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NEOTωIST – Design Study of a Kinetic Impactor Demonstration Mission Featuring NEO Spin Change and Observer Sub-spacecraft

Engel, K. and Pugliatti, Mattia and Drube, Line and Hestroffer, Daniel and Cano, J. L. and Delchambre, Simon and Ziegler, Tobias and Johann, Ulrich and Harris, Alan (2017) NEOTωIST – Design Study of a Kinetic Impactor Demonstration Mission Featuring NEO Spin Change and Observer Sub-spacecraft. Planetary Defence Conference 2017, 15-19. May 2017, Tokyo, Japan.

[img] PDF (Conference Abstract)


Near Earth Object (NEO) deflection for the purpose of Earth impact prevention is recognized as a valid and valuable endeavour. NEOTωIST stands for Near-Earth Object Transfer of angular momentum (ω) Spin Test. This describes a demonstration mission intended to develop the capabilities required to execute an effective kinetic impactor NEO deflection mission. The mission concept features several novel aspects. The most important of these are a new technique to quantify momentum transfer from the Impactor spacecraft to the NEO, and the option to use small sub-spacecraft for observation purposes. For momentum transfer measurement, the NEO is struck off-center which changes its spin rate. This rate change, which can be measured from Earth via light curve measurements, allows quantification of the transferred momentum without the need for a rendezvousing observer spacecraft. To gain additional information about the impact geometry and impact physics, the NEOTωIST Impactor may deploy one or several sub-spacecraft from the main Impactor spacecraft shortly before impact. These sub-spacecraft allow observation of the impact event from multiple vantage points some of which are unique because their destruction is accepted. Different mission variations exist depending on whether the mission is implemented with only the Impactor or with a complement of observing sub-spacecraft. The paper discusses these options. Overall, the concept promises comparatively low cost and features capabilities that are unique and valuable for an operational deflection or reconnaissance mission. The overall mission concept and measurement principle are described in detail in a different abstract by L. Drube et al. This paper focuses on the results of a preliminary mission design study with the objective of demonstrating mission feasibility. It analyses the key technical challenges of the mission, and describes the concept of operations as well as geometry design for the impact and fly-by phase of the mission. Further, the communications architecture between the different spacecraft and Earth is discussed, and the preliminary design of the individual spacecraft is presented.

Item URL in elib:https://elib.dlr.de/111689/
Document Type:Conference or Workshop Item (Speech)
Title:NEOTωIST – Design Study of a Kinetic Impactor Demonstration Mission Featuring NEO Spin Change and Observer Sub-spacecraft
AuthorsInstitution or Email of AuthorsAuthor's ORCID iDORCID Put Code
Engel, K.airbus d&s, friedrichshafen, germanyUNSPECIFIEDUNSPECIFIED
Pugliatti, Mattiadepartment of aerospace engineering, delft university of technologyUNSPECIFIEDUNSPECIFIED
Drube, LineUNSPECIFIEDhttps://orcid.org/0000-0003-2486-8894UNSPECIFIED
Hestroffer, Danielobservatoire de paris, franceUNSPECIFIEDUNSPECIFIED
Ziegler, Tobiasastrium, friedrichshafenUNSPECIFIEDUNSPECIFIED
Johann, Ulrichastrium friedrichshafenUNSPECIFIEDUNSPECIFIED
Harris, AlanUNSPECIFIEDhttps://orcid.org/0000-0001-8548-8268UNSPECIFIED
Refereed publication:No
Open Access:Yes
Gold Open Access:No
In ISI Web of Science:No
Keywords:Near Earth Objects, NEO, asteroids, deflection mission
Event Title:Planetary Defence Conference 2017
Event Location:Tokyo, Japan
Event Type:international Conference
Event Dates:15-19. May 2017
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Space
HGF - Program Themes:Space Exploration
DLR - Research area:Raumfahrt
DLR - Program:R EW - Space Exploration
DLR - Research theme (Project):R - Vorhaben Planetary Evolution and Life (old)
Location: Berlin-Adlershof
Institutes and Institutions:Institute of Planetary Research > Leitungsbereich PF
Deposited By: Drube, Line
Deposited On:20 Jul 2017 14:25
Last Modified:20 Jun 2021 15:49

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