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 PT S
 AU Qian, T
    Xu, R
    Kwan, C
    Linnell, B
    Young, R
 TI Toxic vapor classification and concentration estimation for Space
    Shuttle and International Space Station
 SO ADVANCES IN NEURAL NETWORKS - ISNN 2004, PT 1
 SE LECTURE NOTES IN COMPUTER SCIENCE
 LA English
 DT Article
 ID SUPPORT VECTOR MACHINES
 AB During space walks, the space suits of astronauts may be contaminated
    by toxic vapors such as hydrazine, which are used for attitude control.
    Here we present some initial results on vapor classification and
    concentration estimation by using Support Vector Machine. (SVM). The
    vapor was collected by electronic nose. By collaborating closely with
    NASA KCS, we achieved great results. For example, for Kam15f
    (90-second) data set, the classification success rate was 97.5% using
    SVM as compared to 87% using the linear discriminant method in [1].
    Comparative studies were conducted between the SVM classifier and other
    classifiers such as Back Propagation (BP) Neural Network, Probability
    Neural Network (PNN), and, Learning Vector Quantization (LVQ). In all
    cases, the SVM classifier showed superior performance over other
    classifiers. In the concentration estimation part by using SVM, we
    achieved more than 99% correct estimation of concentration by using the
    90(th) second data samples.
 C1 Intelligent Automat Inc, Rockville, MD 20855 USA.
    NASA, Kennedy Space Ctr, FL 32899 USA.
 RP Qian, T, Intelligent Automat Inc, 15400 Calhoun Dr,Suite 400,
    Rockville, MD 20855 USA.
 EM tqian@i-a-i.com
    hgxu@i-a-i.com
    ckwan@i-a-i.com
    Bruce.Linnell-1@ksc.nasa.gov
    Rebecca.C.Young@nasa.gov
 NR 6
 TC 0
 PU SPRINGER-VERLAG BERLIN
 PI BERLIN
 PA HEIDELBERGER PLATZ 3, D-14197 BERLIN, GERMANY
 SN 0302-9743
 J9 LECT NOTE COMPUT SCI
 PY 2004
 VL 3173
 BP 543
 EP 551
 PG 9
 SC Computer Science, Theory & Methods
 GA BAT64
 UT ISI:000223492600090
 ER
 
 
 PT J
 AU Zelnick, SD
    Mattie, DR
    Stepaniak, PC
 TI Occupational exposure to hydrazines: Treatment of acute central nervous
    system toxicity
 SO AVIATION SPACE AND ENVIRONMENTAL MEDICINE
 LA English
 DT Review
 DE aviation; hydrazine; treatment
 ID UREA CYCLE DISORDERS; ISONIAZID OVERDOSE; UDMH INTOXICATION;
    PYRIDOXINE; MANAGEMENT; THERAPY; INHIBITION; ENZYMES; INVIVO; RAT
 AB ZELNICK SD, MATTIE DR, STEPANIAK PC. Occupational exposure to
    hydrazines: treatment of acute central nervous system toxicity. Aviat
    Space Environ Med 2003; 74:1285-91.
    Exposure to hydrazine and hydrazines' alkylated derivatives is an
    important occupational health issue, which will increase in
    significance as space applications increase. Despite their widespread
    usage as rocket fuels in manned and unmanned space and missile systems,
    serious exposures to hydrazines are rare. While a significant number of
    experimental studies were performed in the late 1950s through the
    mid-1960s, conflicting information exists concerning the most
    appropriate treatment for these exposures. A cross-sectional study
    evaluating the most common rocket fuels such as hydrazine;
    1,1-dimethylhydrazine (UDMH); mono-methylhydrazine (MMH); and
    Aerozine-50 against the most commonly suggested therapies, such as
    pyridoxine, traditional antiseizure therapies, and arginine is needed
    to clarify the treatment implications for human exposure. Treatments
    that have been useful for hyperammonemic states, such as those for the
    six inherited urea cycle defects, have significant potential for the
    improvement of hydrazine exposure treatment.
 C1 US Dept Def, Manned Space Flight Off, Div Med, Patrick AFB, FL USA.
    USAF, Res Lab, Wright Patterson AFB, OH 45433 USA.
    NASA, Contingency Med Operat Grp, Space Med & Crew Hlth Syst, Houston, TX USA.
