft enters the Earth’s shadow is investigated. The influence of all factors jointly and each of the factors separately is analyzed. In each case, to minimize the working substance expenditures for a transfer, the two-point boundary value problem is formulated and solved on the basis of the Pontryagin’s maximum. Only in the case of thrust switching off in the area of the shadow is the so-called “incomplete” boundary value problem solved. This solution does not take into account the conditions for optimal crossing the shadow boundaries. Although the transfers are nonoptimal in this case, it becomes possible by choosing the problem parameters to obtain good (in terms of expenditures) solutions. Here, the criterion is a comparison with the nominal trajectories—the optimal transfers in the central Newtonian field of the Earth without the thrust switching off and without taking the gravitational effect of the Sun and Moon into account. The results of calculations for several nominal trajectories, which differ in transfer duration, in the number of revolutions, and in other parameters, are presented.
The Influence of Disturbances during Multiturn Transfer to a Geostationary Orbit
Cosmic Res
Cosmic Research ; 59 , 5 ; 328-334
2021-09-01
7 pages
Article (Journal)
Electronic Resource
English
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