Launch Vehicle Performance Requirements for Rendezvous with Satellites in 200-Nautical Mile Circular Orbits of 60 Degrees Inclination

摘要

The total ideal velocity required of the launch vehicle to achieve gross rendezvous with satellites in 60-degree inclination, 200-nautical mile altitude circular orbits was determined as a function of the launch azimuth, the relative epoch of the orbit, and the pass on which rendezvous takes place.nA direct ascent launch vehicle trajectory was assumed. Precision flight simulation techniques were used throughout except for the assumption of an impulsive adaptation maneuver. The effects of liftoff time dispersions were not included;the study was rather con¬cerned with the selection and characteristics of nominal trajectories.