Browse Topic: Hydrazines

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Anodic Treatment - Titanium and Titanium Alloys Solution pH 13 or HigherAMS2488D (Historical)02/25/2018
This specification establishes the engineering requirements for producing an anodic coating on titanium and titanium alloys and the properties of the coating.
AMS B Finishes Processes and Fluids Committee
Material Specification
Nanosensor/Cellphone Hybrid for Detecting Chemicals and ConcentrationsTBMG-2067010/01/2014
Nanosensors have been developed for chemical detection using carbon nanotubes (CNTs). Unlike other chemical sensors, this solid-state approach requires no reagents and can be refreshed with a solid-state ultraviolet (UV) diode. The sensors possess high sensitivity (ppbv), fast response (≈2 s), high selectivity, low power (μW), and very small size (1 cm2 or less based on advanced miniaturization), and they are ideally suited for integration with wireless networks or cellphone type devices.
Magazine Article
Hydrazine Absorbent/Detoxification PadTBMG-2031308/01/2014
A new chemistry was developed for existing hydrazine absorbent/detoxification pads. Enhancements include faster reaction rates, weight reduction, a color change that indicates spill occurrence, and another color change that indicates successful hydrazine degradation. The previous spill control pad, using copper oxide on the silica gel substrate as the reactant, affected only 50 percent degradation of hydrazine after 9 hours. The new prototypes have been found to degrade hydrazine from 95 to 99.9 percent in only 5 minutes, and to below detection limits within 90 minutes.
Magazine Article
Thrusters Support Communications Satellite LaunchTBMG-1935804/01/2014
Monopropellant (hydrazine) thrusters Aerojet Rocketdyne Sacramento, CA 916-355-4000
Magazine Article
Ionic Liquids to Replace HydrazineTBMG-944403/01/2011
A method for developing safe, easy-to-handle propellants has been developed based upon ionic liquids (ILs) or their eutectic mixtures. An IL is a binary combination of a typically organic cation and anion, which generally produces an ionic salt with a melting point below 100 °C. Many ILs have melting points near, or even below, room temperature (room temperature ionic liquids, RTILs). More importantly, a number of ILs have a positive enthalpy of formation. This means the thermal energy released during decomposition reactions makes energetic ILs ideal for use as propellants. Unlike traditional, storable propellants like hydrazine, ILs also exhibit near-zero vapor pressure. This makes them safer to handle because it eliminates hazardous inhalation — the primary pathway — as a route for toxicity in humans. Thus, ILs are ideal candidates for replacing hydrazine, which is expensive and dangerous, and poses significant handling difficulties.
Magazine Article
Fuel-Cell Power Source Based on Onboard Rocket PropellantsTBMG-817107/01/2010
The use of onboard rocket propellants (dense liquids at room temperature) in place of conventional cryogenic fuel-cell reactants (hydrogen and oxygen) eliminates the mass penalties associated with cryocooling and boil-off. The high energy content and density of the rocket propellants will also require no additional chemical processing.
Magazine Article
More About N2O-Based Propulsion and Breathable-Gas SystemsTBMG-816207/01/2010
A concept was evaluated of using nitrous oxide as (1) a monopropellant in thrusters for space suits and spacecraft and (2) a source of breathable gas inside space suits and spacecraft, both by exploiting the controlled decomposition of N2O into N2 and O2. Relative to one prior monopropellant hydrazine, N2O is much less toxic, yet offers comparable performance. N2O can be stored safely as a liquid at room temperature and unlike another prior monopropellant hydrogen peroxide does not decompose spontaneously. A prototype N2O-based thruster has been demonstrated. It has also been proposed to harness N2O-based thrusters for generating electric power and to use the N2 + O2 decomposition product as a breathable gas. Because of the high performance, safety, and ease of handling of N2O, it can be expected to be economically attractive to equip future spacecraft and space suits with N2O-based thrusters and breathable-gas systems.
