Accession Number : AD0859711

Title :   Time-Optimal Rendezvous From a Circular Orbit Using a Thrust-Limited Rocket.

Descriptive Note : Master's thesis,

Corporate Author : AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING

Personal Author(s) : Bryner, Glenn H.

Report Date : MAY 1969

Pagination or Media Count : 62

Abstract : The time-optimal rendezvous problem is solved for the case of specified final mass. Pontryagin's maximum principle gives the necessary conditions for existence of the optimal controls (thrust magnitude and direction). The generalized Newton-Raphson algorithm is used to numerically solve the problem. The optimal trajectory for the rendezvous point considered has three thrust phases: maximum, zero, and maximum thrust, in that order. When the Newton-Raphson method is applied to the problem with range angle as independent variable, the solution approximation must be quite good for convergence. Changes in the switching point locations must be restricted to achieve convergence. (Author)

Descriptors :   (*RENDEZVOUS TRAJECTORIES, OPTIMIZATION), THRUST, CIRCULAR ORBITS, COMPUTER PROGRAMS, THESES.

Subject Categories : Spacecraft Trajectories and Reentry

Distribution Statement : APPROVED FOR PUBLIC RELEASE