Computer program for thermal analysis of tank mounted multilayer insulation
Space-hold thermal analysis of oblate spheroid tank mounted multilayer insulation configurations by computer including programs
Cowgill, G. R.↗
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Results for “TANKS”
Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Hypervelocity impact tests on a proposed lunar tug fuel tank configuration
Hypervelocity impact tests to predict meteoritic damage on proposed lunar tug fuel tank configuration
Jex, D. W.↗
Propellant tank pressurization system Patent
Method and apparatus for pressurizing propellant tanks used in propulsion motor feed system
Appel, M. A.↗
Study of thermal conductivity requirements. Volume 3: Analytical and experimental heat transfer study of a venting cryogen tank
Analysis of heat transfer characteristics of venting cryogen tank - Vol. 3
O'Neill, M. J.↗
Zero-g radio frequency gaging system for space shuttle propellant tanks
Radio frequency measuring system for space shuttle propellant tanks under conditions of weightlessness
Thompson, H. E.↗
Development of a bladderless tank for space shuttle
Development of bellows-type tanks for long term storage of potable water for space shuttle
Feindler, C.↗
Zero gravity liquid-vapor interface configurations in conical tanks
Analysis of liquid-vapor interface conditions in conical tanks in weightless environment
Spuckler, C. M.↗
Thermally resistant polymers for fuel tank sealants
Thermally resistant polymers for fuel tank sealants of advanced high speed aircraft
Webster, J. A.↗
Low-frequency vibration qualification testing for Mariner Mars 1971 propellant tanks
LF vibration qualification tests for Mariner Mars 1971 propellant tanks
Epstein, S. J.↗
Vehicle-scale investigation of a fluorine- hydrogen main tank injection pressurization system
Liquid hydrogen fueled space vehicle fluorine- hydrogen main tank injection pressurization system performance prediction by computerized analysis
Cady, E. C.↗
Thermal control for storage of cryogenic propellants in a common-bulkhead tank: A concept
Simple, reliable ground-hold refrigeration system for common-bulkhead tank meets design criteria and objectives for ground-hold of oxygen difluoride and diborane. System is failsafe and malfunctions can be rectified without interruption of basic system functions.
Stone, G. R.↗
Thermal control for storage of cryogenic propellants in a multiple-tank system: A concept
Development of system for storing cryogenic propellants in multiple tank configuration is discussed. System uses single loop and closed loop features. Liquid nitrogen and Freon-14 are used as refrigerants. Diagram of equipment to show components and operation is provided.
Stone, G. R.↗
Thermally resistant polymers for fuel tank sealants
Conversion of fluorocarbon dicarboxylic acid to intermediates whose terminal functional groups permit polymerization is discussed. Resulting polymers are used as fuel tank sealers for jet fuels at elevated temperatures. Stability and fuel resistance of the prototype polymers is explained.
Webster, J. A.↗
An experimental study of axisymmetric modes in various propellant tanks containing liquid
An experimental study of several models used to analyze the longitudinal dynamics of oscillations in launch vehicle propellant tanks, is presented. Several vehicle structural configurations are considered: hemispherical and spherical, cylindrical and spherical, and semiellipsoidal and ellipsoidal. Various bulkheads and flanges are used with each configuration. The results are given in graphs.
Kana, D. D.↗
Aerodynamic characteristics of the North American Rockwell space shuttle delta-wing orbiter (110C) alone and with belly-mounted external oxygen/hydrogen tanks (M equals 0.6 to 5.0)
Experimental aerodynamic investigations were conducted at the MSFC 14 x 14 inch trisonic wind tunnel on a .0044 scale model of the space shuttle orbiter, 110C. The test configurations included the orbiter alone and with external oxygen/hydrogen belly tanks. The six component aerodynamic force and moment data obtained cover a Mach number range from 0.6 to 4.96 at angles of attack from 10 to 60 deg at 0 deg sideslip angle and -10 to 10 deg at -6 deg sideslip angle. Reynolds number per unit length varied somewhat with Mach number but was a nominal 6.8 million per foot.
Allen, E. C.↗
A computer program for the calculation of thermal stratification and self-pressurization in a liquid hydrogen tank
An analysis and computer program are described for calculating the thermal stratification and the associated self-pressurization of a closed liquid hydrogen tank. FORTRAN-IV language is used and runs were made on IBM 360/65 and CDC 3600 computers. Comparisons are made between the program calculations and test results from both ground and orbital coast tests of a Centaur space vehicle.
Arnett, R. W.↗
Development of Lightweight Material Composites to Insulate Cryogenic Tanks for 30-Day Storage in Outer Space
A conceptual design was developed for an MLI system which will meet the design constraints of an ILRV used for 7- to 30-day missions. The ten tasks are briefly described: (1) material survey and procurement, material property tests, and selection of composites to be considered; (2) definition of environmental parameters and tooling requirements, and thermal and structural design verification test definition; (3) definition of tanks and associated hardware to be used, and definition of MLI concepts to be considered; (4) thermal analyses, including purge, evacuation, and reentry repressurization analyses; (5) structural analyses (6) thermal degradation tests of composite and structural tests of fastener; (7) selection of MLI materials and system; (8) definition of a conceptual MLI system design; (9) evaluation of nondestructive inspection techniques and definition of procedures for repair of damaged areas; and (10) preparation of preliminary specifications.
Krause, D. R.↗