Optimum mixing of hypergolic propellants in an unlike doublet injector element
Optimum penetration and separation mixing of unlike doublet injector element with hypergolic hydrazine and nitrogen tetroxide propellants
Houseman, J.↗
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Reactive stream separation photography
Reactive stream separation high speed color photography for impinging streams of nitrogen tetroxide and hydrazine
Campbell, D. T.↗
Titanium alloy pressure vessels in the manned space program
Stress corrosion cracking of Ti alloys in nitrogen tetroxide and methyl alcohol environments in Apollo spacecraft pressure vessels
Johnson, R. E.↗
Liquid phase reactions of hypergolic propellants Final report
Measuring heat and gas release rates for initial reaction of liquid nitrogen tetroxide with hydrazine, monomethyl hydrazine, and unsymmetric dimethyl hydrazine
Axworthy, A. E.↗
Synthesis of elastomers for use with liquid fluorine Final report
Synthesis and chemical properties of elastomeric polymers resistant to effects of fluorine, oxygen difluoride, nitrogen tetroxide, and similar agents
Brown, H. C.↗
The effect of composition on the mechanism of stress-corrosion cracking of titanium alloys in N2O4, and aqueous and hot-salt environments, part 2
Metal composition effects on stress corrosion cracking of titanium alloys in nitrogen tetroxide, water, and salt
Boyd, J. D.↗
Leaching of nitroso rubber material removes uncured polymer
New leaching process removes uncured polymer from nitroso rubber, elastomer used in presence of nitrogen tetroxide. Uncured portion is removed by controlled soaking of polymer slab in Freon TF. Leaching with Freon TF prevents nitroso rubber from adhering to adjoining surfaces and limiting its usefulness in either static or dynamic applications.
Bratfisch, W. A.↗
Material Compatibility with Space Storable Propellants. Design Guidebook
An important consideration in the design of spacecraft for interplanetary missions is the compatibility of storage materials with the propellants. Serious problems can arise because many propellants are either extremely reactive or subject to catalytic decomposition, making the selection of proper materials of construction for propellant containment and control a critical requirement for the long-life applications. To aid in selecting materials and designing and evaluating various propulsion subsystems, available information on the compatibility of spacecraft materials with propellants of interest was compiled from literature searches and personal contacts. The compatibility of both metals and nonmetals with hydrazine, monomethyl hydrazine, nitrated hydrazine, and diborance fuels and nitrogen tetroxide, fluorine, oxygen difluoride, and Flox oxidizers was surveyed. These fuels and oxidizers encompass the wide variety of problems encountered in propellant storage. As such, they present worst case situations of the propellant affecting the material and the material affecting the propellant. This includes material attack, propellant decomposition, and the formation of clogging materials.
Uney, P. E.↗
Preliminary results of large supersonic burning combustor testing.
A hydrogen fueled supersonic-burning combustor 18 in. in diameter, which is equivalent to that of an engine about 6 ft in diameter, was tested as a direct-connected duct at inlet conditions which simulated Mach 8 flight at 115,000 ft alt. A synthetic air consisting of oxygen with 39% nitrogen and 38% water vapor at a total temperature of 4500 deg R and a total pressure of 300 psia was supplied to the combustor inlet by a hydrazine-nitrogen tetroxide hot gas generator which maintained a uniform inlet flow Mach number of 2.8. The large combustor size required a new approach to fuel injector design. Some hydrogen was injected through flush-wall injectors, but most was injected from two rows of swept and tapered struts immersed in the flow stream. Supersonic combustion was obtained at hydrogen equivalence ratios of 0.94 without encountering thermal cho king. Wall static pressures, and the radial distribution of hydrogen, Pitot pressure, and Mach number were determined at the combustor exit.
Metzler, A. J.↗
Control of Nitrogen Dioxide in Stack Emission by Reaction with Ammonia
The development of an acid base gas-phase reaction system which utilizes anhydrous ammonia as the reactant to remove nitrogen dioxide from hydrazine-nitrogen tetroxide rocket combustion exhaust is reported. This reaction reduced NO2 levels in exhaust emissions so that the resulting stack emission is completely white instead of the earlier observed typical reddish-brown coloration. Preliminary analyses indicate the importance of reaction time and ammonia concentration on removal efficiency and elimination of the health hazard to individuals with respiratory problems.
Metzler, A. J.↗
Study to Optimize Gellant Polymer-Water Systems for the Control of Hypergolic Spills and Fires
A system of buffered gelled water was developed to prevent and control fires from small spills of nitrogen tetroxide-(N2O4)-Aerozine 50-hypergolic fuel. Laboratory studies on various alkalis, buffers, and seavengers for the fuel components are described. Chilling and sodium acetate-acetic acid buffer was found to be the best additives to the gelled water. Field tests and a delivery system (airborne) for the extinguishant are described.
