On-orbit transfer trajectory methods using high fidelity dynamic models.

摘要

A high fidelity trajectory propagator for use in targeting and reference trajectory generation is developed for aerospace applications in low Earth and translunar orbits. The dominant perturbing effects necessary to accurately model vehicle motion in these dynamic environments are incorporated into a numerical predictor-corrector scheme to converge on a realistic trajectory incorporating multi-body gravitation, high order gravity, atmospheric drag, and solar radiation pressure. The predictor- corrector algorithm is shown to reliably produce accurate required velocities to meet constraints on the final position for the dominant perturbation effects modeled. Low fidelity conic state propagation techniques such as Lambert's method and multiconic pseudostate theory are developed to provide a suitable initial guess. Feasibility of the method is demonstrated through sensitivity analysis to the initial guess for a bounding set of cases.