{"copyright":{"thirdPartyPermissionsProduced":false,"disclosedToPublic":false,"containsIndication":false,"publisherPermissionOrRightsToDistribute":false,"belongsToUsGov":false,"determinationType":"OTHER","thirdPartyContentCondition":"NOT_SET","belongsToContractor":false,"disclosedInvention":false,"submissionId":19880065955,"containsThirdPartyMaterial":false,"belongsToPublisher":false,"id":"297badb5cc2f411f97eac15cb422b862","belongsToAuthors":false},"subjectCategories":["Spacecraft Design, Testing And Performance"],"exportControl":{"isExportControl":"NO","submissionId":19880065955,"ear":"NO","id":"40162432dc984d8f90deb5f50125bed6","itar":"NO"},"distributionDate":"2019-07-12T00:00:00.0000000+00:00","title":"Design, development, and test of Shuttle/Centaur G-prime cryogenic tankage thermal protection systems","stiType":"CONFERENCE_PAPER","distribution":"PUBLIC","submittedDate":"2013-08-13T16:45:00.0000000+00:00","authorAffiliations":[{"sequence":0,"submissionId":19880065955,"meta":{"author":{"name":"Macneil, Peter N."},"organization":{"name":"General Dynamics Corp.","location":"San Diego, CA, United States"}},"id":"c44eaac29e03413c9cb03073caf5e0bc"},{"sequence":1,"submissionId":19880065955,"meta":{"author":{"name":"England, James E."},"organization":{"name":"General Dynamics Corp.","location":"Space Systems Div., San Diego, CA, United States"}},"id":"950d8aa03658416cb0b3d46fe6375ceb"},{"sequence":2,"submissionId":19880065955,"meta":{"author":{"name":"Knoll, Richard H."},"organization":{"name":"NASA Lewis Research Center","location":"Cleveland, OH, United States"}},"id":"0b2bb97bdf86452a97fe91d7b3578be6"}],"stiTypeDetails":"Conference Paper","technicalReviewType":"TECHNICAL_REVIEW_TYPE_NONE","modified":"2025-08-31T18:39:21.7150190+00:00","id":19880065955,"legacyMeta":{"__type":"LegacyMetaIndex, StrivesApi.ServiceModel","accessionNumber":"88A53182"},"created":"2013-08-13T16:45:00.0000000+00:00","center":{"code":"CDMS","name":"Legacy CDMS","id":"092d6e0881874968859b972d39a888dc"},"onlyAbstract":false,"sensitiveInformation":2,"abstract":"The thermal protection systems (TPS) for the Shuttle/Centaur were designed to provide fail-safe thermal protection during prelaunch, launch ascent, and on-orbit operations as well as during potential abort, where the Shuttle and Centaur would return to earth. The TPS selected used a helium-purged polyimide foam beneath three radiation shields for the liquid-hydrogen (LH2) tank and radiation shields only for the liquid-oxygen (LO2) tank. A double-walled vacuum bulkhead separated the two tanks. The LH2 tank had one 1.9 cm-thick layer of foam on the forward bulkhead and two layers on the larger-area sidewall. Full scale tests of the flight vehicle in a simulated Shuttle cargo bay gave total prelaunch heating rates of 29.5 and 12.9 kW for the LH2 and LO2 tanks, respectively. Calorimeter tests on a representative sample of the LH2 tank sidewall TPS indicated that the measured unit heating one would rapidly decrease from the prelaunch rate of about 300 W/sq m to a desired rate less than 4 W/sq m once on-orbit.","isLessonsLearned":false,"disseminated":"METADATA_ONLY","meetings":[{"country":"United States","submissionId":19880065955,"endDate":"1987-06-18T00:00:00.0000000+00:00","name":"Advances in cryogenic engineering.","location":"Saint Charles, IL","id":"3d0a7ea644f14a27972eb76f01a124ea","startDate":"1987-06-14T00:00:00.0000000+00:00"}],"publications":[{"submissionId":19880065955,"id":"eb6fd6634e634a7bb5f56fc2858a333e","publicationDate":"1988-01-01T00:00:00.0000000+00:00"}],"status":"CURATED","related":[],"downloads":[],"downloadsAvailable":false,"index":"submissions-2026-05-28-04-52"}