Mid Infrared Instrument cooler subsystem test facility overview

Cryogenic Engineering Conference 2017

材料科学;物理学

Moore, B.^1 ; Zan, J.^1 ; Hannah, B.^1 ; Chui, T.^1 ; Penanen, K.^1 ; Weilert, M.^1

Jet Propulsion Laboratory, California Institute of Technology, 4800 Oak Grove Dr, Pasadena

CA

91109, United States^1

关键词: Acceptance testing;    Compressor assembly;    Control electronics;    James Webb space telescope;    Mid infra-red instruments;    Subsystem test;    Thermal environment;    Thermal regions;   

Others  :  https://iopscience.iop.org/article/10.1088/1757-899X/278/1/012006/pdf
DOI  :  10.1088/1757-899X/278/1/012006

学科分类：材料科学（综合）

来源: IOP

【 摘 要 】

The Cryocooler for the Mid Infrared Instrument (MIRI) on the James Webb Space Telescope (JWST) provides cooling at 6.2K on the instrument interface. The cooler system design has been incrementally documented in previous publications [1][2][3][4][5]. It has components that traverse three primary thermal regions on JWST: Region 1, approximated by 40K; Region 2, approximated by 100K; and Region 3, which is at the allowable flight temperatures for the spacecraft bus. However, there are several sub-regions that exist in the transition between primary regions and at the heat reject interfaces of the Cooler Compressor Assembly (CCA) and Cooler Control Electronics Assembly (CCEA). The design and performance of the test facility to provide a flight representative thermal environment for acceptance testing and characterization of the complete MIRI cooler subsystem are presented.