Matthew E. Moran

Glenn Research Center, Cleveland, Ohio

Cryogenic Fluid Storage Technology Development:

Recent and Planned Efforts at NASA

NASA/TM—2009-215514

March 2009
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Matthew E. Moran

Glenn Research Center, Cleveland, Ohio

Cryogenic Fluid Storage Technology Development:

Recent and Planned Efforts at NASA

NASA/TM—2009-215514

March 2009

National Aeronautics and

Space Administration

Glenn Research Center

Cleveland, Ohio 44135

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Level of Review: This material has been technically reviewed by technical management. 

Acknowledgments

The work highlighted in this paper was performed by many dedicated people at several NASA Centers including Ames 

Research Center (ARC), Glenn Research Center (GRC), Goddard Space Flight Center (GSFC), Johnson Space Center (JSC), 

Kennedy Space Center (KSC), and Marshall Space Flight Center (MSFC). Key points of contact are listed for each of

the Cryogenic Fluid Management (CFM) storage technology areas. Matthew Moran, NASA GRC, Michael Meyer, NASA 

GRC, Stephen Tucker, NASA MSFC, Louis Salerno, NASA ARC, Kris Romig, NASA JSC, Robert Johnson, NASA KSC,

Neil T. Van Dresar, NASA GRC, Robin Flachbart, NASA MSFC, Ali Hedayat, NASA MSFC, John Jurns, NASA GRC,

Jeffrey Feller, NASA ARC, Robert Boyle, NASA GSFC, Jeffrey Moder, NASA GRC, Leon Hastings, NASA MSFC,

Steven Sutherlin, NASA MSFC, Wesley Johnson, NASA KSC, Jacob Collins, and Brian Lusby, NASA JSC.
NASA/TM—2009-215514 1

Cryogenic Fluid Storage Technology Development: 

Recent and Planned Efforts at NASA 

Matthew E. Moran 

National Aeronautics and Space Administration 

Glenn Research Center 

Cleveland, Ohio 44135 

Abstract 

Recent technology development work conducted at NASA in the area of Cryogenic Fluid 

Management (CFM) storage is highlighted, including summary results, key impacts, and ongoing efforts. 

Thermodynamic vent system (TVS) ground test results are shown for hydrogen, methane, and oxygen. 

Joule-Thomson (J-T) device tests related to clogging in hydrogen are summarized, along with the absence 

of clogging in oxygen and methane tests. Confirmation of analytical relations and bonding techniques for 

broad area cooling (BAC) concepts based on tube-to-tank tests are presented. Results of two-phase 

lumped-parameter computational fluid dynamic (CFD) models are highlighted, including validation of the 

model with hydrogen self pressurization test data. These models were used to simulate Altair 

representative methane and oxygen tanks subjected to 210 days of lunar surface storage. Engineering 

analysis tools being developed to support system level trades and vehicle propulsion system designs are 

also cited. Finally, prioritized technology development risks identified for Constellation cryogenic 

propulsion systems are presented, and future efforts to address those risks are discussed. 

Introduction 

The Cryogenic Fluid Management (CFM) Project is funded under the National Aeronautics and 

Space Administration’s (NASA) Exploration Technology Development Program (EDTP) to develop, test, 

and analyze critical cryogenic technologies needed to support lunar mission architectures. The storage 

area under CFM addresses crosscutting technologies related to tank pressure control, tank thermal control, 

insulation systems, and associated analysis and modeling tools. 

In order to insure the structural integrity of cryogenic tankage, as well as maintain propellants and/or 

other cryogenic fluids within desired temperature and pressure ranges, appropriate pressure control 

technologies must be employed. Thermodynamic vent systems (TVS) are an attractive technology for inspace pressure control since they enable tank venting in a micro-gravity environment without requiring 

propellant settling. In addition, a TVS exploits the latent and some of the sensible cooling capacity of a 

cryogen by expanding a metered portion of it through a Joule-Thomson (J-T) device rather than directly 

venting. The CFM Project has tested TVS systems in liquid hydrogen, liquid methane, and liquid oxygen 

ground tests. J-T performance tests have also been conducted with hydrogen, methane, and oxygen to 

investigate potential clogging issues. 

