The Space Interferometry Mission, planned for launch in 2006, will measure the positions of celestial objects to an unprecedented accuracy of 4/spl times/10/sup -6/ are sec (about 1 billionth of a degree). In order to achieve this accuracy, which represents an improvement of almost two orders of magnitude over previous astrometric measurements, a ten-meter baseline interferometer will be flown in space. Starlight is collected by 33 cm diameter telescopes and combined to form fringes on detectors. To achieve the stated accuracy, the position of these fringes must be measured to a fraction of a wavelength of visible light. Passive vibration isolation and several layers of active control are used to stabilize the starlight wavefronts at sub-nanometer levels. Tight thermal control is coupled with very low CTE materials. Certain parts of the instrument need to be stabilized so that they move more slowly than the speed at which a baby grows.


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    Title :

    Space Interferometry Mission instrument mechanical layout


    Contributors:
    Aaron, K.M. (author) / Stubbs, D.M. (author) / Kroening, K. (author)


    Publication date :

    2000-01-01


    Size :

    1220579 byte





    Type of media :

    Conference paper


    Type of material :

    Electronic Resource


    Language :

    English



    Space Interferometry Mission Instrument Mechanical Layout

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    Space Interferometry Mission Instrument Mechanical Layout

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    Space Interferometry Mission: recent instrument configuration developments

    Aaron, K. M. / Stubbs, D. M. / Ames, L. et al. | NTRS | 2002


    6.0408 Space Interferometry Mission: Recent Instrument Configuration Developments

    Institute of Electrical and Electronics Engineers | British Library Conference Proceedings | 2002