Internal Thermal Control System Hose Heat Transfer Fluid Thermal Expansion Evaluation Test Report

NASA/TM-211330, Wieland, P.O. and Hawk, H.D., Internal Thermal Control System Hose Heat Transfer Fluid Thermal Expansion Evaluation Test Report, National Aeronautics and Space Administration, Washington, DC 20546-0001, George C. Marshall Space Flight Center Marshall Space Flight Center, AL 35812, Prepared by Flight Projects Directorate *Summer High School Apprenticeship Research Program, Marshall, October 2001, pp. 28, Format(s): PDF 21422k

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During assembly of the International Space Station, the Internal Thermal Control Systems in adjacent modules are connected by jumper hoses referred to as integrated hose assemblies (IHAs). A test of an IHA has been performed at the Marshall Space Flight Center to determine whether the pressure in an IHA filled with heat transfer fluid would exceed the maximum design pressure when subjected to elevated temperatures (up to 60 C (140 F)) that may be experienced during storage or transportation. The results of the test show that the pressure in the IHA remains below 227 kPa (33 psia)(well below the 689 kPa (100 psia) maximum design pressure) even at a temperature of 71 C (160 F), with no indication of leakage or damage to the hose. Therefore, based on the results of this test, the IHA can safely be filled with coolant prior to launch. The test and results are documented in this Technical Memorandum.

Keywords:	itcs, jumper hose, thermal control system
Subjects:	Astronautics: Spacecraft Design, Testing And Performance
ID Code:	582
Deposited On:	01 August 2002