| An algorithm to improve the computational efficiency of the low-thrust escape trajectory is developed. The algorithm reduces computational effort while maintaining accuracy, making it desirable for use in computing optimal escape trajectory by direct method. As low-thrust ionic propulsion engines are considered for use in interplanetary missions, design and planning includes the optimization of the spacecraft trajectory. The low-thrust escape phase evolves in the form of a slowly unwinding spiral. The computational expense required to accurately propagate the dense spiraling trajectory of the planetocentric escape phase through the numerical integration of the ordinary differential equations is undesirable. Implementation of an algorithm that approximates the trajectory while maintaining accuracy and improving computational efficiency is beneficial. The algorithm developed is demonstrated with the optimization of a sample Earth-escape trajectory. An inexpensive trajectory calculation with little error is produced. |
