Abstract
The Origins Space Telescope’s orders-of-magnitude improvement over the scientific capabilities of prior infrared (IR) missions is based on its cold telescope (4.5 K) combined with low-noise far-IR detectors and ultra-stable mid-IR detectors. A number of trades were made in favor of a design with staged cooling, avoiding warm objects in the cold zones and minimizing the number of deployments and their complexity. The result is an architecture that is easily to analyze thermally and straightforward to test in existing facilities.
Highlights
The Origins Space Telescope (Origins) study is one of four potential astrophysics flagship missions commissioned by NASA Headquarters for inclusion in the 2020 Astrophysics Decadal Survey.[1]
DiPirro et al.: Origins Space Telescope cryo-thermal system because the cryocooler size is closer to those already developed,[4] if less cryocooling is required, it is easy to remove a cryocooler, and individual cooling heads may be positioned in several places on the telescope and instrument mounting surfaces to provide local heat sinks and minimize thermal straps
Trades performed on the Origins configuration emphasized simplicity, minimum deployments and ease of modeling.[9]
Summary
The Origins Space Telescope (Origins) study is one of four potential astrophysics flagship missions commissioned by NASA Headquarters for inclusion in the 2020 Astrophysics Decadal Survey.[1]. Four similar cryocoolers provide cooling to the observatory at three different temperatures: 4.5 K for the telescope, baffle, and instruments, 20 K as a radiative and conductive heat intercept between 35 K and 4.5 K, and 70 K as a conductive heat intercept along the barrel bipods. DiPirro et al.: Origins Space Telescope cryo-thermal system because the cryocooler size is closer to those already developed,[4] if less cryocooling is required, it is easy to remove a cryocooler, and individual cooling heads may be positioned in several places on the telescope and instrument mounting surfaces to provide local heat sinks and minimize thermal straps. An ejectable cover is included in the design for three purposes: to protect the mirrors during shipment and handling, to stiffen the barrel and baffle during launch, and to protect the sensitive telescope and detectors from exposure to the Sun during the early phase of the mission. After the first spacecraft thruster firing, the cover is ejected by a mechanism similar to that used on Spitzer
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