Significant elements in detail tank design are wall and end structures, weld joints at bulkhead and attachment junctures, and ports and access openings. Additional design considerations are influence and effect of fabrication processes on tank component design, and finally, testing and inspection that are required to establish confidence in tank design.
Topics: NASA Technical Reports Server (NTRS), FRACTURE MECHANICS, FUEL SYSTEMS, FUEL TANK PRESSURIZATION
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306
Jun 19, 2010
06/10
by
Arnett, R. W.; Millhiser, D. R
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No Abstract Available
Topics: CONFERENCES, CONTAINERS, FUEL TANK PRESSURIZATION, MATHEMATICAL MODELS, PROPELLANT TANKS,...
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410
Jun 21, 2010
06/10
by
NON
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Design, development, and testing of device for measuring spatial orientation between separating S-2 and S-4B stages of Saturn 5
Topics: LIQUEFIED GASES, LIQUID-GAS MIXTURES, METHANE, SOLUBILITY, AIRCRAFT FUEL SYSTEMS, FUEL TANK...
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525
Jun 21, 2010
06/10
by
NON
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Conference proceedings on respiratory physiology in aerospace environment
Topics: GAS ANALYSIS, GAS PRESSURE, LIQUID OXIDIZERS, LIQUID ROCKET PROPELLANTS, DISSOLVING, FUEL TANK...
The following topics are briefly addressed in this one page document: (1) potential instrumentation difficulties; (2) hazardous fluid leakage; (3) propellant loading procedures and operations; (4) pressurization systems; and (5) propellant mass uncertainty.
Topics: NASA Technical Reports Server (NTRS), AUGMENTATION, SPACECRAFT PROPULSION, FUEL TANK...
This analysis is used to evaluate, from a cost and benefit perspective, potential outcomes when replacing the pressurization switches and the pressurization system to meet the needs of the LH2 storage system at Pad B. This also includes alternatives, tangible and intangible benefits, and the results of the analysis.
Topics: NASA Technical Reports Server (NTRS), COST EFFECTIVENESS, SWITCHES, FUEL TANK PRESSURIZATION,...
The manufacturing tasks for the program included the fabrication and assembly of an epoxy fiberglass purge bag to encapsulate an insulated cryogenic propellant tank. Purge, repressurization and venting hardware were procured and installed on the purge bag assembly in preparation for performance testing. The fabrication and installation of the superfloc multilayer insulation (MLI) on the cryogenic tank was accomplished as part of a continuing program. An abstraction of the results of the MLI...
Topics: NASA Technical Reports Server (NTRS), FUEL TANK PRESSURIZATION, MULTILAYER INSULATION, REUSABLE...
Dilution of gelant vapor with inert carrier gas accomplishes gelation. Mixture is injected through heated tube and orifice into liquid methane for immediate condensation within bulk of liquid. Direct dispersion of particles in liquid avoids condensation on walls of vessel and eliminates additional mixing.
Topics: NASA Technical Reports Server (NTRS), CONDENSATION, FUEL TANK PRESSURIZATION, GELATION, GELLED...
No abstract available
Topics: NASA Technical Reports Server (NTRS), CRYOGENICS, FUEL TANK PRESSURIZATION, CRYOGENIC FLUIDS,...
The shuttle orbital maneuvering system (OMS) pressure-volume-temperature (P-V-T) propellant gaging module computes the quantity of usable OMS propellant remaining based on the real gas P-V-T relationship for the propellant tank pressurant, helium. The OMS P-V-T propellant quantity gaging error was determined for four sets of instrumentation configurations and accuracies with the propellant tank operating in the normal constant pressure mode and in the blowdown mode. The instrumentation...
Topics: NASA Technical Reports Server (NTRS), MEASURING INSTRUMENTS, ORBIT MANEUVERING ENGINE (SPACE...
A thermodynamic study has been conducted that investigated the effects of the boost-phase environment on densified propellant thermal conditions for expendable launch vehicles. Two thermodynamic models were developed and utilized to bound the expected thermodynamic conditions inside the cryogenic liquid hydrogen and oxygen propellant tanks of an Atlas IIAS/Centaur launch vehicle during the initial phases of flight. The ideal isentropic compression model was developed to predict minimum...
