Deflecting the orbit of a potentially hazard asteroid by kinetic impact is currently the most technically feasible defense concept.Finding the optimal interception orbit of the impactor to the asteroid so as to achieve the maximum orbit deflection under a given fuel consumption,is of great significance to the design of the defense scenario.This paper takes the kinetic impact on the Apophis asteroid as an example,a method to design the optimal interception trajectory of the impactor is proposed and illustrated.Firstly,the orbit deflection of the asteroid caused by impact is regarded as an impulse maneuver,and the motion of the asteroid is simplified into a two-body problem.Then,the optimal interception position and interception orientation of the impactor on the asteroid is determined using classical theories of orbital dynamics and control,which maximizes the orbit deflection of the asteroid for a given fuel consumption.Finally,a numerical orbit prediction model for Apophis is established,which is used to evaluate the actual orbit deflection of the optimal impact solution.The results show that orbit deflection given by optimal impact solution is basically consistent with the actual situation,which proves that the optimization method has a certain reference value for the design of elaborate impact schemes.
LI Tao
,
QIN Jin-gui
,
REN Lei-sheng
,
LI Yi
. Optimal Interception Orbit Analysis in the Kinetic Impact of Near Earth Asteroids[J]. Journal of Space Science and Experiment, 2021
, 21(4)
: 49
-54
.
DOI: 10.19963/j.cnki.2096-4099.2021.04.008
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