Mathematics
Scientific paper
Mar 1979
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1979kosis..17..225s&link_type=abstract
Kosmicheskie Issledovaniia, vol. 17, Mar.-Apr. 1979, p. 225-233. In Russian.
Mathematics
Elliptical Orbits, Orbital Mechanics, Satellite Orbits, Trajectory Optimization, Transfer Orbits, Differential Equations, Eccentricity, Fixed Points (Mathematics), Gravitational Fields
Scientific paper
One type of optimum (in terms of energy expenditure) multiimpulse orbital transfer for a spacecraft in a central Newtonian gravitational field near a planet is analyzed. The distance from the spacecraft to the center of gravity is bounded both above and below, and the initial state is specified by the distance to the center of gravity as well as the radial and transverse velocities. The orbit that corresponds to the initial data intercepts the inner edge of the permissible ring, the initial point lies on the ascending branch of this orbit, and an elliptical orbit with specified area and energy constants must be obtained upon completion of the transfer. It is found that two to five impulses may be imparted on optimum trajectories.
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