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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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At least 127 records · Page 7
All sourcesNASA NTRSDOE OSTI
NASA NTRS2004

Lightweight, Low-CTE Tubes Made From Biaxially Oriented LCPs

Tubes made from biaxially oriented liquid-crystal polymers (LCPs) have been developed for use as penetrations on cryogenic tanks. ( Penetrations in this context denotes feed lines, vent lines, and sensor tubes, all of which contribute to the undesired conduction of heat into the tanks.) In comparison with corresponding prior cryogenic-tank penetrations made from stainless steels and nickel alloys, the LCP penetrations offer advantages of less weight and less thermal conduction. An additional major advantage of LCP components is that one can tailor their coefficients of thermal expansion (CTEs). The estimated cost of continuous production of LCP tubes of typical sizes is about $1.27/ft ($4.17/m) [based on 1998 prices]. LCP tubes that are compatible with liquid oxygen and that feature tailored biaxial molecular orientation and quasi-isotropic properties (including quasi-isotropic CTE) have been fabricated by a combination of proprietary and patented techniques that involve the use of counterrotating dies (CRDs). Tailoring of the angle of molecular orientation is what makes it possible to tailor the CTE over a wide range to match the CTEs of adjacent penetrations of other tank components; this, in turn, makes it possible to minimize differential-thermal expansion stresses that arise during thermal cycling. The fabrication of biaxially oriented LCP tubes by use of CRDs is not new in itself. The novelty of the present development lies in tailoring the orientations and thus the CTEs and other mechanical properties of the LCPs for the intended cryogenic applications and in modifications of the CRDs for this purpose. The LCP tubes and the 304-stainless-steel tubes that the LCP tubes were intended to supplant were tested with respect to burst strength, permeability, thermal conductivity, and CTE.

Rubin, Leslie↗
NASA NTRSDate not supplied

Design of an Adsorption Bed for Exploration Trace Contaminant Control

The state-of-the-art in long mission duration spacecraft trace contaminant control processes relies on physical and chemical adsorption for contaminant removal. Target species for adsorption include low and semivolatile organic compounds while chemisorption is utilized for metabolic ammonia control. When adsorption is employed in conjunction with a high temperature oxidation process, a complementary impact on cabin air quality may be realized. The adsorption bed also serves to guard the downstream oxidation catalyst from foulants and potential poisons which may decrease its lifetime and activity. To this end, a packed adsorption guard-bed was sized to control a statistical contaminant load model over a simulated Mars transit mission duration. The updated load model incorporates flight air-quality data and contemporary metabolic source emission literature. The guard-bed was operated in tandem with an exploration prototype thermal catalytic oxidizer. The exploration guard-bed prototype included design considerations from recent flight technology demonstrations and changes intended to improve compatibility with enriched oxygen exploration cabin environments as compared to the prior-art of contaminant control system design.

Trace Contaminant Control↗
NASA NTRS1992

Neutralizer and sample chamber for the Atomic Oxygen Simulation System (AOSS)

A neutralizer system capable of converting a beam of oxygen ions (O(+) or O2(+)) into a beam of low-energy neutral oxygen atoms (O) was developed. The neutralizer system is to be designed to be compatible with the Atomic Oxygen Simulation System (AOSS) located in the Physical Science Branch of MSFC. The Center for Molecular and Atomic Studies at Surfaces (CMASS) at Vanderbilt University has met these objectives by developing a system that neutralizes the ions through electron transfer during a grazing-incidence reflection of an ion beam from a smooth nickel surface. The purpose is to describe the system, provide schematic representations of the system, and to discuss the use of the system in relation to the AOSS at the Physical Science Branch of MSFC.

Albridge, Royal G.↗
NASA NTRS1972

Liquid and gaseous oxygen safety review, volume 1

Materials used or contained in liquid and gaseous oxygen systems are analyzed for their compatibility; and areas of possible concern in oxygen systems are outlined. Design criteria, cleaning procedures, and quality control methods are covered in detail.

Lapin, A.↗
NASA NTRS2012

The Search for Nonflammable Solvent Alternatives for Cleaning Aerospace Oxygen Systems

To obtain a high degree of cleanliness without risk of corrosion or hazardous reactivity, hydrochlorofluorocarbon (HCFC)-225 is used for cleaning and cleanliness verification of oxygen system components used on NASA fs bipropellant launch vehicles, associated test stands and support equipment. HCFC-225 is a Class II Ozone Depleting Substance (ODS ]II) that was introduced to replace chlorofluorocarbon (CFC)-113, a Class I ODS solvent that is now banned. To meet environmental regulations to eliminate the use of ozone depleting substances, a replacement solvent is required for HCFC ]225 that is effective at removing oils, greases, and particulate from large oxygen system components, is compatible with materials used in the construction of these systems, and is nonflammable and non ]reactive in enriched oxygen environments. A solvent replacement is also required for aviator fs breathing oxygen systems and other related equipment currently cleaned and verified with HCFC ]225 and stockpiled CFC -113. Requirements and challenges in the search for nonflammable replacement solvents are discussed.