Broad area cooling methods use a cryocooler coupled to cooling passages that are attached to either 

the tank wall or a shield within a multilayer insulation (MLI) system. The objective of these systems is to 

intercept the environmental heat leak before it reaches the cryogen. Initial testing of the tube-to-tank 

concept has been completed and analyzed. Further testing is planned to investigate a tube-to-shield 

configuration. These active distributed cooling systems may be needed for extended lunar operations 

when passive cooling techniques are insufficient to maintain thermal control of a tank within its design 

range. 

Finally, significant effort has been directed toward improving analytical models for predicting fluid, 

thermal, and system performance for CFM systems. These modeling efforts include engineering tools 

based on empirical relations, integrated commercial analysis tools (e.g., finite element and finite 

difference codes), and computational fluid dynamic (CFD) models. The engineering models are essential 
NASA/TM—2009-215514 2

for performing system trades and early design configuration studies. Likewise, the CFD models are 

crucial for predicting fluid and thermodynamic behavior of cryogens in a variety of gravity and thermal 

environments envisioned for the lunar missions. The lack of flight data for extended in-space cryogenic 

fluid management further highlights the priority of accurate CFD models. 

Thermodynamic Vent Systems 

The primary function of a TVS is to control the thermodynamic conditions of a cryogenic propellant, 

namely the pressure and temperature. The fundamental components of the TVS tests highlighted in this 

report include 

(1) A J-T device to expand the fluid to a lower pressure and temperature (e.g., valve or other flow 

restrictor) 

(2) A heat exchanger to transfer heat from the warmer tank bulk liquid to the cooler fluid stream that 

has been expanded through the J-T device 

(3) A pump to withdraw liquid from the tank for the warm side of the heat exchanger, and optionally 

to provide inlet flow to the J-T device (J-T inlet flow can also be pressure driven) 

(4) A method of injecting the cooled bulk liquid back into the tank (e.g., spray bar or fluid jet) 

(5) A vent path for the J-T outlet 

TVS ground testing has been performed with methane and hydrogen using spray bar liquid injection. 

Recently, tests have also been completed with oxygen using both axial jet and spray ring liquid injection 

techniques. The objective of all the tests was to demonstrate the capability of a TVS to control the 

thermodynamic conditions in cryogenic propellant tanks. 

Methane Testing 

Methane TVS tests using a spray bar were performed in a 18.09 m3 tank at NASA’s Marshall Space 

Flight Center (MSFC) in November of 2006 (Refs. 1 and 2). The tank was cylindrical with 2:1 elliptical 

heads, having a diameter of 3.05 m and an overall length of 3.05 m. Boundary temperature was controlled 

to 305 K using a shroud, and testing was performed at heat leak levels of 715 and 420 W at a fill level of 

approximately 90 percent. A total of 23 TVS cycles were completed. 

Figure 1 is a schematic of a spray bar TVS with an ullage shape indicative of low gravity conditions. 

Figure 2 is a photograph of the upper portion of the test tank showing the TVS spray bar, vent line, and 

other tank internals. Figure 3 is a photograph of the test tank within the shroud prior to installation in the 

vacuum chamber. 

Several critical results were obtained with this test series, all with helium in the ullage. First, the TVS 

was able to control ullage pressure within the parameters of the test. Second, controlling TVS operation 

via ullage pressure alone resulted in a rising saturation liquid temperature. Finally, the TVS was capable 

of lowering the saturation temperature of the liquid if it was operated for longer cycle periods. All three of 

these results are evident in Figure 4. 

Hydrogen Testing 

Prior to the methane tests, hydrogen TVS tests were performed using the same test hardware in 

August through September of 2005 (Ref. 3). During this test series, a lower environmental heat leak of 

70 W was maintained. Fill levels of 90, 50, and 25 percent were tested with pure hydrogen ullage and 

mixed hydrogen-helium ullage conditions. 
NASA/TM—2009-215514 3

 
NASA/TM—2009-215514 4

Figure 5 shows data from a typical TVS cycle and illustrates the control scheme employed for this test 

series. The cycle starts with self-pressurization of the tank due to environmental heat leak. When the upper 

pressure control limit is reached, the ullage pressure is reduced by initially operating the TVS in pump-only 

mode (i.e., J-T valve is bypassed). Additional pressure reduction is then achieved by expanding through the 

J-T valve. The cycle is complete when the lower pressure control limit is reached, and the TVS is shut down. 

