Reduction of flight hardware outgassing after integration under a less stringent requirement

Details Reduction of flight hardware outgassing after integration under a less stringent requirement Reduction of flight hardware outgassing after integration under a less stringent requirement

Nov 1996

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1996spie.2864..235h&link_type=abstract

Proc. SPIE Vol. 2864, p. 235-245, Optical System Contamination V, and Stray Light and System Optimization, A. Peter M. Glassford

Physics

Optics

Scientific paper

In preparation for the Hubble Space Telescope (HST) second servicing mission, hardware which was assembled a decade earlier was refurbished and cleaned to meet a requirement more than an order of magnitude cleaner than the original requirement. The fine guidance sensor (FGS) radial bay module is located in ]close proximity to the HST science instruments; therefore the condemnation sensitivity of the second servicing mission science instruments necessitated the establishment of new FGS contamination requirements. These new requirements are based on a critical optics temperature of minus 88 degrees Celsius; the original FGS outgassing requirements were based on protecting the HST primary mirror, which has an average temperature of plus 10 degrees Celsius. A contamination reduction plan was devised, implemented, and refined, resulting in partial deintegration of the FGS, the use of molecular adsorbers, and the use of a bakeout temperature within 1 degree of Celsius of the maximum survival temperature of the hardware. Final contamination measurements are within 3% of the predicted levels and meet the second servicing mission contamination requirements.

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