Optimal finite-thrust spacecraft trajectories using collocation and nonlinear programmingA new method is described for the determination of optimal spacecraft trajectories in an inverse-square field using finite, fixed thrust. The method employs a recently developed optimization technique which uses a piecewise polynomial representation for the state and controls, and collocation, thus converting the optimal control problem into a nonlinear programming problem, which is solved numerically. This technique has been modified to provide efficient handling of those portions of the trajectory which can be determined analytically, i.e., the coast arcs. Among the problems that have been solved using this method are optimal rendezvous and transfer (including multirevolution cases) and optimal multiburn orbit insertion from hyperbolic approach.
Document ID
19900059728
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Enright, Paul J. (Illinois Univ. Urbana, IL, United States)
Conway, Bruce A. (Illinois, University Urbana, United States)