Figure 6 provides data on the ullage and liquid saturation pressure for the 90 percent fill level test with a 

mixed helium-hydrogen ullage. Note that the tank was initially self-pressurizing in pump-only mode until the 

tank pressure increased above 160 kPa. The TVS was able to control the ullage pressure within ±3.45 kPa. 

Figure 7 provides the ullage and liquid temperatures for the same test run. Table 1 gives a summary of all the 

hydrogen TVS tests conducted. Note the extended TVS duty cycle duration required for the mixed heliumhydrogen ullage test at 90 percent fill compared to the pure hydrogen ullage case. 
NASA/TM—2009-215514 5

TABLE 1.—HYDROGEN TEST SUMMARY (REF. 3) 

Fill level, 

percent 

Approximate mass 

GHe present, 

kg 

Number of cycles Typical pressure 

reduction cycle 

duration, 

sec 

Typical pump/ 

JT duty cycle, 

percent 

90 ----- 11 Pump only 

12 Pump only 

189 4.3 

90 0.34 18 Pump only 

31 Pump and JT 

318 10.4 

50 0.34 4 Pump only 

9 Pump and JT 

335 6.7 

50 1.95 0 Pump only 

15 Pump and JT 

512 10.6 

25 1.95 0 Pump only 

12 Pump and JT 

267 5.2 

25 3.69 0 Pump only 

12 Pump and JT 

367 6.6 
NASA/TM—2009-215514 6

Oxygen Testing 

TVS oxygen testing was recently conducted in a 1.65 m3 (58.3 ft3) tank at NASA’s Glenn Research 

Center (GRC) in October of 2008. The objective of the test series was to demonstrate a LOX TVS using 

an axial jet and spray rings at fill levels of 90 and 50 percent. The axial jet injects the cooled liquid from 

near the bottom of the tank toward the liquid-ullage interface, resulting in direct cooling and significant 

mixing of the bulk liquid when the TVS is operated. Conversely, the spray rings inject droplets into the 

ullage space in the upper portion of the tank, resulting in direct cooling of the ullage. 

An additional objective was to investigate control logic schemes that monitor both tank pressure and 

average liquid temperature. The pump-only mode used in the methane tests was not employed since this 

mode tends to increase liquid temperature in a mixed helium-oxygen ullage tank due to the heat added by 

the pump. Baseline tests were run with a pure oxygen ullage using the axial jet. These tests were followed 

by helium-oxygen ullage tests using: axial jet, combined axial jet and spray rings, and spray rings only. 

Controlling the TVS based on a combination of tank pressure and liquid temperature was explored to 

address the rising liquid temperature observed in previous methane TVS tests. It is believed that this 

rising temperature is an inherent artifact of operating the TVS over multiple cycles in a tank containing an 

noncondensable gas in the ullage. To illustrate, as the TVS operates it removes a quantity of liquid, 

thereby increasing the ullage volume. Since the mass of the noncondensable gas is constant, the increased 

ullage results in a decrease in helium partial pressure. This in turn allows the partial pressure of the vapor 

to rise, corresponding to a higher saturation temperature.1

Figure 8 shows a schematic representation of the LOX TVS and test tank (Ref. 4). Note that this is a 

functional schematic, and does not accurately represent the physical locations of the components (e.g., 

axial jet). Figure 9 is a CAD image showing the spray ring design near the top of the tank. Shown in 

Figure 10 are photographs of the TVS hardware installed in the bottom of the tank (internally and 

externally). 

 

1

Paraphrased from discussions with Neil Van Dresar. 
NASA/TM—2009-215514 7

Data reduction and interpretation are currently being performed on the LOX TVS test data, and will 

be published when completed. Operationally, the TVS was able to maintain the tank thermodynamic 

conditions (pressure or temperature) within the prescribed automated control band with all of the liquid 

injection configurations tested. This was demonstrated for both a pure oxygen and mixed helium-oxygen 

ullage. 

