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Extra resources for Advanced Design Problems in Aerospace Engineering: Advanced Aerospace Systems

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14. , LEE, W. , and WU, G. , Ascent Performance Feasibility of the National Aerospace Plane, Atti della Accademia delle Scienze di Torino, Vol. 131, pp. 91-108, 1997. 15. , 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.

In light of these results, a further parametric study is performed. For given initial and final conditions, the transfer problem is solved again for fixed flight time smaller or larger than the optimal time. The results show that, if the prescribed flight time is within one 1 2 Research Professor and Foyt Professor Emeritus of Engineering, Aerospace Sciences, and Mathematical Sciences, Aero-Astronautics Group, Rice University, Houston, Texas 77005-1892, USA. Guidance, Navigation, and Control Engineer, European Space Technology and Research Center, 2201 AZ, Nordwijk, Netherlands.

Because Moon is moving with respect to Earth, the relative-to-Moon coordinates are not the 38 A. Miele and S. Mancuso same as the inertial coordinates As a consequence, corresponding to clockwise or counterclockwise arrival to LMO with tangential, braking velocity impulse, the arrival conditions can be written as follows: or alternatively, where Here, is the radius of the low Moon orbit and is the altitude of the low Moon orbit over the Moon surface; is the spacecraft velocity Design of Moon Missions 39 in the low Moon orbit (circular velocity) after application of the tangential is the braking velocity impulse; is the velocity impulse; spacecraft velocity before application of the tangential velocity impulse.

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