Mission opportunities for the flight validation of the kinetic impactor concept for asteroid deflection

被引：8

作者：

Hernandez, Sonia ^{[1
]}

Barbee, Brent W. ^{[2
]}

Bhaskaran, Shyam ^{[3
]}

Getzandanner, Kenneth ^{[2
]}

机构：

[1] Univ Texas Austin, Austin, TX 78712 USA

[2] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA

[3] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA

来源：

ACTA ASTRONAUTICA | 2014年 / 103卷

关键词：

Kinetic impact; Asteroid deflection; Mission design; SPACECRAFT; DESIGN;

D O I：

10.1016/j.actaastro.2014.04.013

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

The kinetic impactor technique for deflecting near-Earth objects (NEOs), whereby a spacecraft is directed to collide with a NEO to alter its orbit via momentum transfer, is one of several proposed methods for defending Earth against hazardous NEOs (asteroids and comets). In this paper we present detailed mission design concepts for a feasible and affordable kinetic impactor flight validation mission deployed to a currently known near-Earth asteroid (NEA). Several filter steps are devised that utilize relevant criteria to optimally balance key parameters, such as approach phase angle, estimated NEA diameter, relative velocity at intercept, and current NEA orbit knowledge, and produce refined lists of the most promising candidate target NEAs. (C) 2014 IAA. Published by Elsevier Ltd. All rights reserved.

引用

页码：309 / 321

页数：13

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