Abstract
We present a formulation of a finite-dimensional optimization problem associated with the deflection of Earth-crossing asteroids. The performance measure is minimizing the delta-V requirement for achieving a minimum target separation distance. A number of astrodynamical constraints are identified and modeled. The constrained optimization problem is numerically solved using a sequential quadratic programming method. Our numerical analysis indicates that the minimum delta-V requirement is not a monotonically decreasing function of warning time; rather, there is a finer structure associated with the orbital period of the colliding asteroid. The analysis tool presented here may be used for optimizing the interceptor mission for impact mitigation.
Original language | English |
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Pages (from-to) | 415-420 |
Number of pages | 6 |
Journal | Journal of Guidance, Control, and Dynamics |
Volume | 22 |
Issue number | 3 |
DOIs | |
Publication status | Published - 1999 |
All Science Journal Classification (ASJC) codes
- Control and Systems Engineering
- Aerospace Engineering
- Space and Planetary Science
- Electrical and Electronic Engineering
- Applied Mathematics