Noncoplanar transfers between neighboring circular orbits are presented for spacecraft using their own low-thrust blow down propulsion system. It is assumed that the out-of-plane angle between the decaying thrust vector and the current orbit plane remains constant for each extended burn. Switching conditions are derived for the cutoff and relight of the propulsion system in order to carry out a given transfer with inclination change. Furthermore the location where the thrust acceleration is initially applied with respect to the line of nodes of the two orbits is uniquely determined. Finally an analytic derivation of the linearized coplanar motion for stationkeeping and terminal rendezvous studies is also presented and a scheme for deriving the second order correction shown.
Linearized transfer between inclined circular orbits using low-thrust blow down propulsion system
American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting ; 1983 ; Reno, NV
1983-01-01
Conference paper
No indication
English
Optimal Altitude-Constrained Low-Thrust Transfer Between Inclined Circular Orbits
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