Pressurization and expulsion of a flightweight liquid hydrogen tank

  • 4.87 MB
  • 385 Downloads
  • English
by
National Aeronautics and Space Administration, National Technical Information Service, distributor , [Washington, DC], [Springfield, Va
Liquid hydr
StatementN.T. Van Dresar and R.J. Stochl.
SeriesNASA technical memorandum -- 106427.
ContributionsStochl, Robert J., United States. National Aeronautics and Space Administration.
The Physical Object
FormatMicroform
Pagination1 v.
ID Numbers
Open LibraryOL17680614M

Self-pressurization of a flightweight liquid hydrogen storage tank subjected to low heat flux (SuDoc NAS ) Unknown Binding by M. Hasan (Author)Author: M. Hasan.

Description Pressurization and expulsion of a flightweight liquid hydrogen tank PDF

pressurization experiments performed in the early ’s at NASA Lewis research center with a flightweight liquid hydrogen tank. The tank was tested at the heat fluxes, and expected in future space exploration missions.

The tank had high performance multilayer thermal insulation and a low mass-to-volume ratio. Get this from a library. Pressurization and expulsion of a flightweight liquid hydrogen tank.

[N T Van Dresar; R J Stochl; United States. National Aeronautics and Space Administration.]. Self-Pressurization of a Flightweight, Liquid Hydrogen Tank: Simulation and Comparison with Experiments Pressurization and expulsion of a flightweight liquid hydrogen tank.

VAN DRESAR and R. STOCHL; 29th Joint Propulsion Conference and Exhibit August Self-pressurization of a flightweight liquid hydrogen tank - Effectsof fill level. Experimental results are presented for pressurization and expulsion of a flightweight cu m liquid hydrogen storage tank under normal gravity conditions.

Pressurization and expulsion times were parametrically varied to study the effects of longer transfer times expected in future space flight applications.

Pressurization and expulsion of a flightweight liquid hydrogen tank. By R. Stochl and N. Vandresar. Abstract. Experimental results are presented for pressurization and expulsion of a flight-weight cu m liquid hydrogen storage tank under normal gravity conditions.

Pressurization and expulsion times are parametrically varied to study Author: R. Stochl and N. Vandresar. Self-pressurization of a flightweight liquid hydrogen tank - Effectsof fill level at low wall heat flux Pressurization and expulsion of a flightweight liquid hydrogen tank.

Self-Pressurization of a Flightweight, Liquid Hydrogen Tank: Simulation and Comparison with Experiments. Mark Stewart and. Experimental results are presented for pressurization and expulsion of a flightweight cu m liquid hydrogen storage tank under normal gravity conditions.

Pressurization and expulsion times were parametrically varied to study the effects of longer transfer times expected in future space flight : R. Stochl and N. Van Dresar.

pressurization and thermal stratification of a m3 liquid hydrogen storage tank subjected to low heat flux ( and W/m2) in normal gravity. The test tank was representative of future spacecraft tankage, having a low mass-to-volume ratio and high performance multi-layer thermal insulation.

Tests were performed at fill levels of. Thermodynamic models have been formulated to predict lower and upper bounds for the mass of pressurant gas required to pressurize a cryogenic tank and then expel liquid from the tank.

Limiting conditions are based on either thermal equilibrium or zero energy exchange between the pressurant gas and initial tank by: 3. Liquid hydrogen pressurization, venting, and resupply in low-G Pressurization and expulsion of a flightweight liquid hydrogen tank.

VAN DRESAR and R. STOCHL; 29th Joint Propulsion Conference and Exhibit August Self-pressurization of a flightweight liquid hydrogen tank - Effectsof fill level at low wall heat flux. Get this from a library. Self-pressurization of a flightweight liquid hydrogen tank: effects of fill level at low wall heat flux.

[N T Van Dresar; C S Lin; M M Hasan; United States. National Aeronautics and Space Administration.]. Main Tank Injection (MTI) Pressurization of Liquid Rocket Propellant Tanks Dale A.

Fester 54th International Astronautical Congress of the International Astronautical Federation, the International Academy of Astronautics, and the International Institute of Space Law November   Self-pressurization of a spherical liquid hydrogen storage tank in amicrogravity environment.

Pressurization and expulsion of a flightweight liquid hydrogen tank. 52nd AIAA/SAE/ASEE Joint Propulsion Conference July Self-pressurization of a flightweight liquid hydrogen tank - Effectsof fill level at low wall heat flux.

