Comparison of Interplanetary Trajectories as Computed by Patch-Conic and Perturbation Methods.
AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING
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The theory and programing techniques to generate analytical 2 body and perturbed 3-body trajectories for vehicle - planet encounters are presented. A range vehicle initial configurations is used to generate comparative trajectory data for encounters with Venus, Mars, and Jupiter. Underlying assumptions of the study are circular planetary orbits, coplanar 3-body motion, and an inertial planetocentric coordinate system. With vehicle osculation occuring on the surface of the planetary zone of influence, it was found that the time dependent perturbative deviations were simple exponential functions. The data was generated by an Encke method technique and partially verified by a Cowell method program. Author
- Spacecraft Trajectories and Reentry