A vented high-voltage system for satellite applications
Vented high-voltage system for power supply of photomultiplier tube in OAO
Laffert, D.↗
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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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Venting vapor apparatus Patent
Fuel tank pressure-relief device for venting cryogenic liquid vapors through tubes with porous plug
Weber, R. J.↗
Characteristics of Fluid Vented into a Vacuum Annual Report
Characteristics of fluid vented into vacuum
Maples, D.↗
Liquid storage tank venting device for zero gravity environment Patent
Venting device for liquid propellant storage tank using magnetic field to separate liquid and gaseous phases
Graham, R. W.↗
Analysis of two-phase impingement from a cryogen vented in orbit
Impingement pressure analysis associated with two phase cryogenic propellant venting to space environment
Evans, E. A.↗
Pressure sensing control development for pressurization and venting systems Final report, 2 Jul. 1969 - 2 Aug. 1970
Hybird electronic controller developed for pressurization and venting systems of space propulsion system
Tobloski, J.↗
Venting device for pressurized space suit helmet Patent
Venting device for pressurized space suit helmet to eliminate vomit expelled by crewmen
Gran, A. A.↗
Space shuttle compartment venting Final report
In-flight venting of space shuttle vehicles investigated using delta wing booster and high crossrange orbiter vehicles as configurations
Haukohl, J.↗
Compartment venting - Space vehicle design criteria
Analysis of internal and external gas venting system of spacecraft
Source record↗
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.↗
UO2 venting and redistribution
Out-of-pile experiment for measuring uranium dioxide fuel redistribution rates, determining vent hole plugging time and thermal cycling
Phillips, W. M.↗
Design curve for liquid helium cryostats with vapor-cooled vent tubes
Design curve for estimating conduction heat transfer liquid He cryostats with vapor-cooled vent tubes
Dicarlo, J. A.↗
Saturn S-IVB continuous vent system for propellant control during parking orbit
Saturn S-4B continuous vent system for propellant tanks during parking orbit to prevent excessive pressure, requiring liquid settling with auxiliary ullaging rockets
Neher, R. T.↗
Design considerations for an orbital nonpropulsive vent system
Orbital nonpropulsive vent system to remove excess or residual propellant vapors and waste gases with minimum impulse imbalances imparted to vehicle
Buchmann, H. F.↗
Fill and vent quick disconnect
Hydraulic disconnect coupling on ground serving half of spacecraft refrigeration cooling system employs movable center stem for venting and closing nipple poppet. Self sealing poppet quickly connects cooling system to spacecraft without manual work. Recessed sealing surface insures open poppet when stem retracts.
Boerner, R. Y.↗
Study of Thermodynamic Vent and Screen Baffle Integration for Orbital Storage and Transfer of Liquid Hydrogen
A comprehensive analytical and experimental program was performed to determine the feasibility of integrating an internal thermodynamic vent system and a full wall-screen liner for the orbital storage and transfer of liquid hydrogen (LH2). Ten screens were selected from a comprehensive screen survey. The experimental study determined the screen bubble point, flow-through pressure loss, and pressure loss along rectangular channels lined with screen on one side, for the 10 screens using LH2 saturated at 34.5 N/cm2 (50 psia). The correlated experimental data were used in an analysis to determine the optimum system characteristics in terms of minimum weight for 6 tanks ranging from 141.6 m3 (5,000 ft3) to 1.416 m3 (50 ft3) for orbital storage times of 30 and 300 days.
Cady, E. C.↗
Vented vectoring-nozzle for STOL and V/STOL aircraft
Vented vectoring-nozzle has superior thrust coefficient and is lighter in weight because it does not require completely enclosed elbow duct ordinarily used to deflect nozzle flow. Improved nozzle has primary nozzle and three-sided elbow deflector.
Esker, D. W.↗
Results of tests OA26 and IA16 in the NASA/ARC 3.5-foot hypersonic wind tunnel on an 0.015-scale model (36-OTS) of the space shuttle configuration 140A/B to obtain pressures for venting analysis
Tests were conducted, from November 15 to December 4, 1973, to obtain surface pressure data on an 0.015-scale replica of the Space Shuttle Vehicle 4. Data were obtained at Mach numbers of 5.3, 7.4, and 10.3, to support the venting analysis for both launch and entry conditions. These tests were the final tests in a series covering a Mach number range from 0.6 to 10.3. The model was instrumented with pressure orifices in the vicinity of the cargo bay door hinge and parting lines, and on the side of the fuselage at the crew compartment, and below the orbital maneuvering system pods at the aft compartment. The model was tested at angles of attack and sideslip consistent with expected divergencies from the nominal trajectory.
Spangler, R. H.↗