Topics: NASA Technical Reports Server (NTRS), ROCKET PROPELLANTS, PROPELLANT TANKS, FUEL TANK...
This slide presentation reviews the development, validation and application of the model to the Lunar Landing Vehicle. The model named, Computational Propellant and Pressurization Program -- One Dimensional (CPPPO), is used to model in this case cryogenic propellant conditions of the Altair Lunar lander. The validation of CPPPO was accomplished via comparison to an existing analytic model (i.e., ROCETS), flight experiment and ground experiments. The model was used to the Lunar Landing Vehicle...
Topics: NASA Technical Reports Server (NTRS), CRYOGENICS, FUEL TANK PRESSURIZATION, MATHEMATICAL MODELS,...
Tasks accomplished during the HTTA Program study period included: (1) performance of a literature review to provide system guidelines; (2) development of analytical procedures needed to predict system performance; (3) design and analysis of the HTTA pressurization system considering (a) future utilization of results in the design of a spacecraft maneuvering system propellant package, (b) ease of control and operation, (c) system safety, and (d) hardware cost; and (4) making conclusions and...
Topics: NASA Technical Reports Server (NTRS), FUEL TANK PRESSURIZATION, HYDROGEN, SPACE SHUTTLE ORBITERS,...
This presentation is based on the experience gained from having integrated and flown a shuttle middeck experiment. The experiment, which demonstrated filling, expulsion, and fluid behavior of a liquid storage system under low-gravity conditions, is briefly described. The advantages and disadvantages of middeck payloads compared to other shuttle payload provisions are discussed. A general approach to the integration process is described. The requirements for the shuttle interfaces--such as...
Topics: NASA Technical Reports Server (NTRS), BAYS (STRUCTURAL UNITS), EXPERIMENT DESIGN, FLUID MANAGEMENT,...
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585
Sep 20, 2010
09/10
by
Herberg, Joseph R.; Folta, David C
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Future NASA Earth Observing System (EOS) Spacecraft will make measurements of the earth's clouds, oceans, atmosphere, land and radiation balance. These EOS Spacecraft will be part of the NASA Mission to Planet Earth. This paper specifically addresses the EOS AM Spacecraft, referred to as 'AM' because it has a sun-synchronous orbit with a 10:30 AM descending node. This paper describes the EOS AM Spacecraft mission orbit requirements, orbit determination, orbit control, and navigation system...
Topics: CRYOGENIC FLUID STORAGE, LIQUID OXYGEN, SPACE TRANSPORTATION SYSTEM, FLUID MANAGEMENT, FUEL TANK...
A ground test program was conducted to verify several of the design methods and techniques that were used in designing cryogenic acquisition/expulsion systems. The testing of a 63.5-cm diameter DSL subscale model was particularly significant. Under these tests, the operational characteristics of the DSL concept were verified using LH2 and LN2. Demonstration of the gas free liquid expulsion characteristics was accomplished by expelling LH2 under -1 g using both GH2 and GHe pressurization....
Topics: NASA Technical Reports Server (NTRS), CRYOGENIC ROCKET PROPELLANTS, FUEL FLOW REGULATORS,...
Two orbital test plans were prepared to verify one of the passive cryogenic storage tank/feedline candidate designs. One plan considered the orbital test article to be launched as a dedicated payload using an Atlas F burner launching configuration. The second plan proposed to launch the orbital test article as a secondary payload on the Titan E/Centaur proof flight. The secondary payload concept was pursued until January 1973, when work to build the hardware for this phase of the contract was...
Topics: NASA Technical Reports Server (NTRS), CRYOGENIC ROCKET PROPELLANTS, FLIGHT TESTS, FUEL FLOW...
To test and validate key capabilities and technologies required for future exploration elements such as large cryogenic propulsion stages and propellant depots, NASA is leading the efforts to develop and design the Cryogenic Propellant Storage and Transfer (CPST) Cryogenic Fluid Management (CFM) payload. The primary objectives of CPST payload are to demonstrate: 1) in-space storage of cryogenic propellants for long duration applications; and 2) in-space transfer of cryogenic propellants. The...
