Minimum fuel trajectories for low-thrust power-limited spacecraft

Details Minimum fuel trajectories for low-thrust power-limited spacecraft Minimum fuel trajectories for low-thrust power-limited spacecraft

Aug 1990

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1990phdt........24g&link_type=abstract

Ph.D. Thesis Stanford Univ., CA.

Physics

Orbit Calculation, Perturbation, Power Limited Spacecraft, Spacecraft Trajectories, Trajectory Analysis, Trajectory Optimization, Earth Gravitation, Gravitational Fields, Iterative Solution, Moon, Thrust, Transfer Orbits

Scientific paper

Minimum fuel trajectories for low-thrust power-limited spacecraft are investigated. The Pole Squatter mission involves an orbit transfer in Earth's gravity field. Edelbaum's orbit averaging method is used and Marec's analytical solution for the co-latus rectum transfer, as well as the numerically obtained globally optimal transfer are studied. In a mission to Lagrange points L(sub 4) and L(sub 5) Moon's perturbations must be considered. A numerical iterative procedure is started using an analytical approximation for a nearly circular spiral. Optimal Earth-Moon transfer is obtained by patching Earth and Moon spirals on the sphere of influence. The solution of the previous problem serves as a starting point for the iterative procedure. Typical results for the trajectories and for the thrust acceleration variations during the transfer are shown.

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