Mitchell, Mark A.↗
NASA NTRS1994

Simplex turbopump design

Turbomachinery used in liquid rocket engines typically are composed of complex geometries made from high strength-to-weight super alloys and have long design and fabrication cycle times (3 to 5 years). A simple, low-cost turbopump is being designed in-house to demonstrate the ability to reduce the overall cost to $500K and compress life cycle time to 18 months. The simplex turbopump was designed to provide a discharge pressure of 1500 psia of liquid oxygen at 90 lbm/s. The turbine will be powered by gaseous oxygen. This eliminates the need for an inter-propellant seal typically required to separate the fuel-rich turbine gases from the liquid oxygen pump components. Materials used in the turbine flow paths will utilize existing characterized metals at 800 deg R that are compatible with a warm oxygen environment. This turbopump design would be suitable for integration with a 40 K pound thrust hybrid motor that provides warm oxygen from a tapped-off location to power the turbine. The preliminary and detailed analysis was completed in a year by a multiple discipline, concurrent engineering team. Manpower, schedule, and cost data were tracked during the process for a comparison to the initial goal. The Simplex hardware is the procurement cycle with the expectation of the first test to occur approximately 1.5 months behind the original schedule goal.

Marsh, Matt↗
NASA NTRS1971

Impact sensitivity of materials in contact with liquid and gaseous oxygen at high pressures.

An apparatus developed by Marshall Space Flight Center for use in determining the impact sensitivity of engineering materials in liquid and gaseous oxygen at pressures greater than one atmosphere is described. This apparatus uses the impact tester described in ASTM D2512, ?Compatibility of Materials with Liquid Oxygen,' with the addition of a pressurized sample holder in place of the D2512 anvil region.

Key, C. F.↗
NASA NTRS1975

ASRDI oxygen technology survey. Volume 8: Pressure measurement

Pressure transducers and their current uses with gaseous or liquid oxygen are reviewed. All transducer types such as strain gage, capacitance, potentiometric, piezoelectric, etc., are included. Topics covered include: cryogenic pressure measurement; material compatibility with gaseous and liquid oxygen; cleaning procedures; pressure tap connections; transducer types and descriptions; and calibration techniques.

Arvidson, J. M.↗
NASA NTRS1993

A mechanism for the reduction in risk of decompression sickness in microgravity environment

There is an apparent reduction in the incidence of decompression sickness reported by astronauts (from both the USA and the USSR) during extravehicular activity (EVA). The expected incidence, based on studies conducted under unit gravity conditions in Earth-based laboratories, is greater than that encountered during EVA. A biophysical explanation has been proposed for this difference based upon the mechanism of stress-assisted nucleation. Since the partial pressure ratio at which this gas phase forms is considerably smaller in living systems that in quiescent in vitro models, it was proposed that mechanical forces are involved. In that the lower extremities of astronautics are not gravitationally loaded in microgravity, it is possible that tissue gas micronuclei are but minimally regenerated. Most likely, gas micronuclei formed on Earth (by ambulation under 1 g conditions) would be eventually depleted. In a crossover study, 20 individuals were decompressed--from 1 ATA to 0.43 ATA for 3 hours--following either being fully ambulatory at unit gravity or following being hypokinetic and adynamic (simulated microgravity of 3-day bed rest). The subjects were monitored for gas phase formation by means of precordial Doppler monitoring. The results indicate a reduction in whole body gas phase formation in individuals who were bed rested as compared with themselves when fully ambulatory (p = 0.02). In hypokinetic individuals, the protection conferred was equivalent to an extra 175 minutes of oxygen prebreathe. These results are compatible with a hypothesis relating stress-assisted nucleation to the continual formation of tissue gas micronuclei and their gradual depletion with hypokinesia.

Powell, Michael R.↗
NASA NTRS2003

Isothermal Microcalorimetric Evaluation of Compatibility of Proposed Injector Materials with High-Test Hydrogen Peroxide Propellant

