Optimum two-impulse transfers for preliminary interplanetary trajectory design

Details Optimum two-impulse transfers for preliminary interplanetary trajectory design Optimum two-impulse transfers for preliminary interplanetary trajectory design

Aug 1984

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1984jgcd....7..458h&link_type=abstract

Journal of Guidance, Control, and Dynamics (ISSN 0731-5090), vol. 7, July-Aug. 1984, p. 458-461.

Physics

2

Interplanetary Trajectories, Space Flight, Trajectory Optimization, Transfer Orbits, Anomalies, Asteroids, Gravitational Fields

Scientific paper

A method for numerically determining the optimum two-impulse transfer between two positions in two different heliocentric orbits is described. The formulas are based on earlier work by McCue and Bender (1965) for optimum two-impulse transfers between two orbits about the earth. The contours of minimum total Delta-V(Delta-V to launch plus Delta-V to achieve a given final orbit at the target body) are plotted on axes of true anomaly of the launch body at launch and true anomaly of the target body at arrival. The optimum transfers obtained are 'time-open' and the Delta-V from the initial orbit to the final orbit is found using patched conics. These 'prime rib' plots are useful for selecting initial conditions in the early phases of mission design.

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