 RP Zelnick, SD, US Dept Def, Manned Space Flight Off, Div Med, 1201 Edward
    H White II St,MS 7101,Bldg 423,Room S, Patrick AFB, FL USA.
 NR 47
 TC 3
 PU AEROSPACE MEDICAL ASSOC
 PI ALEXANDRIA
 PA 320 S HENRY ST, ALEXANDRIA, VA 22314-3579 USA
 SN 0095-6562
 J9 AVIAT SPACE ENVIRON MED
 JI Aviat. Space Environ. Med.
 PD DEC
 PY 2003
 VL 74
 IS 12
 BP 1285
 EP 1291
 PG 7
 SC Public, Environmental & Occupational Health; Medicine, General &
    Internal; Sport Sciences
 GA 751XH
 UT ISI:000187115000012
 ER
 
 
 PT J
 AU Barragan, M
    Woods, S
    Julien, HL
    Wilson, DB
    Saulsberry, R
 TI Thermodynamic equations of state for hydrazine and monomethylhydrazine
 SO COMBUSTION AND FLAME
 LA English
 DT Article
 AB Thermodynamic equations of state are evaluated for the aerospace fuels
    hydrazine and monomethylhydrazine using Peng-Robinson (PR) and
    Soave-Redlich-Kwong (SRK) formulations. The PR formulation is shown to
    be the best fit for hydrazine, and the SRK formulation to be the best
    fit for monomethylhydrazine, based on available critical property data
    and evaluations of thermodynamic consistency. The adequacy of the
    differing property data for these fuels in the literature is discussed,
    and the methodology used to validate the formulations is outlined. The
    importance of using appropriate real fluid equations of state in
    thermodynamic safety and hazards analysis of fuel systems is
    demonstrated by considering an adiabatic compression of gaseous fuels
    previously postulated in accident scenarios of aerospace propulsion
    systems. Calculation of isentropic compression temperatures for pure
    components using ideal gas constant heat capacity, ideal gas with
    variable heat capacity, and real fluid equations of state are compared
    to illustrate the need for real fluid equations of state. In addition,
    three separate approaches are used for estimating isentropic
    compression temperatures for mixtures involving these fuels, again
    illustrating the importance of treating these mixtures as real fluids
    for design and safety analysis. (C) 2002 by The Combustion Institute.
 C1 NASA, Honeywell Technol Solut Inc, White Sands Test Facil, Las Cruces, NM USA.
    NASA, Lyndon B Johnson Space Ctr, White Sands Test Facil, Las Cruces, NM USA.
 RP Julien, HL, NASA, Honeywell Technol Solut Inc, White Sands Test Facil,
    Las Cruces, NM USA.
 NR 20
 TC 1
 PU ELSEVIER SCIENCE INC
 PI NEW YORK
 PA 360 PARK AVE SOUTH, NEW YORK, NY 10010-1710 USA
 SN 0010-2180
 J9 COMBUST FLAME
 JI Combust. Flame
 PD NOV
 PY 2002
 VL 131
 IS 3
 BP 316
 EP 328
 PG 13
 SC Thermodynamics; Energy & Fuels; Engineering, Multidisciplinary;
    Engineering, Chemical
 GA 618MD
 UT ISI:000179421100008
 ER
 
 
 PT J
 AU Doerr, DF
 TI Development of an advanced rocket propellant Handler's suit
 SO ACTA ASTRONAUTICA
 LA English
 DT Article
 AB Most launch vehicles and satellites in the US inventory rely upon the
    use of hypergolic rocket propollants, many of which are toxic to
    humans. These fuels and oxidizers, such as hydrazine and nitrogen
    tetroxide have threshold limit values as low as 0.01 PPM. It is
    essential to provide space workers handling these agents whole body
    protection as they are universally hazardous not only to the
    respiratory system, but the skin as well. This paper describes a new
    method for powering a whole body protective garment to assure the
    safety of ground servicing crews.
    A new technology has been developed through the small business
    innovative research program at the Kennedy Space Center. Currently,
    liquid air is used in the environmental control unit (ECU) that powers
    the propellant handlers suit (PHE). However, liquid air exhibits
    problems with attitude dependence, oxygen enrichment, and difficulty
    with reliable quantity measurement. The new technology employs the
    storage of the supply air as a supercritical gas. This method of air
    storage overcomes ail of three problems above while maintaining high
    density storage at relatively low vessel pressures (< 7000 kPa or
    similar to 1000 psi). A one hour prototype ECU was developed and tested
    to prove the feasibility of this concept. This was upgraded by the
    design of a larger supercritical dewar capable of holding 7 Kg of air,
    a supply which provides a 2 hour duration to the PHE. A third version
    is being developed to test the feasibility of replacing existing air
    cooling methodology with a liquid cooled garment for relief of heat
    stress in this warm Florida environment.
