The NEOTωIST mission (Near-Earth Object Transfer of angular momentum spin test)

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• 作者：Line Drube^a ; ^{Line.Drube@dlr.de" class="auth_mail" title="E-mail the corresponding author}Author Vitae ; Alan W. Harris^a ; ^{Alan.Harris@dlr.de" class="auth_mail" title="E-mail the corresponding author}Author Vitae ; Kilian Engel^b ; ^{kilian.engel@airbus.com" class="auth_mail" title="E-mail the corresponding author}Author Vitae ; Albert Falke^b ; ^{albert.falke@airbus.com" class="auth_mail" title="E-mail the corresponding author}Author Vitae ; Ulrich Johann^b ; ^{ulrich.johann@airbus.com" class="auth_mail" title="E-mail the corresponding author}Author Vitae ; Siegfried Eggl^c ; ^{Siegfried.Eggl@obspm.fr" class="auth_mail" title="E-mail the corresponding author}Author Vitae ; Juan L. Cano^d ; ^{juan-luis.cano@deimos-space.com" class="auth_mail" title="E-mail the corresponding author}Author Vitae ; Javier Martí ; n Á ; vila^d ; ^{javier.martin@deimos-space.com" class="auth_mail" title="E-mail the corresponding author}Author Vitae ; Stephen R. Schwartz^e ; ^{srs@oca.eu" class="auth_mail" title="E-mail the corresponding author}Author Vitae ; Patrick Michel^e ; ^{michelp@oca.eu" class="auth_mail" title="E-mail the corresponding author}Author Vitae
• 关键词：DSNR ; Detection Signal-to-Noise Ratio ; FoM ; Figure of Merit ; NEO ; Near-Earth Object ; NEOTωIST ; Near-Earth Object Transfer of angular momentum (=ω*I) Spin Test ; LPF ; Lisa Pathfinder Propulsion module
• 刊名：Acta Astronautica
• 出版年：2016
• 出版时间：October-November 2016
• 年：2016
• 卷：127
• 期：Complete
• 页码：103-111
• 全文大小：1664 K

文摘

We present a concept for a kinetic impactor demonstration mission, which intends to change the spin rate of a previously-visited asteroid, in this case 25143 Itokawa. The mission would determine the efficiency of momentum transfer during an impact, and help mature the technology required for a kinetic impactor mission, both of which are important precursors for a future space mission to deflect an asteroid by collisional means in an emergency situation. Most demonstration mission concepts to date are based on changing an asteroid's heliocentric orbit and require a reconnaissance spacecraft to measure the very small orbital perturbation due to the impact. Our concept is a low-cost alternative, requiring only a single launch.

Taking Itokawa as an example, an estimate of the order of magnitude of the change in the spin period, δP, with such a mission results in δP of ~4 min (0.5%), which could be detectable by Earth-based observatories.

Our preliminary study found that a mission concept in which an impactor produces a change in an asteroid's spin rate could provide valuable information for the assessment of the viability of the kinetic-impactor asteroid deflection concept. Furthermore, the data gained from the mission would be of great benefit for our understanding of the collisional evolution of asteroids and the physics behind crater and ejecta-cloud development.