Magazine Article
Fuel-Cell Power Source Based on Onboard Rocket PropellantsTBMG-TB-00817107/01/2010
This high-energy density power source is an alternative to radioisotopes or primary batteries. The use of onboard rocket propellants (dense liquids at room temperature) in place of conventional cryogenic fuel-cell reactants (hydrogen and oxygen) eliminates the mass penalties associated with cryocooling and boil-off. The high energy content and density of the rocket propellants will also require no additional chemical processing.
Magazine Article
Three Methods of Detection of HydrazinesTBMG-793005/01/2010
Three proposed methods for measuring trace quantities of hydrazines involve ionization and detection of hydrazine derivatives. These methods are intended to overcome the limitations of prior hydrazine-detection methods.
Magazine Article
euces Software Development2008-01-207206/29/2008
The euces project was initiated to be prepared for the future role of EADS as stage system prime for stage and launcher developments. Launcher stages for NGLV need to meet ambitious mission and operational demands. The paper will present a brief overview of the currently existing COMPONENT libraries and its possibilities as well as an application example which will be a simplified functional model of the ARIANE 5 EPS upper stage w.r.t. physical model formulation of its incorporated components, its schematic, data initialisation and simulation results obtained. The simulation results will be compared to flight data of a dedicated flight.
Isselhorst, Armin, Rackemann, Nico
Technical Paper
Oxide Protective Coats for Ir/Re Rocket Combustion ChambersTBMG-TB-00122102/11/2007
An improved material system has been developed for rocket engine combustion chambers for burning oxygen/hydrogen mixtures or novel monopropellants, which are highly oxidizing at operating temperatures. The baseline for developing the improved material system is a prior iridium/rhenium system for chambers burning nitrogen tetroxide/monomethyl hydrazine mixtures, which are less oxidizing. The baseline combustion chamber comprises an outer layer of rhenium that provides structural support, plus an inner layer of iridium that acts as a barrier to oxidation of the rhenium. In the improved material system, the layer of iridium is thin and is coated with a thermal fatigue-resistant refractory oxide (specifically, hafnium oxide) that serves partly as a thermal barrier to decrease the temperature and thus the rate of oxidation of the rhenium. The oxide layer also acts as a barrier against the transport of oxidizing species to the surface of the iridium. Tests in which various oxygen/hydrogen
Magazine Article
Precious-Metal Salt Coatings for Detecting HydrazinesTBMG-34412/01/2004
Substrates coated with a precious metal salt KAuCl4 have been found to be useful for detecting hydrazine vapors in air at and above a concentration of the order of 0.01 parts per million (ppm). Upon exposure to air containing a sufficient amount of hydrazine for a sufficient time, the coating material undergoes a visible change in color. Although the color change is only a qualitative indication, it can serve as an alarm of a hazardous concentration of hydrazine or as advice of the need for a quantitative measurement of concentration. Detection of hydrazine vapors by this technique costs much less and takes less time than does laboratory analysis of sorbent tubes using high-performance liquid chromatography, which is the technique used heretofore to detect hydrazines at concentrations down to 0.01 ppm.
Magazine Article
Development of Alternatives to Hydrazines as PropellantsTBMG-753612/01/2001
A brief report summarizes an investigation of less-toxic alternatives to toxic monopropellant fluids used in launch vehicles, upper stages, and spacecraft propulsion. The toxic fluids in question are (1) hydrazine and its derivatives, used, variously, as fuels or by themselves as catalytically decomposable monopropellants; and (2) nitrogen dioxide, used as an oxidizer for such fuels.
