Abstract
In this paper a number of deviation strategies for dangerous Near Earth Objects (NEO) have been compared. For each strategy (i.e. Solar Collector, Nuclear Blast, Kinetic Impactor, Low-thrust Propulsion, Mass Driver) a multi criteria optimisation method has been used to reconstruct the set of Pareto optimal solutions minimising the mass of the spacecraft and the warning time, and maximising the deviation. Then, a dominance criterion has been defined and used to compare all the Pareto sets. The achievable deviation at the MOID, either for a low-thrust or for an impulsive variation of the orbit of the NEO, has been computed through a set of analytical formulas. The variation of the orbit of the NEO has been estimated through a deviation action model that takes into account the wet mass of the spacecraft at the Earth. Finally the technology readiness level of each strategy has been used to compute a more realistic value for the required warning time.
| Original language | English |
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| Pages | AC-06-A3.5.8 |
| Number of pages | 13 |
| Publication status | Published - 2 Oct 2006 |
| Event | AIAA 57th International Astronautical Congress - Valencia, Spain Duration: 2 Oct 2006 → 6 Oct 2006 |
Conference
| Conference | AIAA 57th International Astronautical Congress |
|---|---|
| Country/Territory | Spain |
| City | Valencia |
| Period | 2/10/06 → 6/10/06 |
Keywords
- dangerous near earth objects
- solar collector
- nuclear blast
- kinetic impactor
- low thrust propulsion
- mass driver
- pareto optimal solutions