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Optimization of spacecraft with minimum power solar electric propulsion system interplanetary trajectories
Low-Energy Sub-Optimal Low-Thrust Trajectories to Libration Points and Halo-Orbits-thrust trajectories to the libration points of the Earth–Moon system and to halo-orbits. A method for solving
Trajectory optimization of a lunar direct landing from halo-orbitsThis paper illustrates the problem of optimizing the trajectory of a direct landing from a halo
Okhotsimsky-Egorov Method for Solving the Euler-Lambert ProblemA method for solving the Euler-Lambert problem by V.A. Egorov is presented, based on the work of D
Evaluation of optimal low-thrust interplanetary trajectories with collinear libration points transitions Yoon, Dr. Viacheslav G. Petukhov, Dr. Alexey V. Ivanyukhin. Published by the IAF, with permission
Solution of the Euler–Lambert Problem Based on the Okhotsimsky–Egorov Ballistic ApproachAbstract: The paper propose the method for solving the Euler–Lambert problem proposed by V.A
Optimization of Multi-revolution Limited Power Trajectories Using Angular Independent Variable propulsion systems. We consider the problem of limited power trajectory optimization, which is a well
Two-impulse orbital transfer based on the solution of Lambert problem with optimal flight timeLambert's problem is a classic problem of celestial mechanics. In practical cosmonautics
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