Optimal multiimpulse orbital transfers of a spacecraft from a point

Details Optimal multiimpulse orbital transfers of a spacecraft from a point Optimal multiimpulse orbital transfers of a spacecraft from a point

Mar 1978

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1978kosis..16..208i&link_type=abstract

Kosmicheskie Issledovaniia, vol. 16, Mar.-Apr. 1978, p. 208-216. In Russian.

Computer Science

Elliptical Orbits, Orbital Maneuvers, Satellite Orbits, Spacecraft Maneuvers, Trajectory Optimization, Transfer Orbits, Fuel Consumption, Gravitational Effects, Orbital Velocity

Scientific paper

Fuel-optimal multiimpulse plane transfers from a point on the initial orbit to a terminal elliptical orbit in a central Newtonian gravitational field near a planet. The distance between the spacecraft and the center of attraction, and the radial and transverse velocity components of the craft are known at the point of the initial orbit at the initial moment of time. The pericentric and the apocentric distances are given for the terminal orbit. The running distance between the craft and the center of attraction is subjected to upper and lower bounds. The transfer time is not fixed. All optimal multiimpulse solutions are obtained. These include solutions that are new as compared to solutions in the case of orbital transfer from a nonfixed point.

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