Magazine Article
Gas Generator for Inflating Structures in Outer SpaceTBMG-740908/01/2001
A report proposes a system that would supply gas for inflating one or more inflatable structure(s) in outer space. The system would include a small tank of helium for initial inflation, plus a catalytic hydrazine gas generator that would supply makeup gas over the long term. After initial inflation, when makeup gas was needed, liquid hydrazine from a tank would be made to pass through a catalytic bed, where it would become decomposed into a mixture of N2, H2, and a small amount of NH3. This gaseous mixture would constitute the makeup gas and would be stored in the tank that previously contained the helium. The makeup gas would be released from the tank to the structure(s) as needed. In comparison with an inflation system based only on compressed gas stored in tanks, the proposed inflation system would offer the advantage of lower mass: About 25 percent of the masses of representative previously contemplated large inflatable outer-space structures would have been contained in their
Magazine Article
Thruster Based on Sublimation of Solid HydrazineTBMG-709602/01/2001
A report proposes a small spacecraft attitude-control thruster in which the propellant material would be hydrazine that would be stored frozen until sublimed at the instant of use. From the upstream to the downstream end, the main components of the thruster would include a plug of solid hydrazine in a container, a rapid source of radiant heat (e.g., a laser diode or a flash lamp), and a heated-catalyst-and-nozzle assembly like that of a conventional hydrazine thruster. In operation, each pulse of radiant heat would cause a small amount of frozen hydrazine to sublime. The puff of hydrazine vapor thus generated would become chemically decomposed in the heated catalyst, and an impulse would be generated by the expansion of the puff of decomposition products in the nozzle. This thruster would be attractive for generating small impulses (impulse "bits") on command for precise maneuvering of a spacecraft that either remains below the freezing temperature of hydrazine (≈274 K) or that
Magazine Article
Liquid/Vapor-Hydrazine Thruster Would Produce Small ImpulsesTBMG-709502/01/2001
A report proposes a liquid/vapor-hydrazine thruster for use in controlling the attitude of a small spacecraft. From the upstream to the downstream end, the thruster would include a tank containing liquid hydrazine, a fast liquid valve, a heated prevaporizing plenum, a fast gas valve, and a heated catalytic bed. In one mode of operation (the conventional mode), heat would not be supplied to the prevaporizing plenum; instead, liquid hydrazine would be fed directly to the heated catalytic bed. In another mode of operation, heat would be supplied to the prevaporizing plenum, and the gas valve would be opened in brief pulses to pass the hydrazine vapor to the heated catalytic bed to produce small pulses of thrust. The use of vapor (as compared with liquid) feed in the pulse mode would make it possible to generate smaller impulses, which are better suited for highly precise spacecraft maneuvers.
Magazine Article
Modifications of a Hydrazine Fueling Procedure and EquipmentTBMG-696710/01/2000
A combination of procedure and equipment for loading liquid hydrazine into a spacecraft fuel tank that contains a diaphragm or bladder would be modified, according to a proposal. The purpose of the modifications is to enable fueling technicians to work safely, during all but a small part of the loading process, in less-restrictive protective attire.
Magazine Article
Detecting Hydrazine via Optical Detection of AmmoniaTBMG-2967009/01/2000
In a proposed method for rapidly detecting hydrazine in air at concentrations at or above 10 parts per billion by volume (ppbv), tunable diode lasers (TDLs) and photodetectors would be used to measure infrared absorption spectra of both ammonia and hydrazine simultaneously. In this method, one would take advantage of the fact that (1) ammonia is formed in the decomposition of hydrazine and is always present when hydrazine is present and (2) the spectral features attributable to ammonia are much stronger than those attributable to hydrazine, and thus ammonia can be detected more easily. In a typical situation in which hydrazine is suspected of leaking and in which one could rule out an alternative source of ammonia (e.g., an open bottle of household ammonia solution or window cleaner), an ammonia spectrum could thus be taken as an indication of hydrazine.
Magazine Article
Ion-Mobility Spectrometric Determination of HydrazinesTBMG-3000511/01/1999
Hydrazine, monomethylhydrazine, and unsymmetrical dimethylhydrazine can be detected and measured at concentrations as low as 10 parts per billion in the presence of ammonia at concentrations as high as 10 parts per million (greater than the odor threshold concentration of ammonia, approximately 5 ppm) by modified use of a portable, commercially available ion-mobility spectrometer. The modification consists in the substitution of 5-nonanone for acetone as the ion-forming compound in the drift or source region of the ion-mobility spectrometer. Previously, when acetone was used and ammonia was present in the sampled atmosphere even at ppm levels, chemical reactions between the ammonia and the acetone formed ion adducts that had mobilities comparable to those of monomethylhydrazine and that, consequently, interfered with the detection of hydrazines.
