NASA LogoNTRSNTRS - NASA Technical Reports ServerSearchmore_vertCollectionsAboutNewsHelpLogin Back to ResultsSolar Thermal Upper Stage Liquid Hydrogen Pressure Control TestingHigh-energy cryogenic propellant is an essential element in future space exploration programs. Therefore, NASA and its industrial partners are committed to an advanced development/technology program that will broaden the experience base for the entire cryogenic fluid management community. Furthermore, the high cost of microgravity experiments has motivated NASA to establish government/aerospace industry teams to aggressively explore combinations of ground testing and analytical modeling to the greatest extent possible, thereby benefitting both industry and government entities. One such team consisting of ManTech SRS, Inc., Edwards Air Force Base, and Marshall Space Flight Center (MSFC) was formed to pursue a technology project designed to demonstrate technology readiness for an SRS liquid hydrogen (LH2) in-space propellant management concept. The subject testing was cooperatively performed June 21-30, 2000, through a partially reimbursable Space Act Agreement between SRS, MSFC, and the Air Force Research Laboratory. The joint statement of work used to guide the technical activity is presented in appendix A. The key elements of the SRS concept consisted of an LH2 storage and supply system that used all of the vented H2 for solar engine thrusting, accommodated pressure control without a thermodynamic vent system (TVS), and minimized or eliminated the need for a capillary liquid acquisition device (LAD). The strategy was to balance the LH2 storage tank pressure control requirements with the engine thrusting requirements to selectively provide either liquid or vapor H2 at a controlled rate to a solar thermal engine in the low-gravity environment of space operations. The overall test objective was to verify that the proposed concept could enable simultaneous control of LH2 tank pressure and feed system flow to the thruster without necessitating a TVS and a capillary LAD. The primary program objectives were designed to demonstrate technology readiness of the SRS concept at a system level as a first step toward actual flight vehicle demonstrations. More specific objectives included testing the pressure and feed control system concept hardware for functionality, operability, and performance. Valuable LH2 thermodynamic and fluid dynamics data were obtained for application to both the SRS concept and to future missions requiring space-based cryogen propellant management.Document ID20160005437Acquisition SourceMarshall Space Flight CenterDocument TypeTechnical Publication (TP)AuthorsMoore, J. D.*(ManTech SRS Technologies Huntsville, AL, United States)*Otto, J. M.*(ManTech SRS Technologies Huntsville, AL, United States)*Cody, J. C.*(ManTech SRS Technologies Huntsville, AL, United States)*Hastings, L. J.*(Alpha Technology Huntsville, AL, United States)*Bryant, C. B.*(NASA Marshall Space Flight Center Huntsville, AL, United States)*Gautney, T. T.*(NASA Marshall Space Flight Center Huntsville, AL, United States)*Date AcquiredApril 27, 2016Publication DateAugust 1, 2015Subject CategorySpacecraft Propulsion And PowerFluid Mechanics And ThermodynamicsReport/Patent NumberM-1400NASA/TP-2015-218211Funding Number(s)CONTRACT_GRANT: NNM09AA18CDistribution LimitsPublicCopyrightPublic Use Permitted.Available DownloadsNameType20160005437.pdfSTIcloud_downloadcontent_copyvisibilityRelated RecordsThere are no records associated with this record.visibility_offNo Preview Available
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