An Architecture for a Generalized Spacecraft Trajectory Design and Optimization System

The elements of a general high precision system for trajectory design and optimization for single or multiple spacecraft using one or more distinct propulsion systems, and operating in any gravitational environment within the solar system are discussed. The system architecture attempts to consolidate most all spacecraft trajectory design and optimization problems by using a single framework that requires solutions to either a system of nonlinear equations or a parameter optimization problem with general equality and/or inequality constraints. The use of multiple reference frames that generally translate, rotate, and pulsate between two arbitrary celestial bodies facilitates the analysis of multiple celestial body force field trajectories such as those associated with libration point missions, cycling trajectories between any set of celestial bodies, or any other type of trajectory or mission requiring the use of multiple celestial bodies. A basic trajectory building block, referred to as the basic segment, that can accommodate impulsive maneuvers, maneuver and non-maneuver based mass discontinuities, and finite burn or finite control acceleration maneuvers, is used to construct single or multiple spacecraft trajectories. The system architecture facilitates the modeling and optimization of a large range of problems ranging from single spacecraft trajectory design around a single celestial body to complex missions using multiple spacecraft, multiple propulsion systems, and operating in multiple celestial body force fields.