Joule-Thomson Device Performance 

A key component of any TVS is the J-T device used to expand the fluid to provide cooling. Previous 

tests conducted with multiorifice J-T devices in liquid hydrogen have indicated the possibility of clogging 

under some operating conditions (Ref. 5). It has been postulated that the clogging may be due to the 

presence of neon impurities in the liquid hydrogen that solidify on the cold surfaces of a J-T device during 

operation due to the expansion process. Neon impurities as low as parts per billion (ppb) are believed to 

be sufficient to cause the clogging. 

Figure 11 shows a liquid hydrogen J-T test with a 0.254 mm orifice where the flowrate decreases 

from 37 slpm to nearly zero over an operating time of 20 min (Ref. 6). The clogging has been observed to 

occur at liquid hydrogen temperatures between 22 and 26 K (37 to 44 °R), with no clogging below or 

above this range (Ref. 5). 
NASA/TM—2009-215514 8

Testing was started in October of 2008 at NASA’s Glenn Research Center to investigate a variety of 

clogging mitigation strategies for hydrogen such as (Ref. 7) 

(1) Stopping flow, and observing if the device unclogs spontaneously over time 

(2) Varying the duty cycle of flow through the device 

(3) Using a heater to unclog the device 

(4) Switching flow between parallel devices 

(5) Running parallel devices simultaneously 

(6) Mechanical unclogging techniques (e.g., varying needle valve travel) 

No clogging has been observed in testing to date with liquid methane or liquid oxygen2

 (Refs. 6 and 

7). Additional testing with methane is planned at higher pressures (i.e., up to 1720 kPa or 250 psia) to 

insure no clogging occurs under those conditions as well. Table 2 summarizes all the J-T clogging tests 

completed to date (Ref. 7). 

TABLE 2.—J-T CLOGGING TESTS SUMMARY (REF. 7) 

Fluid Temperature 

range, 

°R 

Pressure range, 

psia 

Test result Test location 

LCH4 181 to 203 20 to 22 No clogging GRC CCL-7 

LOX 168 to 209 20 to 121 No clogging GRC SMiRF 

LH2 32 to 47 52 to 60 Clogging GRC CCL-4 

LH2 39 to 46 29 to 33 Clogging GRC CCL-7 

Active Distributed Cooling 

A “tube-to-tank” test series was conducted at NASA’s Ames Research Center (ARC) in January of 

2008 to validate analytical models that have been formulated for distributed cooling concept designs and 

trade studies (e.g., broad area cooling) (Refs. 8 to 10). Additionally, the test addressed the thermal and 

mechanical feasibility of bonding a distributed cooling line to a structure (e.g., a tank wall) that is subject 

to large temperature variations. 

 

2

Liquid oxygen J-T clogging tests were performed at the NASA GRC SMiRF test facility in August, 2007. 
NASA/TM—2009-215514 9

Figure 12 illustrates the test article which was comprised of: a 42 long by 19.75 wide by 6.6 mm thick 

aluminum plate, a 2.6 mm i.d. tube with 0.7 mm wall thickness, heater wire attached with varnish, inlet 

and outlet heat exchangers consisting of stacked copper screens, and low temperature epoxy bonding the 

tube to the plate. A Gifford-McMahon cryocooler provided the cooling for the helium stream. 

Figure 13 provides the transient temperature profile at various points throughout the test article for 

one of the tests (Ref. 8). At 23.6 hr, a differential temperature of roughly 200 K exists from the cryocooler 

cold head to the tube outlet heat exchanger. Less than 6 hr later, the test article temperatures have cooled 

down to within a few degrees of each other. 

Figure 14 shows the thermal resistance between the plate and the helium gas stream (multiplied by 

the tube effective length) as a function of Reynolds number. The experimentally measured resistance 

shows good agreement with the calculated resistance for finite tube length. Note that the bond resistance 

is an order of magnitude smaller than the overall resistance, confirming the bonding technique’s 

feasibility from a thermal performance standpoint. The thermal resistance for an infinite length tube is 

also plotted. 