Topics: NASA Technical Reports Server (NTRS), VENTS, SYSTEMS ANALYSIS, CRYOGENIC ROCKET PROPELLANTS,...
No abstract available
Topics: NASA Technical Reports Server (NTRS), FUEL TANK PRESSURIZATION, PROPELLANT TANKS, CRYOGENICS,...
An analysis to predict the pressurant gas requirements for the discharge of cryogenic liquid propellants from storage tanks is presented, along with an algorithm and two computer programs. One program deals with the pressurization (ramp) phase of bringing the propellant tank up to its operating pressure. The method of analysis involves a numerical solution of the temperature and velocity functions for the tank ullage at a discrete set of points in time and space. The input requirements of the...
Topics: NASA Technical Reports Server (NTRS), COMPUTER PROGRAMS, CRYOGENIC ROCKET PROPELLANTS, EXPULSION,...
Four Arde conospheroid metallic diaphragms were tested to evaluate their capability for use in the orbit adjust propulsion subsystem (OAPS) of the Explorer spacecraft. The diaphragms will be used for positive propellant expulsion and spacecraft center of mass control. A leak-free cycle life capability of nine reversals was demonstrated. The diaphragms rolled smoothly from ring to ring in a predictable manner on the first reversal. Varying amounts of diaphragm cocking and ring skipping were...
Topics: NASA Technical Reports Server (NTRS), DIAPHRAGMS (MECHANICS), EXPULSION BLADDERS, LIQUID ROCKET...
The Centaur space launch vehicle airborne computer, which was primarily used to perform guidance, navigation, and sequencing tasks, was further used to monitor and control inflight pressurization and venting of the cryogenic propellant tanks. Computer software flexibility also provided a failure detection and correction capability necessary to adopt and operate redundant hardware techniques and enhance the overall vehicle reliability.
Topics: NASA Technical Reports Server (NTRS), AIRBORNE/SPACEBORNE COMPUTERS, CENTAUR LAUNCH VEHICLE,...
Guidelines for the successful design of pressurization systems for main propulsion, auxiliary propulsion, and attitude control systems for boosters, upper stages, and spacecraft were presented, drawing on the wealth of design experience that has accumulated in the development of pressurization systems for liquid rockets operational in the last 15 years. The design begins with a preliminary phase in which the system requirements are received and evaluated. Next comes a detail-design and...
Topics: NASA Technical Reports Server (NTRS), FUEL TANK PRESSURIZATION, LIQUID PROPELLANT ROCKET ENGINES,...
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205
May 29, 2011
05/11
by
Springer, Anthony M
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This document is a viewgraph presentation which reviews the progress in the X-34 Project. The X-34 program demonstrates the technologies and operations required to develop the next generation of reusable launch vehicles. The presentation includes descriptions and design views of the vehicle. It reviews features of the MC-1 (i.e. Fastrac Engine), and the propulsion system. It also includes information about the thermal protection system.
Topics: FUEL TANK PRESSURIZATION, RP-1 ROCKET PROPELLANTS, FEED SYSTEMS, COMPUTERIZED SIMULATION, HELIUM,...
NASA Lewis Research Center's Cryogenic Fluid Systems Branch (CFSB) within the Space Propulsion Technology Division (SPTD) has the ultimate goal of enabling the long term storage and in-space fueling/resupply operations for spacecraft and reusable vehicles in support of space exploration. Using analytical modeling, ground based testing, and on-orbit experimentation, the CFSB is studying three primary categories of fluid technology: storage, supply, and transfer. The CFSB is also investigating...
Topics: NASA Technical Reports Server (NTRS), CRYOGENIC FLUID STORAGE, FLUID MANAGEMENT, PROPELLANT...
No abstract available
Topics: NASA Technical Reports Server (NTRS), GROUND TESTS, CRYOGENIC FLUIDS, STORAGE TANKS, FUEL TANK...
Single-walled, jacketed aluminum tanks have been conceived for storing liquefied natural gas (LNG) in LNG-fueled motor vehicles. Heretofore, doublewall steel tanks with vacuum between the inner and outer walls have been used for storing LNG. In comparison with the vacuum- insulated steel tanks, the jacketed aluminum tanks weigh less and can be manufactured at lower cost. Costs of using the jacketed aluminum tanks are further reduced in that there is no need for the vacuum pumps heretofore...
