2022-01-25T13:34:37Zhttps://jaxa.repo.nii.ac.jp/?action=repository_oaipmhoai:jaxa.repo.nii.ac.jp:000075092021-03-17T09:20:15Z01543:01544:0155701887:01891
Earth escape trajectories starting from L2 pointengラグランジュ平衡点L2点脱出軌道脱出速度軌道計算軌道力学運動方程式逐次2次計画法SQP法地球重力軌道変換宇宙機軌道速度3体問題Lagrangian equilibrium pointL2 pointescape trajectoryescape velocityorbit calculationorbital mechanicsequation of motionsequential quadratic programming methodSQP methodEarth gravitationorbital maneuverspacecraft trajectoryvelocitythree body problemhttp://id.nii.ac.jp/1696/00007503/Conference Paper中宮, 賢樹山川, 宏Nakamiya, MasakiYamakawa, Hiroshi宇宙航空研究開発機構宇宙科学研究本部Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA/ISAS)第16回アストロダイナミクスシンポジウム講演後刷り集 2006 = Proceedings of 16th Workshop on JAXA Astrodynamics and Flight Mechanics42482007-03The L1 and L2 points of the Sun-Earth system, which are located about 1.5 million km away from the Earth in the sun and anti-sun direction, are widely used as suitable locations for space observatories to a great extent. These points are also thought as a gateway for the interplanetary transfer in the near future. This paper investigates the escape trajectories from the Earth's gravity leaving the Sun-Earth L2 point in the restricted three-body problem. Firstly, we discussed the one-impulse escape strategy assuming velocity correction only at L2 point, and the two-impulse escape strategy assuming the first velocity correction at L2 point and the second velocity correction at the subsequent perigee point. By keeping the hyperbolic excess velocity constant, the required total velocity correction amount and the flight path geometry are analyzed both analytically using Jacobi integral. Finally, optimal escape trajectories of these strategies are calculated by SQP (Sequential Quadratic Programming method), optimal multi-impulse escape strategy is also investigated.資料番号: AA00634810082020-01-17