Thrusting trajectory minimization program for orbital transfer maneuvers /

"A computer program has been designed which determines the minimum-burn-time, thrusting, transfer trajectory between two Keplerian orbits. The minimization equations are formulated with constant Lagrange multipliers and solved numerically with the Newton-Raphson method. The solution obtained in this paper is not truly optimum because the control vector has been restricted to constant values (i.e., to be optimum the control vector should be a function of time)."--P. [i]."L-7440.""NASA TN D-6120.""June 1971."Includes bibliographical references (p. 33)."A computer program has been designed which determines the minimum-burn-time, thrusting, transfer trajectory between two Keplerian orbits. The minimization equations are formulated with constant Lagrange multipliers and solved numerically with the Newton-Raphson method. The solution obtained in this paper is not truly optimum because the control vector has been restricted to constant values (i.e., to be optimum the control vector should be a function of time)."--P. [i].Sponsored by the National Aeronautics and Space Administration (NASA); performed by the NASA Langley Research Center under work unit no. 815-10-01-20.Mode of access: Internet