Titlebook: Cryocoolers 8; R. G. Ross Book 1995 Springer Science+Business Media New York 1995 Pet.Superconductor.Vibration.cryogenics.development.eart

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Sara Buttsworth,Maartje Abbenhuispressors coupled to two 10-mm displacers via transfer tubes. It is required to produce 2W of thermal cooling at an instrument interface temperature of 65K for less than 100W of input power into the cryocooler’s controller. The controller uses Lockheed’s proprietary Digital Error Correction (DECS) co

BLOT

Sara Buttsworth,Maartje Abbenhuisn the AXAF X-ray Spectrometer/Cryogenic Subsystem (XRS/CSS)..The cryocooler incorporates the basic Oxford heritage cryocooler design acquired by Ball from Rutherford Appleton Laboratory. Two opposed compressors are connected to a momentum compensated single-stage integral displacer/regenerator coldh

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Simon Heywood,Shonaleigh CumbersOS-AM1 platform in 1998. The mission instrument consists of a visible and near-infrared radiometer (VNIR), a shortwave infrared radiometer (SWIR) and a thermal infrared radiometer (TIR). Two cryocoolers are included to cool the infrared detectors for SWIR and TIR. The mission life of the EOS-AM1 pla

sundowning

https://doi.org/10.1007/978-981-10-2684-3aneously cooling capacities of 1 Watt at 50 K and 5 Watts at 190 K, with maximum efficiency. An original technology using hydrodynamic gas bearings and clearance seals for contactless operation has been developed and successfully assessed. A twin piston pressure oscillator and a two stage cold expan

FLOUR

M. K. Singh,C. L. Sharma,M. Sharmaan 50 W/W into the compressors. The design improves on the flexure spring and gas-gap seal design originally developed by Oxford University. Significant design improvements have been incorporated in the compressor and displacer, yielding improved cooling and efficiency, resulting in the measured per

生命层

M. K. Singh,C. L. Sharma,M. Sharmace sensors. These coolers are improved versions of the Hughes/Air Force/Phillips Laboratory developed 65K Standard Spacecraft Cryocooler. The ISSC is a split-Stirling cryocooler designed for 1.25 W of cooling at 60K. The ISSC coolers under test carry cold end loads of 600 mW at 60K and 832 mW at 60K

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assail

M. K. Singh,C. L. Sharma,M. Sharmaoddard Space Flight Center. Design requirements provide 0.8-W cooling at 80 K, while minimizing the specific power of the system and maintaining the exported vibration levels to less than 0.02 lb..The cryocooler design is based on the flexure spring and gas gap seal design originally developed by Ox

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