Figure 15 plots the derived test article heat transfer effectiveness ratio (η) as a function of flow rate 

(Ref. 8). Again, good agreement between the measured and calculated values is evident. Since the test 

article used a short tube length, Figure 15 also shows a calculated heat transfer effectiveness ratio 

trendline for a long tube, as would be typical of a distributed cooling application. 

The key result of the test series was confirmation of the overall approach and assumptions of the 

analytical models for laminar flow conditions. In addition, determination of the thermal resistance 

between the plate and gas stream, and the heat transfer effectiveness, provides confidence in the tube-totank broad area cooling concept. 

Tube-to-shield testing is planned next to address the concept of cooling one layer (i.e., shield) of 

multilayer insulation (MLI). Selection of a layer of MLI to actively cool could make use of the first stage of 

a two stage cryocooler to intercept environmental heat leak at a higher temperature than at the tank wall. 
NASA/TM—2009-215514 10

 
NASA/TM—2009-215514 11

Analytical Modeling 

The objectives of the Cryogenic Fluid Management analytical modeling efforts in the storage area are 

split into two categories based on the intended application 

(1) Develop CFD models capable of simulating the thermodynamic and fluid dynamic behavior of 

cryogenic tankage with high fidelity, particularly for on-orbit and lunar environments where no long 

duration data is available. 

(2) Develop engineering system analysis tools for engineering trades, system performance 

simulation, and design predictions. 

CFD Modeling 

A key issue for developing any analytical modeling capability is the need to validate the model with 

flight and/or test data. NASA’s Glenn Research Center conducted liquid hydrogen self-pressurization 

tests in a 4.955 cm3

 liquid hydrogen flightweight tank under normal gravity conditions in the 1990s 

(Refs. 11 to 13). This experimental data was used to validate a two-phase lumped-vapor CFD model 

(Ref. 14). 

Figure 16 provides CFD model results for self pressurization of the hydrogen tank at various elapsed 

times. Temperature isocountours are shown on the left side of the line of symmetry in the liquid, with 

stream function isocontours on the right side. These plots illustrate the thermal stratification that occurs in 

a quiescent tank, along with the natural convection flows that are induced, in a normal gravity 

environment. 
NASA/TM—2009-215514 12

Figure 17 provides comparisons of the CFD model results to the experimental data. In general, the 

model showed good agreement with the test data. The divergence of the results for the higher fill levels is 

presumed to be due to nonuniform heat flux conditions for the test configuration (Ref. 14). 

With some validation of the modeling approach completed, a two-phase lumped-vapor CFD model 

was developed to account for noncondensable gas (e.g., helium) in the ullage. This modeling approach 

was applied to a representative Altair ascent stage composed of liquid oxygen and liquid methane 

propellants, and subjected to a lunar surface thermal environment simulating a 210 day storage period 

(Ref. 15). 

Figure 18 shows the CFD model results of the temperature and flow fields for the liquid methane tank 

after two days simulated duration on the lunar surface. The reduced gravity at the lunar surface is 

sufficient to produce thermal stratification and natural convection flows; in this case 98.22 to 98.52 K, 

and 1.13 mm/s maximum velocity, after two days. 

Once a stationary state was achieved within the liquid phase of the model, a reduced multizone model 

(ullage, liquid, and interface zones) was used to extrapolate the solution for extended periods. Figure 19 

shows the methane tank pressure and temperature response over a simulated 210 day lunar surface storage 

period. Initial tank pressures at launch of 100 and 200 psia are plotted separately. Results for the oxygen 

tank are similarly presented in Reference 15. 
NASA/TM—2009-215514 13

This CFD modeling approach provides a valuable tool for simulating detailed thermodynamic 

response of cryogenic tanks on the lunar surface. Ongoing work is addressing other relevant environments 

and operational conditions to expand the CFD modeling capability for cryogenic tanks. 

Engineering System Analysis 

In addition to CFD models, system level analytical tools are needed for engineering trades and system 

design support. There are numerous existing cryogenic system analytical tools of varying complexity, 

approach, assumptions, and documentation. The verification and validation of these tools also ranges 

widely. An effort has been undertaken to standardize a portfolio of these analytical tools and make them 

available as a library of FORTRAN algorithms that can be incorporated into a variety of custom models 

(e.g., finite difference commercial codes, spreadsheet system models and macros, etc.). 

