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  • 1
    Publication Date: 2019-07-13
    Description: The paper presents the development background and the present status of the Atmospheric Cloud Physics Laboratory (ACPL) thermal control capability. The ACPL, a Spacelab payload, is currently in the initial flight hardware development phase for a first flight scheduled in June 1981. The ACPL is intended as a facility for conducting a wide variety of cloud microphysics experimentation under zero gravity conditions. The cloud chambers, which are key elements of the ACPL, have stringent thermal requirements. Thus the expansion chamber inner walls must be uniform to within + or - 0.1 C during both steady-state and transient operation over a temperature range of +30 to -25 C. Design progression of the expansion chamber, from early in-house NASA-MSFC concepts (including test results of a prototype chamber) to a thermal control concept currently under development, is discussed.
    Keywords: GROUND SUPPORT SYSTEMS AND FACILITIES (SPACE)
    Type: ASME PAPER 78-ENAS-9 , American Society of Mechanical Engineers, Intersociety Conference on Environmental Systems; Jul 10, 1978 - Jul 13, 1978; San Diego, CA
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  • 2
    Publication Date: 2019-08-14
    Description: Earth-to-Orbit Propulsion Technology program is considered. The program's three major technical areas include combustion devices, turbomachinery, and controls and monitoring. Directed toward reducing acquisition and operations risk and cost the ETO program is conducted in two serially-performed categories: technology acquisition and technology validation. The former is constituted of studies, tool building, and bench-scale experimentation. The latter involves next-step verification of the acquisition results and findings, usually leading to a test-bed validated technology 'product'.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: IAF PAPER 91-258
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  • 3
    Publication Date: 2019-08-28
    Description: The paper discusses the primary objective of the NASA-OAST earth-to-orbit (ETO) propulsion technology program, namely, to completely overhaul the nation's liquid rocket design and analysis capabilities which were found to be severely limited when used for the design and development of the Space Shuttle Main Engine (SSME). Meeting this objective is to provide a much sounder, very comprehensive technology base that will enable the cost-effective low-risk development, acquisition, and operation of high-performance, expendable, or reusable ETO propulsion systems. This in turn will enable the future development of space transportation system launch vehicles with greatly reduced life-cycle costs. Work is carried out in three major areas: combustion devices, turbomachinery, and controls and health management.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 92-1478
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