By A. Miele, et al.
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Extra resources for Advanced Des. Probs in Aerospc Eng. - [Vol 1 Adv. Aero. Systs]
The major parameters of the problem, the phase angles at departure, and the phase angles at arrival are shown in Table 1 for clockwise LMO arrival and Table 2 for counterclockwise LMO arrival. Design of Moon Missions 41 42 A. Miele and S. Mancuso Design of Moon Missions 43 A. Miele and S. Mancuso 44 Also for the optimal trajectory in Earth-Moon space, nearEarth space, and near-Moon space is shown in Fig. 1 for clockwise LMO arrival and Fig. 2 for counterclockwise LMO arrival. Major comments are as follows: the accelerating velocity impulse is nearly independent of the orbital altitude over the Moon surface (see Ref.
Recent Advances in the Optimization and Guidance of Aeroassisted Orbital Transfers, The 1st John V. Breakwell Memorial Lecture, Acta Astronautica, Vol. 38, No. 10, pp. 747-768, 1996. 16. , Robust Predictor-Corrector Guidance for Aeroassisted Orbital Transfer, Journal of Guidance, Control, and Dynamics, Vol. 19, No. 5, pp. 1134-1141, 1996. 17. , Flight Mechanics, Vol. 1: Theory of Flight Paths, Chapters 13 and 14, Addison-Wesley Publishing Company, Reading, Massachusetts, 1962. 18. NOAA, NASA, and USAF, US Standard Atmosphere, 1976, US Government Printing Office, Washigton, DC, 1976.
17. , Flight Mechanics, Vol. 1: Theory of Flight Paths, Chapters 13 and 14, Addison-Wesley Publishing Company, Reading, Massachusetts, 1962. 18. NOAA, NASA, and USAF, US Standard Atmosphere, 1976, US Government Printing Office, Washigton, DC, 1976. 2 Design of Moon Missions A. MIELE1 AND S. MANCUSO2 Abstract. In this paper, a systematic study of the optimization of trajectories for Earth-Moon flight is presented. The optimization criterion is the total characteristic velocity and the parameters to be optimized are: the initial phase angle of the spacecraft with respect to Earth, flight time, and velocity impulses at departure and arrival.