The pseudostate theory, which approximates three-body trajectories by overlapping the conic effects of both massive bodies on the third body, has been used to solve boundary-value problems. Frequently, the approach to the secondary is quite close, as in interplanetary gravity-assist or satellite-tour trajectories. In this case, the orbit with respect to the primary is radically changed so that perturbation techniques are time consuming, yet higher accuracy than point-to-point conics is necessary. This method reduces the solution of the three-body Lambert problem to solving two conic Lambert problems and inverting a 7 x 7 matrix, the components of which are all found analytically. Typically 90-95 percent of the point-to-point conic error, with respect to an integrated trajectory, is eliminated.
Application of the pseudostate theory to the three-body Lambert problem
1989-09-01
Miscellaneous
No indication
English
Nonimpact Lunar Transfer Trajectories Using the Pseudostate Technique
Online Contents | 2005
|Integrated Algorithm for Lunar Transfer Trajectories Using a Pseudostate Technique
Online Contents | 2002
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