By A. Miele, et al.
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Extra info for Advanced Des. Probs in Aerospc Eng. - [Vol 1 Adv. Aero. Systs]
50 A. Miele and S. Mancuso Design of Moon Missions 51 52 A. Miele and S. Mancuso Design of Moon Missions 53 5. Earth-Moon-Earth Flight A very interesting observation can be made by comparing the results obtained in Sections 3 and 4, in particular Tables 1-2 and Tables 3-4. In these tables, two kinds of phase angles are reported: for the phase angles and the reference line is the initial direction of the Earth-Moon axis; for the phase angles and the reference line is the instantaneous direction of the Earth-Moon axis.
For TSTO configurations, these results justify having neglected in the analysis drag changes due to staging, and hence having assumed that the drag function of Stage 2 is the same as the drag function of Stage 1. 7. Conclusions In this paper, the feasibility of single-stage-suborbital (SSSO), single- Design of Rocket-Powered Orbital Spacecraft 27 stage-to-orbit (SSTO), and two-stage-to-orbit (TSTO) rocket-powered spacecraft has been investigated using optimal control theory. Ascent trajectories have been optimized for different combinations of spacecraft structural factor and engine specific impulse, the optimization criterion being the maximum payload weight.
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. 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.
Advanced Des. Probs in Aerospc Eng. - [Vol 1 Adv. Aero. Systs] by A. Miele, et al.