Jennings, R. R.↗
Apollo 16 Mission: Oxidizer Deservicing Tank Failure: Anomaly Report - No. 1
An explosive failure of a ground support equipment decontamination unit tank occurred during the postflight deactivation of the oxidizer (nitrogen tetroxide) portion of the Apollo 16 command module reaction control system. A discussion of the significant aspects of the incident and conclusions are included.
Source record↗
The Viking Orbiter 1975 beryllium INTEREGEN rocket engine assembly.
Description of the conversion of the Mariner 9 rocket engine for Viking Orbiter use. Engine conversion consists of replacing the 40:1 expansion area ratio nozzle with a 60:1 nozzle of the internal regeneratively (INTEREGEN) cooled rocket engine. Five converted engines using nitrogen tetroxide and monomethylhydrazine demonstrated thermal stability during the nominal 2730-sec burn, but experienced difficulty at operating extremes. The thermal stability characteristic was treated in two ways. The first treatment consisted of mapping the operating regime of the engine to determine its safest operating boundaries as regards thermal equilibrium. Six engines were used for this purpose. Two of the six engines were then modified to effect the second approach - i.e., extend the operating regime. The engines were modified by permitting fuel injection into the acoustic cavity.
Martinez, R. S.↗
An application of a space technique for pollution detection.
Description of the hazardous gas detection system (HGDS) used during Apollo-Saturn launch tests for identifying and analyzing extremely minute amounts of gases escaping during cryogenic loading. These gases included hydrogen, helium, nitrogen, oxygen, nitrogen tetroxide, and hydrazine N2H3 radical. The heart of the HGDS is a mass spectrometer operating under high vacuum and capable to measure both qualitatively and quantitatively the presence and percentage of any gas whose molecular weight is between 2 and 150 atomic mass units. It is suggested that such a system could be utilized to detect environmental pollutants.
Hall, J. J.↗
Space shuttle seal material and design development for earth storable propellant systems
The results of a program to investigate and characterize seal materials suitable for space shuttle storable propellant systems are given. Two new elastomeric materials were identified as being potentially superior to existing state-of-the art materials for specific sealing applications. These materials were AF-E-124D and AF-E-411. AF-E-124D is a cured perfluorinated polymer suitable for use with dinitrogen tetroxide oxidizer, and hydrazine base fuels. AF-E-411 is an ethylene propylene terpolymer material for hydrazine base fuel service. Data are presented relative to low and high temperature characteristics as well as propellant exposure effects. Types of data included are: mechanical properties, stress strain curves, friction and wear characteristics, compression set and permeability. Sealing tests with a flat poppet-seal valve were conducted for verification of sealing capability. A bibliography includes over 200 references relating to seal design or materials and presents a concise tabulation of the more useful seal design data sources.
Source record↗
The hard start phenomena in hypergolic engines. Volume 2: Combustion characteristics of propellants and propellant combinations
The combustion characteristics of hypergolic propellants are described. A research project was conducted to determine if the reaction control system engine propellants on Apollo spacecraft undergo explosive reaction when subjected to conditions present in the engine at the time of ignition. Combustion characteristics pertinent to the hard-start phenomenon are considered. The thermal stability of frozen mixtures of hydrazine-based fuels with nitrogen tetroxide was analyzed. Results of the tests are presented in the form of tables and graphs.
Miron, Y.↗
SS/RCS surface tension propellant acquisition/expulsion tankage technology program
An evaluation of published propellant physical property data together with bubble point tests of fine-mesh screen in propellants, was conducted. The effort consisted of: (1) the collection and evaluation of pertinent physical property data for hydrazine (N2H4), monomethylhydrazine (MMH), and nitrogen tetroxide (N2O4); (2) testing to determine the effect of dissolved pressurant gas, temperature, purity, and system cleanliness or contamination on system bubble point, and (3) the compilation and publishing of both the literature and test results. The space shuttle reaction control system (SS/RCS) is a bipropellant system using N2O4 and MMH, while the auxiliary power system (SS/APU) employs monopropellant N2H4. Since both the RCS and the APU use a surface tension device for propellant acquisition, the propellant properties of interest are those which impact the design and operation of surface tension systems. Information on propellant density, viscosity, surface tension, and contact angle was collected, compiled, and evaluated.
Source record↗
A feasibility study of developing toroidal tanks for a spinning spacecraft. Part 2: Evaluation of fluid behavior in spinning toroidal tanks
An experimental program was conducted for the purpose of evaluating propellant behavior characteristics in spinning toroidal tanks. The effects of typical mission requirements, and related phenomena upon propellant slosh and settling, and orientation and stability of the ullage were investigated in a subscale model tank under both one-g and low-g acceleration environments. Specific conditions included were axial acceleration, spin rate, spinrate change, and spacecraft wobble, both singly and in combination. Methanol and water in combination with appropriate spin-rates and accelerations of the scale model system were used to simulate the behavior of fluorine, nitrogen tetroxide, monomethylhydrazine, and hydrazine. The experimental results indicate that no major fluid behavior problems would be encountered with the use of toroidal tanks containing any of the four propellants in a proposed spin-stabilized orbiter spacecraft.
Anderson, J. E.↗