Experimental results are presented for the self pressurization and thermal stratification of a cu m liquid hydrogen storage tank subjected to low. Wang et al., focused on the LH 2 expulsion period under the open pressurization, Liu et al. focused on the fluid sloshing in the liquid oxygen (LO 2) tank under different initial liquid filling levels, Chen and Liang focused on the vaporizing rate and pressure variation in a large-sized LH 2 tank of a launch vehicle during atmospheric and self Author: Jiachao Li, Guozhu Liang, Pingping Zhu, Xi Wang.

Ramp times (times to pressurize the tank to the expulsion pressure) were parametrically varied from to mill; the range of expulsion time was from 12 to 33 rain.

Download Pressurization and expulsion of a flightweight liquid hydrogen tank PDF

Ambient temperature hydrogen gas was used as the pressurant. In order to accurately predict the whole operating process of a liquid hydrogen tank under gaseous hydrogen pressurization, a 2-D axial symmetry Volume-of-Fluid (VOF) based numerical simulation method is established. Phase change and turbulence models are included in the numerical : Jiachao Li, Guozhu Liang, Pingping Zhu, Xi Wang.

During self-pressurization, the tank's liquid fill level and the heat load from the surroundings can have significant effects on the tank's thermal stratification and pressurization rate. When controlling pressure with a mixing jet, the velocity and temperature of the jet are important design parameters affecting the thermal destratification and pressure reduction time by: Abstract.

Experimental results are reported for submerged injection pressurization and expulsion tests of a m 3 liquid hydrogen tank. The pressurant injector was positioned near the bottom of the test vessel to simulate liquid engulfment of the pressurant gas inlet; a condition that may occur in low-gravity by: 5.

A multizone model is used to predict both the self-pressurization and pressure control behavior of a ground-based experiment. The multizone model couples a finite element heat conduction model of the tank wall to the bulk conservation equations in the ullage and the by: Heat leak into the liquid nitrogen tank is controlled by the change of vacuum level and is measured by boil-off calorimetry before and after the self-pressurization process.

Boil-off calorimetry also gives information whether the experimental initial boundary condition is steady or transient by: Experience has shown that the pressure in a closed liquid-hydrogen tank may be considerably greater than the vapor pressure that corresponds to the average liquid temperature.

This increase in pressure is due to a.

Details Pressurization and expulsion of a flightweight liquid hydrogen tank PDF

surface layer of liquid hydrogen that is warmer than the bulk liquid. Previous experiments carried out at the Lewis Research Center Cited by: 5. Get this from a library. Final technical report for multi-dimensional modeling of pressurization and expulsion of multi-phase hydrogen propellant: NASA grant NAG [John I Hochstein; United States.

National Aeronautics and Space Administration.]. and Stratification of Liquid Hydrogen 1, 2 A. Schmidt, J. Purcell, W. Wilson, and R. Smith 3 (Decem ) A gallon powder-insulated Dewar has been built and appropriately instrumented to provide information concerning pressurization gas consumption, ullage pressure, liquidFile Size: 8MB.

For the helium pressurization situations, the propellant vapor effect was also ignored and a pure-helium ullage was applied. Comparing the numerical results to the experimental data suggested the CFD model had an acceptable adaptability in pressurization computation.

Compared to the pressurized discharge event, Cited by: 2. Since publication of the revised correlation, additional experimental data was obtained at the NASA Lewis Research Center for the pressurized expulsion of liquid hydrogen from spherical and nearly spherical tanks 4 " 8.

The data series and references are listed in Table 2. Data Series Reference Tank Diameter Tank Shape Pressurant Gas I VanDresar &.

Introduction. Liquid oxygen (LO 2), due to its high specific impulse when reacting with hydrogen or kerosene, has become a popular oxidizer for space the rocket launching process, LO 2 is discharged from the bottom of oxidizer tank, meanwhile high-temperature helium gas as a pressurant may be injected into the tank to hold tank pressure Cited by: Get this from a library.

Self-pressurization of a flightweight liquid hydrogen storage tank subjected to low heat flux. [M M Hasan; C S Lin; N T Van Dresar; United States.

National Aeronautics and Space Administration.]. The application of satellite technology in the Internet of Things (IOT) can just make up for the defects of the ground system for its wide coverage and. For the event of pressuring a liquid hydrogen (LH2) tank with K hydrogen gas, the same thickness foam layer produces a decrease of % in gas requirement.Experiments have been conducted to investigate the effect of fluid mixing on the depressurization of a large liquid hydrogen storage tank.

The test tank is approximately ellipsoidal, having a.A 'read' is counted each time someone views a publication summary (such as the title, abstract, and list of authors), clicks on a figure, or views or downloads the full-text.