LAUNCH VEHICLE PERFORMANCE REQUIREMENTS FOR RENDEZVOUS WITH SATELLITES IN 200-NAUTICAL MILE CIRCULAR POLAR ORBITS
Abstract
A detailed analysis is presented of direct ascent rendezvous with polar orbits, illustrating quantitatively the effects of range angle, launch azimuth, and satellite epoch on the ascent trajectory and the performance required of the launch vehicle. The total ideal velocity capability required of the launch vehicle to achieve gross rendezvous with satellites in 200nautical mile circular polar orbits was determined as a function of the launch azimuth, the relative epoch of the orbit, and the pass on yhich rendezvous takes place. A direct ascent launch vehicle trajectory was assumed. Precision flight simulation techniques were used throughout except for the assumption of an impulsive adaptation maneuver. Launch window effects were not included; rather, the study was concerned with the selection and characteristics of nominal trajectories.
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 20, 1963
- Accession Number
- AD0422969
Entities
People
- G. L. Coates
Organizations
- The Aerospace Corporation