http://swrc.ontoware.org/ontology#InProceedings
Earth escape trajectories starting from L2 point
en
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
中宮 賢樹
山川 宏
Nakamiya Masaki
Yamakawa 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)
Proceedings of 16th Workshop on JAXA Astrodynamics and Flight Mechanics
42-48
2007-03
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.
資料番号: AA0063481008