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- W1998245615 abstract "Interplanetary transfer trajectories, subject to the third-body gravitational attraction of the departure and arrival planets, noticeably deviate from the conic Lambert theorem solutions. The pseudostate method represents a useful improvement over conic theory by allowing the spacecraft motion about the sun and each terminal body to be superimposed, provided certain rules are followed. The new variant of the method requires iteration on time along the two planetocentric rectilinear impact trajectories. The operational equivalence of the method to the point-to-point Lambert formulation is an attractive feature, already used to advantage in the generation of mission design data" @default.
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- W1998245615 date "1983-01-10" @default.
- W1998245615 modified "2023-10-01" @default.
- W1998245615 title "Application of the rectilinear impact pseudostate method to modelingof third-body effects on interplanetary trajectories" @default.
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- W1998245615 doi "https://doi.org/10.2514/6.1983-15" @default.
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