GRAVITY-ASSISTED TRAJECTORIES FOR SOLAR PROBE MISSIONS
Abstract
An investigation of direct-transfer trajectories for solar probe missions indicates that expensive launch vehicles such as the Saturn V are required to achieve perihelia less than 0.25 AU and inclination angles above 20 degrees. Methods are developed for two- and three-dimensional gravity-assisted trajectories (trajectories which pass through one or more planetary gravitational fields), and are applied to solar probe missions in an attempt to reduce launch vehicle costs. The analysis is based on the pieced-conic approximation and the assumption of circular coplanar planetary orbits. It is found that a perihelion of 0.16 AU can be obtained with the Atlas/Centaur/TE- 364-3 by using a Venus assist. Even greater reductions in perihelia are attained with multiple passes at Venus; in addition, these missions allow the exploration of several regions near the Sun with a single launch. Venus-Mercury combination- assisted trajectories are of little value in solar probe missions. Solar impact and 90 degrees -out-of-ecliptic trajectories can be attained with a Jupiter assist; however, traversal of the asteroid belt and a three-year mission time decreases spacecraft reliability.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1967
- Accession Number
- AD0822156
Entities
People
- Kenneth A. Myers
Organizations
- Air Force Institute of Technology