Lagrangian equilibrium point, L2 point, escape trajectory, escape velocity, orbit calculation, orbital mechanics, equation of motion, sequential quadratic programming method, SQP method, Earth gravitation, orbital maneuver, spacecraft trajectory, velocity, three body problem
Graduate University for Advanced Studies
Japan Aerospace Exploration Agency
出版者
宇宙航空研究開発機構宇宙科学研究本部
出版者（英）
Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA/ISAS)
雑誌名
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
雑誌名(英)
Proceedings of 16th Workshop on JAXA Astrodynamics and Flight Mechanics
ページ
42 - 48
発行年
2007-03
抄録（英）
The 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.
Earth escape trajectories starting from L2 point