The building blocks of this portfolio of cryogenic system tools includes previously developed legacy 

codes for passive and active storage calculations (Refs. 16 to 18). In general, these codes employ first 

principle derivations, engineering correlations, and empirically based relations to predict a range of 

parameters relevant to cryogenic systems. 

Figure 20 shows an example plot from the Passive Cryogenic Storage Analyzer (PCSA) code that 

provides mass trade study results for a tank wrapped with variable density MLI as a function of the 

number of layers (Ref. 16). As MLI layers are added, the boiloff mass is reduced due to lower 
NASA/TM—2009-215514 14

environmental heat leak. Likewise, the tank mass is reduced since less tank volume is required to provide 

the same amount of propellant due to lower boiloff losses. However, the tradeoff occurs due to the 

increasing MLI mass as more layers are added. It can be seen that the total tankage system weight 

(denoted as “Ins+Boiloff+Tank ∆m” in Figure 20 with the triangle plot symbols) reaches a minimum at 

approximately 40 to 50 layers of MLI. 

Figure 21 summarizes the basic strategy being implemented (Ref. 19). Initially, integration of these 

analytical tools into vehicle-level SINDA3

 thermal models has been undertaken to support Constellation 

 

3

Systems Improved Numerical Differencing Analyzer 
NASA/TM—2009-215514 15

Program needs. Expanded capabilities are planned to address launch hold and ascent heating, TVS 

performance, multilayer insulation optimization, passive vapor cooling, and other key cryogenic system 

parameters. 

Summary and Conclusions 

The CFM project has completed several key technology development milestones in the storage area. 

1. TVS have been demonstrated in ground tests for hydrogen, methane, and oxygen. In all tests, the total 

tank pressure was controlled by the TVS for ullages containing both pure vapor, and a mixture of 

vapor and noncondensable gas. From a control standpoint, the liquid temperatures were found to be a 

key parameter to monitor in addition to the tank pressure. Automated TVS control by monitoring both 

tank pressure and liquid temperature was recently demonstrated during the liquid oxygen TVS 

testing. 

2. The Joule-Thomson device clogging observed under some conditions with hydrogen is being 

addressed in current testing. These tests will indicate which techniques, or set of techniques, are most 

likely to address the clogging issue in hydrogen. Regarding other cryogenic propellants, testing has 

ruled out clogging as an issue for oxygen and methane at low pressures. Testing of methane at high 

pressures is planned to insure no issue exists under these conditions as well. 

3. The analytical models formulated for active distributed cooling concepts have been confirmed with 

the completion of a tube-to-tank test series. The thermal and mechanical feasibility of bonding a 

cooling tube to an aluminum plate subjected to cryogenic cooldown was also demonstrated. Thermal 

resistance between the cooling gas stream and aluminum plate were determined, along with the heat 

transfer effectiveness ratio. The test results showed good overall agreement with analytically 

calculated values. Testing of a tube-to-shield concept is planned next. 

4. Advances have been made in the development of CFD and system analytical modeling tools for 

cryogenic storage systems. A two-phase lumped-parameter CFD modeling method has been validated 

against liquid hydrogen self pressurization data taken in ground tests with a flightweight tank. This 

same modeling approach has been applied to Altair representative methane and oxygen tanks to 

predict thermodynamic and fluid dynamic behavior during a 210 day lunar surface storage scenario. 

Likewise, a suite of cryogenic system analytical tools are being developed in the form of a 

FORTRAN library of algorithms, that have already been implemented in vehicle SINDA analysis 

models. An expanded set of algorithms is planned to address key cryogenic parameters relevant to the 

Constellation Program. 

