Vehicle-and-trajectory optimization of nuclear electric spacecraft for lunar missions

Details Vehicle-and-trajectory optimization of nuclear electric spacecraft for lunar missions Vehicle-and-trajectory optimization of nuclear electric spacecraft for lunar missions

Jan 1995

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1995jspro..32..126k&link_type=abstract

Journal of Spacecraft and Rockets (ISSN 0022-4650), vol. 32, no. 1, p. 126-132

Computer Science

1

Earth-Moon System, Earth-Moon Trajectories, Nuclear Electric Propulsion, Orbital Mechanics, Three Body Problem, Trajectory Optimization, Circular Orbits, Low Earth Orbits, Lunar Orbits, Specific Impulse, Transfer Orbits

Scientific paper

A new combined vehicle-and-trajectory optimization problem is solved for a low-thrust nuclear-electric-propulsion spacecraft whose motion is governed by restricted three-body-problem dynamics for the earth-moon system. The problem involves computing the optimal spacecraft sizing parameters and trajectory design variables that result in the maximum payload for a fixed-trip-time, planar transfer from circular low earth orbit to circular low-lunar orbit. In particular, the optimal specific impulse and input power are computed. The detailed vehicle-and-trajectory optimization approach is effective in solving a complex interactive problem that is important to both spacecraft and mission designers. Several numerical solutions are obtained for a wide range of trip times.

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