    Testing of the first one hour prototype yielded data comprobable to the
    liquid air powered predecessor, but enjoyed advantages of attitude
    independence and oxygen level stability. Thermal data revealed heat
    stress relief at least as good as liquid air supplied units.
    The application of supercritical air technology to this whole body
    protective ensemble marked an advancement in the state-of-the-art in
    personal protective equipment. Not only was long duration environmental
    control provided, but it was done without a high pressure vessel. The
    unit met human performance needs for attitude independence, oxygen
    stability, and relief of heat stress. This supercritical air (and
    oxygen) technology is suggested for microgravity applications in life
    support such as the Extravehicular Mobility Unit. (C) 2001 Published by
    Elsevier Science Ltd.
 C1 NASA, Kennedy Space Ctr, FL 32899 USA.
 RP Doerr, DF, NASA, Kennedy Space Ctr, FL 32899 USA.
 NR 0
 TC 1
 PU PERGAMON-ELSEVIER SCIENCE LTD
 PI OXFORD
 PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD OX5 1GB, ENGLAND
 SN 0094-5765
 J9 ACTA ASTRONAUT
 JI Acta Astronaut.
 PD AUG-NOV
 PY 2001
 VL 49
 IS 3-10
 BP 463
 EP 468
 PG 6
 SC Engineering, Aerospace
 GA 468HK
 UT ISI:000170751900035
 ER
 
 
 PT J
 AU Cardelino, BH
    Moore, CE
    Cardelino, CA
    Frazier, DO
    Bachmann, KJ
 TI Theoretical study of indium compounds of interest for organometallic
    chemical vapor deposition
 SO JOURNAL OF PHYSICAL CHEMISTRY A
 LA English
 DT Article
 ID MOLECULAR-ORBITAL THEORY; EXTENDED BASIS-SETS; POTENTIAL-ENERGY
    SURFACES; DENSITY-FUNCTIONAL THEORY; IR MATRIX-ISOLATION; SPECTROSCOPIC
    CONSTANTS; ELECTRONIC STATES; PSEUDOPOTENTIAL APPROXIMATION;
    DISSOCIATION-ENERGIES; TRANSITION-METALS
 AB The structural, electronic, and thermochemical properties of indium
    compounds which are of interest in halide transport and organometallic
    chemical vapor deposition processes have been studied by ab initio and
    statistical thermodynamic methods. The compounds reported include:
    indium halides and hydrides (InF, InCl, InCl3, InH, InH2, InH3); indium
    clusters (In-2, In-3); methylindium, dimethylindium, and their hydrogen
    derivatives [In(CH3), In(CH3)H, In(CH3)H-2, In(CH3)(2), In(CH3)(2)H];
    dimethylindium dimer [In-2(CH3)(4)] and trimethylindium [In(CH3)(3)];
    dehydrogenated methyl-, dimethyl-, and trimethylindium [In(CH3)(2)CH2,
    In(CH3)CH2. In(CH2)]; trimethylindium adducts with ammonia,
    trimethylamine and hydrazine [(CH3)(3)In:NH3, (CH3)(3)In:N(CH3)(3),
    (CH3)(3)In:N(H-2)N(H-2)]; dimethylamino-indium and methylimino-indium
    [In(CH3)(2)(NH2). In(CH3)(NH)]; indium nitride and indium nitride dimer
    (InN, In2N2); indium phosphide, -arsenide, and -antimonide (InP, InAs,
    InSb). The predicted electronic properties are based on density
    functional theory calculations; the calculated thermodynamic properties
    are reported following the format of the JANAF (Joint Army, Navy, NASA,
    Air Force) Tables. Equilibrium compositions at two temperatures (298
    and 1000K) have been analyzed for groups of competing simultaneous
    reactions.
 C1 Spelman Coll, Dept Chem, Atlanta, GA 30314 USA.
    NASA, George C Marshall Space Flight Ctr, Space Sci Lab, Huntsville, AL 35812 USA.
