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Minimum-Time Low-Thrust Rendezvous Using Epoch Mean Longitude Formulation*
Jean Albert Kechichian**
Abstract
The problem of minimum-time rendezvous using a set of nonsingular elements involving the mean longitude at epoch is presented. The continuous constant acceleration is optimized in direction and the appropriate boundary conditions developed for the optimizer Both state and adjoint equations are explicit functions of time in this formulation that Involves natural orbital elements. The optimal Hamiltonian is also varying in time, but a certain transversality condition is shown to be constant for the entire duration of the transfer The shooting method coupled with a quasi-Newton scheme solves the two-point boundary value problem and generates the exact numerically integrated trajectory.
*This work was supported by the U.S. Air Force Space and Missle Systems Center under Contract No. F-04701-88-C-0089
**Engineering Specialist, Flight Dynamics Department, The Aerospace Corporation, MS M4-942 P.O. Box 92957 Los Angeles California 90009. Member AAS