Magazine Article
Kit for Sampling Nitrosamines From Aqueous SolutionsTBMG-2992406/01/1999
Scientists at White Sands Test Facility (WSTF) have devised a kit for extracting nitrosamines from aqueous solutions. In comparison with extractions according to the method recommended by the Environmental Protection Agency (EPA), extractions by use of the kit are faster, cheaper and less labor-intensive, and they yield greater recoveries as well as test results that are more accurate. No other nitrosamine test kit performs at the level of this kit while satisfying requirements unique to WSTF.
Magazine Article
Micromachined Monopropellant ThrustersTBMG-3227505/01/1998
A report proposes monopropellant microthrusters for a new generation of miniature spacecraft with mission lifetimes stretching into years. These thrusters would include micromachined nozzle/chamber assemblies containing microvalves, designed according to emerging concepts of microelectromechanical systems (MEMS). Like some previously designed monopropellant thrusters, these thrusters would generate expanding gases and thereby generate thrust through catalytic dissociation of liquid hydrazine; however, these thrusters would be considerably smaller. Moreover, instead of putting catalytic pellets in chambers according to the previous designs, one would roughen the inner walls of the chambers and coat them with iridium or some other suitable catalyst. The micromachined thruster assemblies would be enclosed within aerogel bodies for thermal insulation. Each thruster would be heated with a small amount of power (< 1 W) to promote vaporization. Flow geometries and the characteristic times of
Magazine Article
Electrochemical Monitoring of Hydrazine in AirTBMG-3200804/01/1998
An instrumentation system monitors ambient air to determine whether hydrazine vapor is present in sufficient concentration to be harmful to humans or equipment. The system can measure hydrazine concentrations as low as 10 parts per billion (ppb); this level of concentration is denoted the threshold limit value (TLV) in a revised safety standard proposed by the American Conference of Governmental Industrial Hygienists.
Magazine Article
Sonochemical Treatment To Remove Hydrazines From WaterTBMG-3201904/01/1998
A sonochemical treatment has been proposed for removing hydrazine contaminants from water. The basis of the proposal is a conjecture that the sonochemical effect in water containing hydrazines would cause the hydrazines and some of the water to decompose, forming relatively innocuous products like nitrogen, ammonia, and derivatives of ammonia. On a large scale, this treatment could be incorporated into processes for remediation of industrial wastewater streams. On a smaller scale, this treatment could be effected by portable equipment that could be brought to locations where water contaminated by hydrazines has been spilled; examples of such locations include industrial chemical processing sites and spacecraft-launching sites, where hydrazines are used as hypergolic fuels.
Magazine Article
ANODIC TREATMENT, TITANIUM AND TITANIUM ALLOYSAMS2488C (Historical)12/01/1994
This specification establishes the engineering requirements for producing an electrolytic conversion (anodic) coating on titanium and titanium alloys and the properties of the coating.
AMS B Finishes Processes and Fluids Committee
Material Specification
ANODIC TREATMENT OF TITANIUM AND TITANIUM ALLOYSAMS2488B (Historical)10/01/1989
This specification establishes the engineering requirements for producing an electrolytic conversion (anodic) coating on titanium and titanium alloys and the properties of the coating.
AMS B Finishes Processes and Fluids Committee
Material Specification
Lox/Hydrocarbon Propellants for Space Propulsion Systems84152910/01/1984
The significant results of technology efforts directed by the NASA Lyndon B. Johnson Space Center investigating liquid oxygen/hydrocarbon (lox/HC) propellant combination are presented. These efforts are intended to identify viable propellant combinations and system designs to replace nitrogen tetroxide and monomethylhydrazine for future spacecraft orbital maneuvering and attitude control systems, and to date have been focused primarily on the various technology areas of lox/HC combustion - injector element design effects, performance, combustion chamber heat transfer, coking, and ignition. In addition, a study was performed to compare candidate lox/HC propulsion system concepts and to evaluate major system/component design options. The data generated provide quantitative substantiation of trends previously experienced with hypergolic propellants and with a lox and rocket propellant combination. More importantly, however, the data provide a sound footing for the technology data base
Boyd, William C.