    Georgia Inst Technol, Sch Earth & Atmospher Sci, Atlanta, GA 30332 USA.
    N Carolina State Univ, Dept Mat Sci & Engn, Raleigh, NC 27695 USA.
 RP Cardelino, BH, Spelman Coll, Dept Chem, Box 238, Atlanta, GA 30314 USA.
 NR 88
 TC 7
 PU AMER CHEMICAL SOC
 PI WASHINGTON
 PA 1155 16TH ST, NW, WASHINGTON, DC 20036 USA
 SN 1089-5639
 J9 J PHYS CHEM A
 JI J. Phys. Chem. A
 PD FEB 8
 PY 2001
 VL 105
 IS 5
 BP 849
 EP 868
 PG 20
 SC Chemistry, Physical; Physics, Atomic, Molecular & Chemical
 GA 400AF
 UT ISI:000166845900008
 ER
 
 
 PT S
 AU Johnson, NL
 TI The cause and consequences of a satellite fragmentation: A case study
 SO SPACE DEBRIS
 SE ADVANCES IN SPACE RESEARCH
 LA English
 DT Article
 AB The fragmentation of a Pegasus Hydrazine Auxiliary Propulsion System
    upper stage on 3 June 1996 stands as the worst satellite breakup on
    record in terms of cataloged orbital debris. In addition to the more
    than 700 debris large enough to be tracked (approximately 10 cm in
    diameter or greater) in the 200 km by 2,000 km orbital regime by the
    U.S. Space Surveillance Network, a debris population of up to 300,000
    objects larger than 4 mm appears to have been generated, based upon
    special radar observations. The debris cloud presented an immediate
    threat to many resident space objects, such as the Hubble Space
    Telescope, which resided in an orbit just 25 kin below the breakup
    altitude. Special analyses were required to ensure the safety of the
    STS-82 Hubble Space Telescope servicing mission in February 1997. This
    paper describes the activities undertaken-at the National Aeronautics
    and Space Administration Lyndon B. Johnson Space Center to characterize
    the near-term and far-term hazard of the debris cloud to manned and
    robotic spacecraft and to investigate the probable cause of the
    accident. The role of composite materials in the vehicle may have led
    to the creation of a much larger number of debris than would have been
    expected from a more conventional upper stage. To avoid a repetition of
    the incident, the Hydrazine Auxiliary Propulsion System upper stage was
    modified before its next launch, and additional passivation measures
    were adopted. This fragmentation event represents a textbook case for
    the hazards posed by satellite breakups and how fragmentation potential
    can be reduced without significantly affecting the capability of the
    vehicle. Published by Elsevier Science Ltd on behalf of COSPAR.
 C1 NASA, Lyndon B Johnson Space Ctr, Orbital Debris Program Off, Houston, TX 77058 USA.
 RP Johnson, NL, NASA, Lyndon B Johnson Space Ctr, Orbital Debris Program
    Off, 2101 NASA Rd 1, Houston, TX 77058 USA.
 NR 0
 TC 3
 PU PERGAMON PRESS LTD
 PI OXFORD
 PA THE BOULEVARD LANGFORD LANE KIDLINGTON, OXFORD OX5 1GB, ENGLAND
 SN 0273-1177
 J9 ADV SPACE RES
 PY 1999
 VL 23
 IS 1
 BP 165
 EP 173
 PG 9
 SC Engineering, Aerospace; Astronomy & Astrophysics; Geosciences,
    Multidisciplinary; Meteorology & Atmospheric Sciences
 GA BM98C
 UT ISI:000080334700020
 ER
 
 
 PT J
 AU Lichon, PG
    Sankovic, JM
 TI Development and demonstration of a 600-second mission-average I-sp
    arcjet
 SO JOURNAL OF PROPULSION AND POWER
 LA English
 DT Article
 AB Recent advanced development has resulted in a 550-h demonstration of a
    hydrazine arcjet at a mission-average special impulse I,, of greater
    than 600 s, The laboratory-type arcjet thruster was operated at 1800 W
    through a flow rate schedule consistent with a flight application, The
    thruster demonstrated stable, high-efficiency operation for the
    duration of the test, The development effort leading to the
    demonstration addressed the operational and life issues associated with
    achieving high performance, As a result of the development activity, a
    wide range of performance Has also achieved, Performance levels of
    greater than 575 s at 1000 W and greater than 675 s at 2000 W were
    demonstrated. The problems encountered with extending low-power arcjet
    performance are discussed, Increased thruster component temperatures
    caused new life issues to be identified, along with low propellant flow
    rate stability limits, The elevated temperatures caused significant
    changes in the electrode geometry for a thruster based on the
    state-of-the-art tungsten anode designs, Three paths to solving the
    problem were attempted, including lowering the operating temperature
    through improved heat rejection, mechanical design changes to reduce
    thermal stresses, and higher strength materials selection, The success
    of this program provides substantial evidence that an arcjet capable of
    greater than 600-s mission-average specific impulse will be available
    in the near term for night qualification and application.
