According to the requirements, the thermal control system must ensure the cooling of 10-m space telescope down to 4K and cooling of on-board instruments. That will be implemented by a combination of passive (sunshields) and active cooling (mechanical cryo coolers).
Critical points to achieve the requirements:
Implementation of this principle affects almost every aspect of the space observatory design to a greater or lesser degree, therefore thermal design drives structural design.
The observatory is equipped with large deployable sunshields to block the light and heat from the Sun, Earth, and Moon. Millimetron orbital position the Earth-Sun Lagrange point L2 keeps all three bodies on the same side of the spacecraft at all times, that maintains a constant thermal environment for the telescope. The sunshield system passively cools the telescope to the temperature level of 30-50K. Each sunshield consists of 2 layers of pretension two-sided aluminum-plated polyimide thin-films that are supported and 12 deployable spokes. The nearest to the primary mirror cryoshield will be connected to the 20K level of the mechanical coolers and cooled down to 20 K. It will have a different structure comparing to the sunshields.
A key moment for the thermal design of the Millimetron is to reduce the heat load for the stages of active cooling system operation. The dominant factor behind the heat load was the heat conduction through the basic structure. Two solutions were implemented: use the materials with low thermal conductivity and reduce the ratio of the cross-sectional area-to-length in truss elements. However, finding a solution was challenging since the main truss assembly must have sufficient stiffness and strength to support the payload module and its mass exceeding 3000 kg during the launch. Following launch, the primary mirror basic structure is required only to apply the loads associated with observatory operation: L2 orbit insertion, repointing, and station keeping. To reduce the thermal conductance of the basic structure, we have assumed that launch loads associated with the telescope and instruments will be applied via some detachable interface between cryogenic and warm parts of the basic structure.
A combination between active and passive cooling should be carefully designed by taking into account an appropriate margin of cooling capacity in each temperature level, because the active mechanical cooling is very expensive and complicated. Minimization of active mechanical cooling reduces cost and risks of mission.
|Level||Radiation Exchange,W||Structure Conduction, W||Cable networkConduction*,W||Heat dissipation of instruments, W||ΣQ, W|
Pulse Tube Cooler PT15K
TRL5/6 (planned in 2019)
800mW at 20K
TRL5/6 (planned in 2019)
4K-class Joule Thomson cooler
40mW at 4.5K (EOL)
90 W at EOL
> 3 years (5years as a goal)
1K-class Joule Thomson cooler
10mW at 1.7K (EOL)
19mW at 1.77K (with PT15K precooling)
(with PT15K precooling)
75 W at EOL
Engineering model of the sunshields deployment system
Full scale mock-up of cryoshield
Thermal model (Scale 1:10)
The cryogenic test in the vacuum chamber