High-test hydrogen peroxide (HTP) is receiving renewed interest as a monopropellant and as the oxidizer for bipropellant systems. HTP is hydrogen peroxide in concentrations ranging from 70 to 98%. All surfaces wetted by HTP must be evaluated for compatibility with the fluid. In the case of tanks, lines and valves compatibility is required to preserve the HTP oxygen and energy content and to avoid overpressurization due to decomposition. With injectors and regenerative cooling passages shorter exposure time reduces these concerns. However, phase changes from fluid to gas impact heat transfer and become the dominant compatibility concern. Isothermal microcalorimetry (IMC) provides a convenient and reproducible means to observe the decomposition of HTP when exposed to structural materials and therefore the compatibility of those materials'. The instrument provides heat flow values in terms of watts that may be converted to a reaction rate given the heat of reaction for the decomposition of hydrogen peroxide. These values are then converted to percent active oxygen loss per week (%AOL/wk) to preserve an earlier convention for quantifying HTP compatibility. Additionally, qualitative designations of compatibility have been assigned to these values. This scheme consists of four classes with Class 1 being the most compatible. While historical compatibility data is available its current applicability is in question due to subtle changes in the compositions of both HTP and structural materials. Trace levels of molecules can have significant influence on compatibility. Therefore representative samples of materials must be evaluated with current HTP formulations. In this work seven materials were selected for their strength characteristics at high temperature as expected in a HTP injector. The materials were then evaluated by IMC for HTP compatibility.

Gostowski, Rudy↗
NASA NTRS1993

A high specific power solar array for low to mid-power spacecraft

UltraFlex is the generic term for a solar array system which delivers on-orbit power in the 400 to 6,000 watt per wing sizes with end-of-life specific power performance ranging to 150 watts-per-kilogram. Such performance is accomplished with off-the-shelf solar cells and state-of the-art materials and processes. Much of the recent work in photovoltaics is centered on advanced solar cell development. Successful as such work has been, no integrated solar array system has emerged which meets NASA's stated goals of 'increasing the end-of-life performance of space solar cells and arrays while minimizing their mass and cost.' This issue is addressed; namely, is there an array design that satisfies the usual requirements for space-rated hardware and that is inherently reliable, inexpensive, easily manufactured and simple, which can be used with both advanced cells currently in development and with inexpensive silicon cells? The answer is yes. The UltraFlex array described incorporates use of a blanket substrate which is thermally compatible with silicon and other materials typical of advanced multi-junction devices. The blanket materials are intrinsically insensitive to atomic oxygen degradation, are space rated, and are compatible with standard cell bonding processes. The deployment mechanism is simple and reliable and the structure is inherently stiff (high natural frequency). Mechanical vibration modes are also readily damped. The basic design is presented as well as supporting analysis and development tests.

Jones, P. Alan↗
NASA NTRS1971

Nonmetallic-material configuration control in the Apollo spacecraft

The methods employed by NASA to establish configuration control of nonmetallic materials on Apollo spacecraft are described. A five step procedure for examining contractor materials for suitability and compatibility is presented. The compatibility of the materials with the oxygen enriched environment of the spacecraft enclosures is emphasized.

Steinthal, M. W.↗
NASA NTRS1971

Apollo spacecraft nonmetallic materials applications

The applications of nonmetallic materials to the structures of Apollo spacecraft are discussed. The spacecraft components are examined and the rationale behind the use of specific nonmetallic materials is presented. The emphasis is on the compatibility of the materials with the oxygen enriched atmosphere of the spacecraft enclosures.

Craig, J. W.↗
NASA NTRS1987

Bonding Lexan and sapphire to form high-pressure, flame-resistant window

Flammable materials have been studied in normal gravity and microgravity for many years. Photography plays a major role in the study of the combustion process giving a permanent visual record that can be analyzed. When these studies are extended to manned spacecraft, safety becomes a primary concern. The need for a high-pressure, flame-resistant, shatter-resistant window permitting photographic recording of combustion experiments in manned spacecraft prompted the development of a method for bonding Lexan and sapphire. Materials that resist shattering (e.g., Lexan) are not compatible with combustion experiments; the material loses strength at combustion temperatures. Sapphire is compatible with combustion temperatures in oxygen-enriched atmospheres but is subject to shattering. Combining the two materials results in a shatter-resistant, flame-resistant window. Combustion in microgravity produces a low-visibility flame; however, flame propagation and flame characteristics are readily visible as long as there is no deterioration of the image. Since an air gap between the Lexan and the sapphire would reduce transmission, a method was developed for bonding these unlike materials to minimize light loss.

Richardson, William R.↗
NASA NTRS1988

Electromagnetic dampers for cryogenic applications

Cryogenic turbomachinery of the type used to pump high-pressure liquid hydrogen at -423 F and liquid oxygen at -297 F to the main engines of the Space Shuttle are subjected to lateral rotor vibrations from unbalance forces and transient loads. Conventional dampers which utilize viscous fluids such as lubricating oil cannot be used in turbopumps because the bearing components are filled with either liquid hydrogen or liquid oxygen, which have viscosity comparable to air and, therefore, are not effective in viscous dampers. Electromagentic dampers are currently being explored as a means of providing damping in cryogenic turbopumps because their damping effectiveness increases as temperature decreases and because they are compatible with the liquid hydrogen or liquid oxygen in the turbopumps.

Brown, Gerald V.↗