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Spacecraft attitude impacts on COLD-SAT non-vacuum jacketed LH2 supply tank thermal performanceThe Cryogenic On-Orbit Liquid Depot - Storage, Acquisition and Transfer (COLD-SAT) spacecraft will be launched into low earth orbit to perform fluid management experiments on the behavior of subcritical liquid hydrogen (LH2). For determining the optimum on-orbit attitude for the COLD-SAT satellite, a comparative analytical study was performed to determine the thermal impacts of spacecraft attitude on the performance of the COLD-SAT non-vacuum jacketed LH2 supply tank. Tank thermal performance was quantified by total conductive and radiative heat leakage into the pressure vessel due to the absorbed solar, earth albedo and infra-red on-orbit fluxes, and also by the uniformity of the variation of this leakage on the vessel surface area. Geometric and thermal analysis math models were developed for the spacecraft and the tank as part of this analysis, based on their individual thermal/structural designs. Two quasi-inertial spacecraft attitudes were investigated and their effects on the tank performance compared. The results are one of the criteria by which the spacecraft orientation in orbit was selected for the in-house NASA Lewis Research Center design.
Document ID
19900013276
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Arif, Hugh (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 6, 2013
Publication Date
January 1, 1990
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
NASA-TM-103158
E-5525
NAS 1.15:103158
AIAA PAPER 90-1672
Meeting Information
Meeting: Joint Thermophysics and Heat Transfer Conference
Location: Seattle, WA
Country: United States
Start Date: June 18, 1990
End Date: June 20, 1990
Sponsors: ASME, AIAA
Accession Number
90N22592
Funding Number(s)
PROJECT: RTOP 506-48-21
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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