Accession Number : AD0774429
Title : An Investigation of Minimum Time, Launch-to-Rendezvous Trajectories.
Descriptive Note : Master's thesis,
Corporate Author : AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OHIO SCHOOL OF ENGINEERING
Personal Author(s) : Edelman,Steven H.
Report Date : DEC 1973
Pagination or Media Count : 71
Abstract : Minimum time trajectories between the surface of the Earth and a 270 statute mile circular orbit, generated with the assumption of impulsive thrusting, are used to determine minimum time-to-rendezvous with a target in the specified orbit. The amount of impulse is fixed by specifying the ratio of the launch vehicle's final to initial masses. The study is divided into two principal phases. In the orbit injection portion of the study, a set of minimum time orbit injection trajectories, subject to certain launch constraints, is generated by the solution of a fourth order polynomial for various range angles. The effect on the number of admissible trajectories of changing the mass ratio is also investigated. During the rendezvous phase of the study, the generated set of trajectories is used to determine a window for direct launch to rendezvous. (Modified author abstract)
Descriptors : *Manned spacecraft, *Rendezvous trajectories, Computer programs, Ascent trajectories, Optimization, Space stations, Safety, Computerized simulation, Theses
Subject Categories : Spacecraft Trajectories and Reentry
Distribution Statement : APPROVED FOR PUBLIC RELEASE