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LISA Propulsion Module Separation StudyThe Laser Interferometer Space Antenna (LISA) mission is a space-borne gravitational wave detector consisting of three spacecraft in heliocentric orbit. Each spacecraft is delivered to it operational orbit by a propulsion module. Because of the strict thermal and mass balancing requirements of LISA, the baseline mission concept requires that the propulsion module separate from the sciencecraft after delivery. The only propulsion system currently baselined for the sciencecraft are micronewton level thrusters, such as FEEP or colloid thrusters, that are used to balance the 30-40 microN of solar radiation pressure and provide the drag-free and attitude control of the spacecraft. Due to these thrusters limited authority, the separation of the propulsion module from the sciencecraft must be well controlled to not induce a large tip-off rotation of the sciencecraft. We present here the results of a design study of the propulsion module separation system that is shown to safely deliver the LISA sciencecraft to its final operational orbit.
Document ID
20040082154
Acquisition Source
Headquarters
Document Type
Conference Paper
Authors
Merkowitz, Stephen
(NASA Goddard Space Flight Center Greenbelt, MD, United States)
Date Acquired
August 21, 2013
Publication Date
January 1, 2004
Subject Category
Instrumentation And Photography
Meeting Information
Meeting: 5th International LISA Symposium
Location: Noordwijk
Country: Netherlands
Start Date: July 12, 2004
End Date: July 16, 2004
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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