The customer (scientist or project manager) most often does not want just one point solution to the mission design problem Instead, an exploration of a multi-objective trade space is required. For a typical main-belt asteroid mission the customer might wish to see the trade-space of: Launch date vs. Flight time vs. Deliverable mass, while varying the destination asteroid, planetary flybys, launch year, etcetera. To address this question we use a multi-objective discrete outer-loop which defines many single objective real-valued inner-loop problems.
Multi-Objective Hybrid Optimal Control for Multiple-Flyby Interplanetary Mission Design Using Chemical Propulsion
2015
24 pages
Report
Keine Angabe
Englisch
Astronautics , Spacecraft Trajectories & Flight Mechanics , Design analysis , Optimal control , Interplanetary trajectories , Flyby missions , Asteroid missions , Chemical propulsion , Jupiter (planet) , Gravitation , Swingby technique , Nonlinear programming , Trajectories , Flight time , Launch dates , Spacecraft launching , Mission planning