Automated design of multiple encounter gravity-assist trajectoriesGiven a range of initial launch dates and a set of target planets, a new approach to planetary mission design is developed, using an automated method for finding all conic solutions. Each point on the diagrams reproduced represents a single ballistic trajectory and is computed by modeling the trajectory as a conic section and solving the corresponding Lambert problem for each set of launch and arrival dates. An example which prescribes a launch period of 1975-2050 and target planets Uranus, Saturn, Jupiter, Neptune and Pluto is described whereby, all possible grand tour missions of this class are found, including the Voyager II trajectory. It is determined that this automated design tool may be applied to a variety of multiple encounter gravity-assist trajectories that are being considered for future missions.
Document ID
19900066002
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Longuski, James M. (Purdue University West Lafayette, IN, United States)
Williams, Steve N. (Purdue Univ. West Lafayette, IN, United States)