NASA/TM—2009-215514 17

Appendix—Future Work 

In the Fall of 2007, a CFM Propulsion Workshop was held to identify cryogenic system technology 

risks associated with the Altair Lunar Lander and the Ares V Earth Departure Stage. Following the 

identification of these risks, mitigation strategies were developed, and prioritized ranking of the risks was 

made. Current CFM Storage tasks are addressing many of these risks, and future work is planned to 

address the remaining risks either directly or in coordination with other efforts. The top eight risk areas 

identified in the CFM Storage area were 

(1) Cryogenic subcooling of propellants (loading and maintenance) 

(2) Cryogenic system engineering modeling (appropriate analytical tools) 

(3) Heat leak uncertainty (performance prediction and installation of insulation systems) 

(4) Cryogenic system advanced materials and structures (COPV, MMOD, etc.) 

(5) Uncertainty in initial conditions for analytical model validation 

(6) Thermodynamic vent systems 

(7) Degraded insulation performance during ground hold and ascent 

(8) Large scale insulation systems 

In the next year, CFM Storage testing will be focused on a methane lunar storage demonstration to 

support the Altair decision gate for selecting hypergolics or cryogenic propellants for the Ascent Stage. 

These tests will demonstrate operation of a TVS in a multilayer insulated tank designed to simulate the 

thermal and geometric parameters of the flight tanks. A new methane conditioning system will have the 

capability to supply thermodynamic propellant conditions consistent with any statepoint anticipated 

throughout a 210 day lunar surface storage duration. A cryoshroud will provide the appropriate thermal 

boundary to simulate lunar surface conditions. 

Figure 22 shows the external and internal features of the methane tank preliminary design (Ref. 20). 

External protuberances have been minimized to facilitate installation of the multilayer insulation. The top 

and bottom access hatches are designed to be interchangeable to provide assembly flexibility. 
NASA/TM—2009-215514 18

Analytical modeling work will continue to expand the capabilities to support key spacecraft cryogenic 

system designs and simulate mission operational concepts. Emphasis will remain on verification and 

validation of the tools against test data. Testing efforts beyond next year will begin to address ascent 

heating and venting as well as insulation systems (including integrated MMOD shielding) for large tanks. 

References 

1. Flachbart, R.H., Hastings, L.J., Hedayat, A., Nelson, S.L., and Tucker, S.P., “Thermodynamic Vent 

System Performance Testing With Subcooled Liquid Methane and Gaseous Helium Pressurant,” 

Cryogenics, 2008. 

2. “Liquid Methane Thermodynamic Vent System Testing With Gaseous Helium Pressurant,” CFM 

Project Report, Dec. 21, 2007. 

3. Flachbart, R.H., Hastings, L.J., Hedayat, A., Nelson, S.L., and Tucker, S.P., “Testing the Effects of 

Helium Pressurant on Thermodynamic Vent System Performance With Liquid Hydrogen,” Cryogenic 

Engineering Conference, July 16–20, 2007. 

4. Van Dresar, Robinson, Bamberger, Czaruk, “Thermodynamic Vent System (TVS) Test Readiness 

Review,” CFM internal presentation, August 28, 2008. 

5. Jurns, J.M., and Lekki, J.D., “Clogging of Joule-Thomson Devices in Liquid Hydrogen Handling,” 

AIAA Joint Propulsion Conference, July 9–12, 2006. 

6. Jurns, J.M., “Visco Jet Joule-Thomson Device Characterization Tests in Liquid Methane,” NASA 

TM-TBD, 2008. 

7. Jurns, J.M., “Clogging of Joule-Thomson Devices in Liquid Hydrogen—Experiment Requirements 

Document,” CFM project document, May, 2008. 

8. Feller, J.R., Salerno, L.J., Kashani, A., and Helvensteijn, B.P.M., “Summary of the Tube-to-Plate 

Distributed Cooling Test,” CFM Project Report, March 14, 2008. 

9. Feller, J.R., Kashani, A., Helvensteijn, B.P.M., and Salerno, L.J., “Summary of Distributed Cooling 

and Advanced Regenerator Test Fixture Development,” end-of-year progress report to the NASA 

PCAD Project, 2006. 

10. Feller, J.R., Kashani, A., Helvensteijn, B.P.M., Salerno, L.J., Kittel, P., Plachta, D., Christie, R., and 

Carlberg, E., “Analysis of Continuous Heat Exchangers for Cryogenic Boil-Off Reduction,” in 

Advances in Cryogenic Engineering: Transactions of the 2007 Cryogenic Engineering Conference—

CEC, vol. 52, 2007. 

