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- 佐々木 敏郎
- (株)日立製作所システム開発研究所
書誌事項
- タイトル別名
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- Proposal of a High Precision Orbit Design Method for Multiple Swingby Sequences
- スウィングバイ キドウ ニ オケル コウ セイド キドウ セッケイ ホウシキ
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In recent deep space mission analyses of artificial satellites, multiple swingby maneuvers using gravity assists become more important. Because of fuel limitation due to weight constraint on these satellites, a high precision optimal trajectory analysis is required to minimize total impulsive ΔV for trajectory control.<br>This multiple swingby trajectory analysis is formulated as a nonlinear parameter optimization problem. The difficulty of this problem is caused by the unstable convergence due to a non-linear gravity effect, because swingby trajectories must pass close to the gravity resources.<br>In this paper, a new optimization procedure for high precision multiple swingby trajectories is proposed, which uses the patched conic method in an iteration scheme to calculate the non-linear characteristics expressing a gravity effect precisely. The simulation results of a double lunar swingby trajectory show that the proposed method is effective for a multiple swingby trajectory analysis from the viewpoints of computation time and total ΔV for trajectory control.
収録刊行物
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- 計測自動制御学会論文集
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計測自動制御学会論文集 23 (9), 954-960, 1987
公益社団法人 計測自動制御学会
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詳細情報 詳細情報について
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- CRID
- 1390282679479995904
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- NII論文ID
- 130003790303
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- NII書誌ID
- AN00072392
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- ISSN
- 18838189
- 04534654
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- NDL書誌ID
- 3154457
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- JaLC
- NDL
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