The paper describes a tradeoff in selecting a planetary encounter aimpoint and a spacecraft propulsive maneuver strategy in the Pioneer Venus Orbiter Mission. The method uses parametric data spanning a region of acceptable targeting aimpoints in the delivery space and the geometric considerations. Real-time maneuver adjustments accounted for known attitude control errors, orbit determination updates, and late changes in a targeting specification.
An interplanetary targeting and orbit insertion maneuver design technique
Astrodynamics Conference ; 1980 ; Danvers, MA
1980-08-01
Conference paper
No indication
English