Topics: NASA Technical Reports Server (NTRS), LIQUEFIED NATURAL GAS, STORAGE TANKS, ALUMINUM, COMPOSITE...
The library for Mathworks Simscape does not currently contain a model for a closed volume fluid tank where the ullage pressure is variable. In order to model a closed-volume variable ullage pressure tank, it was necessary to consider at least two separate cases: a vertical cylinder, and a sphere. Using library components, it was possible to construct a rough model for the cylindrical tank. It was not possible to construct a model for a spherical tank, using library components, due to the...
Topics: NASA Technical Reports Server (NTRS), FUEL TANKS, CYLINDRICAL TANKS, SPHERICAL TANKS, FUEL TANK...
252
252
Jun 21, 2010
06/10
by
Kashyap, R. L
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Maximum likelihood identification of stochastic linear systems
Topics: APOLLO 8 FLIGHT, STAGE SEPARATION, PROPULSION SYSTEM PERFORMANCE, SATURN S-2 STAGE, FUEL TANK...
Two transient operational modes of the X-34 pressurization system were analyzed using the ROCket Engine Transition Simulation (ROCETS) program. The first operational mode considers the normal operation. For the engine burn period, the required helium mass and pressure of each propellant tank were calculated. In the second case, the possibility of failure of the pressurization system solenoid valves, its consequence on the over-pressurization, and simultaneous operation of pressurization and...
Topics: NASA Technical Reports Server (NTRS), X-34 REUSABLE LAUNCH VEHICLE, ROCKET ENGINES, FUEL TANK...
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385
May 26, 2011
05/11
by
Cobleigh, Brent R
texts
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An aerodynamic uncertainty model for the X-33 single-stage-to-orbit demonstrator aircraft has been developed at NASA Dryden Flight Research Center. The model is based on comparisons of historical flight test estimates to preflight wind-tunnel and analysis code predictions of vehicle aerodynamics documented during six lifting-body aircraft and the Space Shuttle Orbiter flight programs. The lifting-body and Orbiter data were used to define an appropriate uncertainty magnitude in the subsonic and...
Topics: PROPULSION SYSTEM PERFORMANCE, EJECTORS, OPERATIONAL PROBLEMS, BOOSTER ROCKET ENGINES, PROPELLANT...
No abstract available
Topics: NASA Technical Reports Server (NTRS), PRESSURE VESSELS, SAFETY, SAFETY MANAGEMENT, FUEL TANK...
Contaminant-resistant seal designs and a dynamically stable prototype check valve for the orbital maneuvering and reaction control helium pressurization systems of the space shuttle were developed. Polymer and carbide seal models were designed and tested. Perfluoroelastomers compatible with N2O4 and N2H4 types were evaluated and compared with Teflon in flat and captive seal models. Low load sealing and contamination resistance tests demonstrated cutter seal superiority over polymer seals....
Topics: NASA Technical Reports Server (NTRS), CONTROL VALVES, ORBIT MANEUVERING ENGINE (SPACE SHUTTLE),...
A pressurization system model was developed for a generic bimese Two-Stage-to-orbit Reusable Launch Vehicle using a cross-feed system and operating with densified propellants. The model was based on the pressurization system model for a crossfeed subscale water test article and was validated with test data obtained from the test article. The model consists of the liquid oxygen and liquid hydrogen pressurization models, each made up of two submodels, Booster and Orbiter tank pressurization...
Topics: NASA Technical Reports Server (NTRS), PRESSURIZING, REUSABLE LAUNCH VEHICLES, FUEL TANK...
A conceptual design study was conducted to devise and evaluate techniques for the external vaporization of fuel for use in an aircraft gas turbine with characteristics similar to the Energy Efficient Engine (E(3)). Three vaporizer concepts were selected and they were analyzed from the standpoint of fuel thermal stability, integration of the vaporizer system into the aircraft engine, engine and vaporizer dynamic response, startup and altitude restart, engine performance, control requirements,...
