Optimization of a low-thrust transfer to an artificial satellite orbit around Jupiter

Details Optimization of a low-thrust transfer to an artificial satellite orbit around Jupiter Optimization of a low-thrust transfer to an artificial satellite orbit around Jupiter

Aug 1986

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1986mvsmm.......90g&link_type=abstract

Moskovskii Universitet, Vestnik, Seriia 1 - Matematika, Mekhanika (ISSN 0579-9368), July-Aug. 1986, p. 90-92. In Russian.

Physics

Artificial Satellites, Flight Optimization, Jupiter (Planet), Low Thrust, Planetary Orbits, Transfer Orbits, Boundary Value Problems, Energy Conservation, Planetary Gravitation, Satellite Orbits

Scientific paper

The problem considered here is that of plotting a minimum-energy trajectory for the transfer of a spacecraft with a low-thrust engine from a parabolic geocentric orbit to an orbit around Jupiter. The low-thrust engine is assumed to be perfectly adjustable and have constant power. The problem is divided into two subproblems: the internal one and the external one. The external problem, which consists in optimizing the trajectory of a flight from a geocentric orbit to the gravitational field of Jupiter, is reduced to a six-parameter boundary value problem. The internal problem, i.e., the transfer to an orbit around Jupiter, is reduced to that of solving a two-parameter boundary value problem. Two possible schemes for putting the spacecraft in orbit around Jupiter are examined.

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