This paper investigates the solution of Lamberts Problem for targets in elliptical orbits. A mission design software framework to determine the optimal interplanetary trajectory and final capture orbit based on mission constraints and requirements between a departure and arrival body has been developed. Integration of a trade space visualization tool, such as the Applied Research Laboratory Trade Space Visualizer software permits a mission designer to visually inspect the multi-dimensional trade space and investigate regions of feasible trajectories. This analysis process can provide a mission designer with the capability to reduce the amount of time needed to design interplanetary trajectories by reducing the number of feasible solutions that would need to be investigated.
|Original language||English (US)|
|Number of pages||15|
|State||Published - May 1 2016|
All Science Journal Classification (ASJC) codes
- Aerospace Engineering