11. Stochl R., Knoll R., “Thermal Performance of a Liquid Hydrogen Tank Multilayer Insulation System 

at Warm Boundary Temperatures of 630, 530, and 152 R,” NASA TM-104476, 1991. 

12. Van Dresar, N., Lin C., Hasan M., “Self-Pressurization of a Flightweight Liquid Hydrogen Tank: 

Effects of Fill Level at Low Wall Heat Flux,” NASA TM-105411, 1992. 

13. Hasan M., Lin C., Van Dresar N., “Self-Pressurization of a Flightweight Liquid Hydrogen Storage 

Tank Subjected to Low Heat Flux,” NASA TM-103804, 1991. 

14. Barsi, S., and Kassemi, V., “Numerical and Experimental Comparisons of The Self Pressurization 

Behavior of an LH2 Tank in Normal Gravity,” Cryogenics, 48(3/4), pp. 122–129, 2008. 

15. Barsi, S., Moder, J., and Kassemi, M., “Numerical Investigation of LO2 and LCH4 Storage Tanks on 

the Lunar Surface,” AIAA–2008–4749, Joint Propulsion Conference, 2008. 

16. Johnson, W.L., Sutherlin, S.G., Tucker, S.P, “Cryogenic Propellant Insulation System Design Tools 

for Mass Optimization of Space Vehicles,” SPACE 2008, AIAA–2008–7765, September 9–11, 2008. 

17. Plachta, D.W., Christie, R.J., Jurns, J.M., and Kittel, P., “Passive ZBO Storage of Liquid Hydrogen 

and Liquid Oxygen Applied to Space Science Mission Concepts,” Cryogenics, 46, pp. 89–97, 2006. 

18. Carlberg, E.R., “Envision Cryogenic Analysis Tool (CAT) and Broad Area Cooling (BAC): 

Engineering Theory & Descriptive Discussion,” NASA GRC draft internal report, November, 2006. 

19. Moran, M., Sutherlin, S., Johnson, W., Plachta, D., “Integrated Cryogenic Modeling: Creating a 

Standard Toolset,” CFM internal presentation, May 21, 2008. 

20. Griffiths, C., “Preliminary Methane Tank Design,” CFM internal presentation, September 25, 2008. 
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1. REPORT DATE (DD-MM-YYYY)

01-03-2009 

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Technical Memorandum 

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4. TITLE AND SUBTITLE

Cryogenic Fluid Storage Technology Devleopment: Recent and Planned Efforts at NASA 

5a. CONTRACT NUMBER

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6. AUTHOR(S)

Moran, Matthew, E. 

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WBS 095240.04.03.01.03.03 

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National Aeronautics and Space Administration 

John H. Glenn Research Center at Lewis Field 

Cleveland, Ohio 44135-3191 

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E-16816 

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Available electronically at http://gltrs.grc.nasa.gov 

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14. ABSTRACT

Recent technology development work conducted at NASA in the area of Cryogenic Fluid Management (CFM) storage is highlighted, 

including summary results, key impacts, and ongoing efforts. Thermodynamic vent system (TVS) ground test results are shown for 

hydrogen, methane, and oxygen. Joule-Thomson (J-T) device tests related to clogging in hydrogen are summarized, along with the absence 

of clogging in oxygen and methane tests. Confirmation of analytical relations and bonding techniques for broad area cooling (BAC) 

concepts based on tube-to-tank tests are presented. Results of two-phase lumped-parameter computational fluid dynamic (CFD) models are 

highlighted, including validation of the model with hydrogen self pressurization test data. These models were used to simulate Altair 

representative methane and oxygen tanks subjected to 210 days of lunar surface storage. Engineering analysis tools being developed to 

support system level trades and vehicle propulsion system designs are also cited. Finally, prioritized technology development risks identified 

for Constellation cryogenic propulsion systems are presented, and future efforts to address those risks are discussed. 

15. SUBJECT TERMS

Cryogenics; Propulsion; Oxygen; Methane; Hydrogen; Joule-Thomson effect; Propellant storage; Cryogenic cooling; 

Thermodynamics; Computational fluid dynamics; System analysis 

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