Physics
Scientific paper
Aug 1989
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1989jgcd...12..487p&link_type=abstract
Journal of Guidance, Control, and Dynamics (ISSN 0731-5090), vol. 12, July-Aug. 1989, p. 487-494.
Physics
2
Ascent Trajectories, Circular Orbits, Interception, Trajectory Optimization, Equatorial Orbits, Lunar Orbits, Planetary Orbits, Planetary Rotation
Scientific paper
Minimum-fuel, impulsive, time-fixed solutions are obtained for the problem of direct-ascent interception of a target in circular orbit from a launch point on the surface of a planet or moon. Both a nonrotating and rotating planet are considered, as well as coplanar (launch point in target orbital plane) and noncoplanar cases. In the rotating planet model, the target orbit plane is assumed to be equatorial. Atmospheric effects are neglected, and the planet surface constraint is included. Primer vector theory is used to obtain the optimal solutions, which often include an initial coast interval prior to the first thrust impulse. Optimal intercept solutions obtained include both one- and two-impulse posigrade and retrograde trajectories. Solutions are obtained for a range of fixed transfer times, target orbit radii and inclinations, and initial target phase angles relative to the launch point.
Heckathorn William G.
Prussing John E.
Wellnitz Linda J.
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