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Thermostabilization Devices for Spacecrafts

#0785


Advanced Thermostabilization System of Devices for High Power Spacecraft

Tech Area / Field

  • SAT-VEC/Space Vehicles and Support Equipment/Space, Aircraft and Surface Transportation

Status
3 Approved without Funding

Registration date
05.11.1996

Leading Institute
Scientific and Technical Center ELECTROCOSMOS, Russia, Moscow

Supporting institutes

  • Plant of Electro-Mechanical Equipment , Russia, Moscow reg., Protvino\nState Enterprise Krasnaya Zvezda, Russia, Moscow

Project summary

The design purpose - are the investigation and development of node, based on heat pipes for the formation of the heat regime condition system (HRCS) for high power spacecraft. HRCS must provide required temperature range of the equipment functioning, must be simple and safe, not to require energy waste, its functioning must be automatically without using management systems. On the ground of the investigation of various selected schematic diagrams and performed thermal calculations advanced diodes and temperature controls constructions should be created, which performance should be confirmed in surface condition including external influence, based on specially developed program, which results may be used in space condition.

Engineering approach

Changing of the heat pipes performance by the transmission is based on changing of the balance of the arranging capillary head and hydraulic wastes in the circulation contour of the heat pipes. The increase of the hydraulic wastes in the heat pipe contour causes the decrease of the length of the heat supply zone, watered by the heat transport medium. The heat control calculation is based on this fact. The diode functioning is based on sharp increase of the thermal resistance by the back heat streaming, achieving at the expense of the recondensation of the working medium and at the expense of the dewater of the heat supply zone. The diode "operation energy", i.e. the quantity of the transmitting heat by the recondensation, is determined by integration including changing thermal resistance in supply zone of the back heat streaming.

Design essence consists in the design engineering of the specific HRCS components, never used before, and in experimental confirmation of its performances.

Commercial exploitation. The HRCS application for high power spacecraft, using our present design, will increase safe operating, of the devices, will increase the working resource of the objects. It will cause the interest of firms in using the results of the present design.


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