Topics: NASA Technical Reports Server (NTRS), FUEL TANK PRESSURIZATION, GAS TURBINE ENGINES, THERMAL...
Results are presented for pressure-volume-temperature (PVT) gauging of a liquid oxygen/liquid nitrogen tank pressurized with gaseous helium that was supplied by a high-pressure cryogenic tank simulating a cold helium supply bottle on a spacecraft. The fluid inside the test tank was kept isothermal by frequent operation of a liquid circulation pump and spray system, and the propellant tank was suspended from load cells to obtain a high-accuracy reference standard for the gauging measurements....
Topics: NASA Technical Reports Server (NTRS), PROPELLANT TANKS, LIQUID OXYGEN, LIQUID NITROGEN, HELIUM,...
A review of technology, history, and current status for pressurized expulsion of cryogenic tankage is presented. Use of tank pressurization to expel cryogenic fluids will continue to be studied for future spacecraft applications over a range of operating conditions in the low-gravity environment. The review examines experimental test results and analytical model development for quiescent and agitated conditions in normal-gravity, followed by a discussion of pressurization and expulsion in...
Topics: NASA Technical Reports Server (NTRS), CRYOGENIC COMPUTER STORAGE, CRYOGENIC FLUIDS, FINITE...
The Zero Boil-Off Technology (ZBOT) Experiment involves performing a small scale ISS experiment to study tank pressurization and pressure control in microgravity. The ZBOT experiment consists of a vacuum jacketed test tank filled with an inert fluorocarbon simulant liquid. Heaters and thermo-electric coolers are used in conjunction with an axial jet mixer flow loop to study a range of thermal conditions within the tank. The objective is to provide a high quality database of low gravity fluid...
Topics: NASA Technical Reports Server (NTRS), FUEL TANK PRESSURIZATION, CRYOGENIC FLUIDS, COMPUTATIONAL...
An unsteady finite volume procedure has been developed to predict the history of pressure, temperature and mass flow rate of the pressurant and propellant during the expulsion of the propellant from a tank. The time dependent mass, momentum and energy conservation equations are solved at the ullage space. The model accounts for the change in the ullage volume due to expulsion of the propellant. It also accounts for the heat transfer from the tank wall and propellant to the ullage gas. The...
Topics: NASA Technical Reports Server (NTRS), ENERGY CONSERVATION, FUEL TANK PRESSURIZATION, HEAT TRANSFER,...
The use of Tri-gas in rocket propulsion systems is somewhat of a new technology. This paper defines Tri-gas as a mixture of gases composed largely of helium with a small percentage of a stoichiometric mixture of hydrogen and oxygen. When exposed to a catalyst the hydrogen and oxygen in the mixture combusts, significantly raising the temperature of the mixture. The increase in enthalpy resulting from the combustion process significantly decreases the required quantity of gas needed to pressurize...
Topics: NASA Technical Reports Server (NTRS), GAS MIXTURES, CRYOGENICS, PROPULSION SYSTEM PERFORMANCE,...
As space shuttle tanks are loaded with N2O4, pressurization gas is displaced and at the same time N2O4 entering the tank evaporates and mixes with the pressurization gas remaining in the tank. Further addition of N2O4 to the tank requires venting of this mixture of N2O4/NO2 vapor and pressurization gas, which must be scrubbed prior to atmospheric release. A computer analysis was performed to estimate concentrations, flow rates, and total quantities vented during the planned fast fill/slow fill...
Topics: NASA Technical Reports Server (NTRS), FUEL TANKS, LOADING OPERATIONS, NITROGEN TETROXIDE, SPACE...
Trade studies plans for a number of elements in the Liquid Rocket Booster (LRB) component of the Space Transportation System (STS) are given in viewgraph form. Some of the elements covered include: avionics/flight control; avionics architecture; thrust vector control studies; engine control electronics; liquid rocket propellants; propellant pressurization systems; recoverable spacecraft; cryogenic tanks; and spacecraft construction materials.
Topics: NASA Technical Reports Server (NTRS), AVIONICS, BOOSTER ROCKET ENGINES, ROCKET ENGINE CONTROL,...
