Mathematics
Scientific paper
Oct 1982
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1982dsj....32..303s&link_type=abstract
Defence Science Journal, vol. 32, Oct. 1982, p. 303-312.
Mathematics
Flight Time, Interplanetary Transfer Orbits, Orbital Rendezvous, Rendezvous Trajectories, Rocket Flight, Trajectory Optimization, Circular Orbits, Eccentric Orbits, Elliptical Orbits, Gravitational Fields, Interception, Mathematical Models, Orbit Calculation
Scientific paper
A numerical model for the optimum trajectory for a commuter rocket to follow in order to rendezvous with a destination rocket vehicle is presented. The interceptor is launched from a launch orbit, then receives a specific velocity impulse at some point along the course to achieve the meeting. An optimum exit path from the launch orbit is characterized by minimum fuel expenditure, as is the intermediate-point velocity injection. Calculations are made of the flight durations and the launch angle, and elements of an optimum transfer trajectory for a rendezvous are defined. Sample calculations are presented for a rendezvous between a circular and an elliptical orbit, and for a meeting somewhere between earth and Mars.
Nangia A. K.
Srivastava T. N.
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