Low-thrust Optimal Trajectories for Rendezvous with Near Earth Asteroids
Abstract
The interest of the scientific community for small bodies has been growing for the last decades. A direct consequence is the number of missions or projects envisaged by national space agencies considering asteroids and comets as potential targets. We can quote for example NEAR to asteroid Eros and ROSETTA to comet 67P/Churyumov-Gerasimenko. A crucial point for the mission design is the cost, in terms of propellant requirement. Some interesting bodies, indeed, may not be reached by means of classical chemical propulsion because of the propellant mass having to be loaded on board. In this framework, the use of electric propulsion allows to consider either targets needing a lot of energy to be reached or multiple targets in a one way mission. Moreover, the computation of low-thrust optimal trajectories is a very complex task. The solution of the associated optimal control problems is done by combined means of the maximum principle, non-classical smoothing techniques and decomposition-coordination methods. After the general formulation and definition of the problems, we will present different optimal trajectories to various targets (such as Orpheus, Anteros, 1999FG3…) including the Earth escape phase and the heliocentric cruise. Complex options with flyby of intermediate asteroids or with gravity assist of the Earth are also proposed.
- Publication:
-
18th International Symposium on Space Flight Dynamics
- Pub Date:
- 2004
- Bibcode:
- 2004ESASP.548..481B