An unsteady finite volume procedure has been developed to predict the history o pressure, temperature and mass flow rate of the pressurant and propellant during the expulsion of the propellant from a tan. The time dependent mass, momentum and energy conservation equations are solved at the ullage space. The model accounts for the change in the ullage volume due to expulsion of the propellant. It also accounts for the heat transfer from the tank wall and propellant to the ullage gas. The...
Topics: NASA Technical Reports Server (NTRS), FUEL TANK PRESSURIZATION, PROPELLANT TANKS, MATHEMATICAL...
The Vented Tank Resupply Experiment (VTRE) Program is a NASA In-Space Technology Experiments Program (IN-STEP) that will develop, and fly a small, low cost space experiment to investigate, develop, and acquire needed data to extend and advance the technology of capillary vane fluid management devices to applications requiring direct venting of gas from tanks in low-gravity. GAS venting may be required for control of pressure, or to allow low-g fill of a tank with liquid while holding a constant...
Topics: NASA Technical Reports Server (NTRS), AEROSPACE ENVIRONMENTS, EXPERIMENT DESIGN, FLUID MANAGEMENT,...
Laminar models agree closely with the pressure evolution and vapor phase temperature stratification but under-predict liquid temperatures. Turbulent SST k-w and k-e models under-predict the pressurization rate and extent of stratification in the vapor but represent liquid temperature distributions fairly well. These conclusions seem to equally apply to large cryogenic tank simulations as well as small scale simulant fluid pressurization cases. Appropriate turbulent models that represent both...
Topics: NASA Technical Reports Server (NTRS), COMPUTATIONAL FLUID DYNAMICS, TEMPERATURE DISTRIBUTION, VAPOR...
A computational fluid dynamics (CFD) model is developed to simulate pressure control of an ellipsoidal-shaped liquid hydrogen tank under external heating in normal gravity. Pressure control is provided by an axial jet thermodynamic vent system (TVS) centered within the vessel that injects cooler liquid into the tank, mixing the contents and reducing tank pressure. The two-phase cryogenic tank model considers liquid hydrogen in its own vapor with liquid density varying with temperature only and...
Topics: NASA Technical Reports Server (NTRS), FUEL TANK PRESSURIZATION, COMPUTATIONAL FLUID DYNAMICS,...
A series of tests were conducted to evaluate the performance of a propellant tank pressurization system with the pressurant diffuser intentionally submerged beneath the surface of the liquid. Propellant tanks and pressurization systems are typically designed with the diffuser positioned to apply pressurant gas directly into the tank ullage space when the liquid propellant is settled. Space vehicles, and potentially propellant depots, may need to conduct tank pressurization operations in...
Topics: NASA Technical Reports Server (NTRS), LIQUID HYDROGEN, PROPELLANT TANKS, LIQUID ROCKET PROPELLANTS,...
The Low Profile Diffuser (LPD) project originated as an award from the Marshall Space Flight Center (MSFC) Advanced Development (ADO) office to the Main Propulsion Systems Branch (ER22). The task was created to develop and test an LPD concept that could produce comparable performance to a larger, traditionally designed, ullage gas diffuser while occupying a smaller volume envelope. Historically, ullage gas diffusers have been large, bulky devices that occupy a significant portion of the...
Topics: NASA Technical Reports Server (NTRS), SPACECRAFT LAUNCHING, ULLAGE, PROPELLANT TANKS, OXYGEN, FUEL...
No abstract available
Topics: NASA Technical Reports Server (NTRS), PROPELLANT TRANSFER, CRYOGENIC TANKS, FUEL TANK...
A final report on the Operationally Efficient Propulsion System Study (OEPSS) is presented. A review of Launch Site Operations, OEPSS objectives, operations support structure, OEPSS Concerns List, and scope of OEPSS are summarized, along with goals of OEPSS technologies, and operations technology levels. Air-augmented ejector/rocket, flash boiling tank pressurization technology, and advanced LH2 turbopump are described. Launch facilities, operations-driven propulsion system architecture,...
Topics: NASA Technical Reports Server (NTRS), PROPULSION SYSTEM PERFORMANCE, ADVANCED LAUNCH SYSTEM (STS),...
