| タイトル | Application of the rectilinear impact pseudostate method to modeling of third-body effects on interplanetary trajectories |
| 著者（英） | Sergeyevsky, A. B.; Damario, L. A.; Byrnes, D. V. |
| 著者所属（英） | Jet Propulsion Lab., California Inst. of Tech. |
| 発行日 | 1983-01-01 |
| 言語 | eng |
| 内容記述 | 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 |
| NASA分類 | ASTRODYNAMICS |
| レポートNO | 83A19576
AIAA PAPER 83-0015 |
| 権利 | Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/405818 |
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