
Accession Number : ADA314771
Title : Optimal ContinuousThrust Orbit Transfers.
Descriptive Note : Doctoral thesis,
Corporate Author : AIR FORCE INST OF TECH WRIGHTPATTERSON AFB OH
Personal Author(s) : Thorne, James D.
PDF Url : ADA314771
Report Date : JUN 1996
Pagination or Media Count : 103
Abstract : The minimum time orbital transfer problem for spacecraft with steerable, continuous thrust of constant magnitude may be solved using EulerLagrange theory, which leads to the optimal control law in terms of Lagrange multipliers. However, the initial values of the Lagrange multipliers are not known from the orbital boundary conditions. Using analytical and empirical results, the optimal initial costates are modeled as functions of the problem parameters which are the initial thrust acceleration, A, and the final orbit radius, H, in canonical units. For circle to circle, coplanar orbit transfers, these approximate initial costate models lead to convergence in the shooting method for all practical values of A and H. The models also lead to convergence for a wide rang of other problems, including circle to hyperbola transfers and noncoplanar transfers. To counter the extreme sensitivity to small changes in the initial costate conditions, a dynamic step limiter is introduced which improve the convergence properties.
Descriptors : *CELESTIAL MECHANICS, *TRANSFER TRAJECTORIES, DYNAMICS, ACCELERATION, THESES, CONVERGENCE, CONTROL THEORY, SPACECRAFT TRAJECTORIES, THRUST, RADIUS(MEASURE), LAGRANGIAN FUNCTIONS.
Subject Categories : Spacecraft Trajectories and Reentry
Distribution Statement : APPROVED FOR PUBLIC RELEASE