The Wide-Field Infrared Survey Explorer (WISE) is a JPL-managed MIDEX mission to perform an infrared all-sky
survey. The WISE instrument, developed by the Space Dynamics Laboratory (SDL), is a 40-cm cryogenically-cooled
telescope which includes a cryogenic scan mirror and four infrared focal planes (2-HgCdTe, 2-Si:As). Cooling the
instrument to the desired temperatures is accomplished by a two-stage, solid hydrogen cryostat, provided by Lockheed
Martin Advanced Technology Center (LMATC). Required temperatures for the instrument optics and Si:As focal planes
are <13 K and <7.6 K respectively. To reduce heat loads, the vacuum shell is isolated from the spacecraft bus via
composite struts and radiatively cooled to <200 K. The telescope aperture is protected from on-orbit environmental loads
via a two-stage radiatively cooled aperture shade. WISE was successfully launched into a 530 km, polar orbit on
December 14, 2009, beginning a 10-month mission to survey the entire sky in the infrared.
The Wide-Field Infrared Survey Explorer (WISE) is a MIDEX mission that is being developed by the Jet Propulsion Laboratory (JPL) to address several of NASA's Astronomical Search of Origins (ASO) objectives. Space Dynamics Laboratory/ Utah State University is providing the cryogenically cooled infrared instrument. Cooling for the instrument optics and focal planes is provided by a dual-stage solid hydrogen cryostat. Driving requirements for the cryogenic
subsystem are: a seven-month lifetime and operating temperatures of less than 17 K for the optics, 32 K for the HgCdTe focal planes, and 7.8 K for the Si:As focal planes. This paper provides an overview of the dual-stage hydrogen cryogenic subsystem status and discusses the results of the thermal performance testing.
The Wide-Field Infrared Survey Explorer (WISE) is a MIDEX mission that is being developed by the Jet Propulsion Laboratory (JPL) to address several of NASA's Astronomical Search of Origins (ASO) objectives. The WISE instrument, developed by the Space Dynamics Laboratory (SDL), includes a cryogenically cooled telescope (at < 13K) and four focal plane assemblies (2 at 7.6K, 2 at 32K). Cooling of the instrument is accomplished by a dual-stage solid hydrogen cryostat that is developed by the Lockheed Martin Advanced Technology Center (LM-ATC). This paper provides a combined overview of the WISE cryostat design and thermal support system.
For the past several years, cryogenically cooled sensors have become a popular method of observation and study for both space-based and ground-based operations. Accordingly, various cooling techniques have been developed to accommodate this group of sensors. Because of rising performance standards and escalating cost limitations, cryocoolers have become an impressive cooling technique to consider. This report focuses on the use of a mechanical cryocooler in conjunction with the Russian American Observational Satellites (RAMOS). RAMOS consists of two co- orbital satellites which will map using infrared radiometers. The telescope focal plane assembly will be cooled using a multiple cryocooler configuration to approximately 60 K. The use of multiple coolers introduces redundancy into the cooling system. The cooling system will also incorporate various other new technologies, such as thermal disconnects, a thermal storage unit, and low- resistance flexible thermal links to meet the overall system requirements. Incorporating thermal switches and thermal storage units into a cooling system design can alleviate the concerns of cryocooler vibration and parasitic heat loads from the redundant cooler. An understanding of these concepts and configurations will assist in the design of similar optical instruments for both space-based and ground- based exploration campaigns.
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