Technical Paper
Long-Term Storage of Liquid Rocket Propellant Tankage and Components70080002/01/1970
Air Force weapons systems require long-term maintenance-free storage, preferably under uncontrolled environmental conditions. Liquid propulsion system components must be capable of satisfactory operation after years of exposure to highly reactive propellants while retaining the propellant without leakage under severe ambient conditions of temperature and relative humidity. Oxidizer leakage caused by improper component design and severe ambient storage conditions has presented serious operational problems. The Air Force Rocket Propulsion Laboratory (AFRPL) has initiated a program to investigate the storability of liquid system components and tankage under extreme conditions of relative humidity and temperature. A variety of system components and tankage materials are being evaluated for long-term storability with storable liquid rocket fuels and oxidizers. Storage conditions are 85 F temperature and 85% RH for oxidizer systems and +65 to +165 F temperature for fuel systems. The
Branigan, John E.
Technical Paper
Hydrazine-Hydrogen Peroxide Fuel Cell System for Deep Submergence Vehicles69073002/01/1969
Present deep submersible powerplants are limited in terms of on-board energy storage capacity. Of the planned advanced deep submersibles, the Deep Submergence Search Vehicle (DSSV) is an immediate and typical advanced power system application. This paper discusses DSSV power requirements and briefly outlines and compares the competing power system candidates. The pressure balanced, hydrazine-hydrogen peroxide fuel cell is identified as a leading competitor. A typical system approach is described, system design options identified, and system advantages cited.
Rich, G. E.
Technical Paper
AIR FORCE BOOSTER GROWTH CONCEPTS69071302/01/1969
The current family of Air Force space launch vehicles which has grown primarily from our series of ballistic missile programs is described. Continuing evolutionary booster developments and improvements, in combination with space configured upper stages and strap-on solid motors, have provided the Air Force with this versatile family of small, medium and large launch vehicles. Growth versions of these vehicles, attained through stage and component improvements, new combinations of stages, and application of advanced technology programs, are presented. These growth versions provide the Air Force with a number of options for increased launch vehicle capabilities in the 1970's.
Saavedra, J.A.
Technical Paper
Low-Cost Boosters67038002/01/1967
This paper summarizes recent work performed by The Boeing Company to evaluate various low-cost methods of providing rocket-launch vehicles of payload capability between the uprated Saturn I (40,000 lb. to low earth orbit) and Saturn V (262,000 lb. to low earth orbit). A NASA space program has been postulated indicating that from 33 to 69 vehicles may be required during the 1970's in the payload range described. In increasing development complexity, the vehicles evaluated include 1) existing developed equipment like the S-IC and S-IVB stages of Saturn V, 2) a new 260-inch diameter solid booster vehicle and 3) new pressure fed storable propellant booster vehicles. Comparisons are made evaluating the effort and cost required to implement the various systems and their individual operational costs. The low cost system selection changes with mission requirements and is further contingent on a booster stage recovery and reuse decision.
Martin, John E., Mayhall, John A., Hardy, Richard
Technical Paper
Propellant Gaging Utilizing Radio Frequency Techniques64048601/01/1964
This paper describes theoretical analyses performed on cylindrical and spherical propellant tanks to establish the basis for selection of the proper mode (electric and magnetic field configurations) of operation of the cavity. Extensive experimental investigations were then conducted. Scale models were constructed and loaded under conditions simulating zero gravity and applied accelerations with typical fuels such as hydrazine and unsymmetrical dimethyl hydrazine. The results of these measurements have verified the theoretical predications and have established the basic feasibility of this radio frequency technique.
Burns, G. A., Meierbachtol, C. J.
Technical Paper
Some Considerations Affecting the Selection of a Liquid or Solid Propellant Propulsion System61012001/01/1961
Etheridge, F. G.
Technical Paper
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