An energy approach for orbital transfers

Abstract

Evaluating the energy change in an orbital transfer vehicle due to its propulsion system provides an approach for solving a variety of transfer problems and expressing results in common propulsion terms. A high-thrust geosynchronous mission is given as an example to demonstrate one application and for comparing low-thrust results. Solutions to low-thrust ion engine transfers are developed by equating work performed to total energy change. Low-thrust plane changes are also analyzed. Using the energy approach, orbital transfer problems are analogous to certain classical problems in mechanics.