Limitation of spacecraft orbit near colinear libration center of limited elliptical three body problem

Details Limitation of spacecraft orbit near colinear libration center of limited elliptical three body problem Limitation of spacecraft orbit near colinear libration center of limited elliptical three body problem

Nov 1987

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1987rpsct.......64e&link_type=abstract

In its JPRS Report: Science and Technology. USSR: Space p 64 (SEE N88-16063 08-42) Transl. into ENGLISH from Doklady Akademii Na

Physics

Constraints, Elliptical Orbits, Libration, Orbit Calculation, Spacecraft Orbits, Three Body Problem, Gravitational Fields, Spacecraft Control

Scientific paper

The method of osculating parameters is used to obtain the integral orbit
restrictedness condition around the colinear libration center in the
restricted elliptical three body problem. It is shown that, if a
restricted orbit exists, it can be found by solvig the equations of
spacecraft motion under the above mentioned conditions.

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