Geometric solution of the problem of a rendezvous on close nearly circular coplanar orbits.

Details Geometric solution of the problem of a rendezvous on close nearly circular coplanar orbits. Geometric solution of the problem of a rendezvous on close nearly circular coplanar orbits.

May 1990

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1990cosre..27..689b&link_type=abstract

Cosmic Res., Vol. 27, No. 6, p. 689 - 696

Computer Science

Scientific paper

Two-, three-, and four-impulse manoeuvers are considered in a linear formulation, ensuring a gentle rendezvous of an active spacecraft: with the spacecraft's target. The impulses are applied in two phases of manoeuvering, separated by a distance of several orbits. Algorithms are presented which allow a determination of both the angles of application and the components of the impulses for which the total characteristic speed of the manoeuver is a minimum.

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