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1-9. References 10-11 are general interest papers. References 12-15 investigate the partial or total use of electric propulsion or nuclear propulsion for Earth-Moon flight. For the algorithms employed to solve the problems formulated in this paper, see Refs. 16-17. For further details on topics covered in this paper, see Ref. 18. 2. System Description The present study is based on a simplified version of the restricted three-body problem. More precisely, with reference to the motion of a spacecraft in Earth-Moon space, the following assumptions are employed: (A1) the Earth is fixed in space; (A2) the eccentricity of the Moon orbit around Earth is neglected; (A3) the flight of the spacecraft takes place in the Moon orbital plane; (A4) the spacecraft is subject to only the gravitational fields of Earth and Moon; the gravitational fields of Earth and Moon are central and obey (A5) the inverse square law; (A6) the class of two-impulse trajectories, departing with an accelerating velocity impulse tangential to the spacecraft velocity relative to Earth [Moon] and arriving with a braking velocity impulse tangential to the spacecraft velocity relative to Moon [Earth], is considered.
LEPSCH, R. , and WIHITE, A. 241-249, 1995. 7. GREGORY, I. , CHOWDHRY, R. , and McMIMM, J. , Hypersonic Vehicle Model and Control Law Development Using and Synthesis, Technical Memorandum 4562, NASA, 1994. 8. , Primal and Dual Formulations of Sequential Gradient-Restoration Algorithms for Trajectory Optimization Problems, Acta Astronautica, Vol. 13, No. 8, pp. 491-505, 1986. 9. , Primal-Dual Properties of Sequential Gradient-Restoration Algorithms for Optimal Control Problems, Part 1: Basic Problem, Integral Methods in Science and Engineering, Edited by F.
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