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Proceedings Paper

Microprecision interferometer: pointing system solutions for on-orbit disturbance environment
Author(s): Frank G. Dekens; Gregory W. Neat
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Paper Abstract

The Space Interferometer Mission (SIM) is required to point each arm of its science interferometer to better than 30 milli-arcseconds (mas) RMS residual jitter using a 0.01 Hz bandwidth optical sensor on the star. We address the residual pointing error due to the spinning spacecraft reaction wheel assemblies which emit disturbances from 2 Hz to 1 kHz. The vibration attenuation strategy for this 'blind' pointing problem is to isolate each reaction wheel assembly with a vibration isolation system and to possibly augment the low bandwidth closed loop system with an internal high bandwidth sensor. Central to estimating the high frequency pointing error is the Micro-Precision Interferometer (MPI) testbed which is a softly suspended hardware model of a spaceborne optical interferometer and is dimensionally representative of SIM. Using the testbed and a transfer function-based performance prediction algorithm, we show that the 30 mas requirement is missed by a factor of six when only employing a six-axis active vibration isolator made by TRW. In preparation for augmenting the vibration attenuation strategy, we also show that the primary contributor to the tip-tilt jitter error is the first optic in the interferometer's optical train.

Paper Details

Date Published: 22 June 2000
PDF: 8 pages
Proc. SPIE 3985, Smart Structures and Materials 2000: Smart Structures and Integrated Systems, (22 June 2000); doi: 10.1117/12.388841
Show Author Affiliations
Frank G. Dekens, Jet Propulsion Lab. (United States)
Gregory W. Neat, Jet Propulsion Lab. (United States)

Published in SPIE Proceedings Vol. 3985:
Smart Structures and Materials 2000: Smart Structures and Integrated Systems
Norman M. Wereley, Editor(s)

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