A solution to the asteroid deviation problem via a low-thrust strategy is proposed. This formulation makes use of the proximal motion equations and a semi-analytical solution of the Gauss planetary equations. The average of the variation of the orbital elements is computed, together with an approximate expression of their periodic evolution. The interception and the deflection phase are optimised together through a global search. The low-thrust transfer is preliminary designed with a shape based method; subsequently the solutions are locally refined through the Differential Dynamic Programming approach. A set of optimal solutions are presented for a deflection mission to Apophis, together with a representative trajectory to Apophis including the Earth escape.
|Number of pages||16|
|Publication status||Published - 29 Sep 2008|
|Event||59th International Astronautical Congress - Glasgow, Scotland|
Duration: 29 Sep 2008 → 3 Oct 2008
|Conference||59th International Astronautical Congress|
|Period||29/09/08 → 3/10/08|
- near earth objects
- solar collector strategy
Colombo, C., Vasile, M., & Radice, G. (2008). Interception and deviation of near Earth objects via solar collector strategy. A3.I.06. Paper presented at 59th International Astronautical Congress, Glasgow, Scotland, .