 C1 NASA,LEWIS RES CTR,CLEVELAND,OH 44135.
 RP Lichon, PG, OLIN AEROSP CO,REDMOND,WA 98073.
 NR 5
 TC 3
 PU AMER INST AERONAUT ASTRONAUT
 PI RESTON
 PA 1801 ALEXANDER BELL DRIVE, STE 500, RESTON, VA 22091
 SN 0748-4658
 J9 J PROPUL POWER
 JI J. Propul. Power
 PD NOV-DEC
 PY 1996
 VL 12
 IS 6
 BP 1018
 EP 1025
 PG 8
 SC Engineering, Aerospace
 GA VT426
 UT ISI:A1996VT42600004
 ER
 
 
 PT J
 AU PALASZEWSKI, B
 TI LUNAR MISSIONS USING ADVANCED CHEMICAL PROPULSION - SYSTEM-DESIGN ISSUES
 SO JOURNAL OF SPACECRAFT AND ROCKETS
 LA English
 DT Article
 AB To provide the transportation of lunar base elements to the Moon, large
    high-energy propulsion systems will be required. Advanced propulsion
    systems for lunar missions can provide significant launch mass
    reductions and payload increases. These mass reductions and added
    payload masses can be translated into significant launch cost savings
    for the lunar base missions. In this paper, the masses in low Earth
    orbit (LEO) were compared for several propulsion systems: nitrogen
    tetroxide/monomethyl hydrazine (NTO/MMH), oxygen/methane (O2/CH4),
    oxygen/hydrogen (O2/H-2), and metallized O2/H-2/Al propellants. Also,
    the payload mass increases enabled with O2/H-2 and O2/H-2/Al systems
    were addressed. In addition, many system design issues involving the
    engine thrust levels, engine commonality between the transfer vehicle
    and the excursion vehicle, and the number of launches to place the
    lunar mission vehicles into LEO will be discussed. Analyses of small
    lunar missions launched from a single STS-C night are also presented.
 RP PALASZEWSKI, B, NASA,LEWIS RES CTR,DIV SPACE PROPULS TECHNOL,LAUNCH
    VEHICLE PROPULS BRANCH,CLEVELAND,OH 44135.
 NR 22
 TC 6
 PU AMER INST AERONAUT ASTRONAUT
 PI RESTON
 PA 1801 ALEXANDER BELL DRIVE, STE 500, RESTON, VA 22091
 SN 0022-4650
 J9 J SPACECRAFT ROCKET
 JI J. Spacecr. Rockets
 PD MAY-JUN
 PY 1994
 VL 31
 IS 3
 BP 458
 EP 465
 PG 8
 SC Engineering, Aerospace
 GA NU611
 UT ISI:A1994NU61100016
 ER
 
 
 PT J
 AU SCHNEIDER, SJ
 TI LOW THRUST CHEMICAL ROCKET TECHNOLOGY
 SO SPACE TECHNOLOGY-INDUSTRIAL AND COMMERCIAL APPLICATIONS
 LA English
 DT Article
 AB An on-going technology program to improve the performance of low thrust
    chemical rockets for spacecraft on-board propulsion applications is
    reviewed. Improved performance and lifetime is sought by the
    development of new predictive tools to understand the combustion and
    flow physics, introduction of high temperature materials and improved
    component designs to optimize performance, and use of higher
    performance propellants. Improved predictive technology is sought
    through the comparison of both local and global predictions with
    experimental data. Predictions are based on both the RPLUS
    Navier-Stokes code with finite rate kinetics and the JANNAF
    methodology. Data were obtained with laser-based diagnostics along with
    global performance measurements. Results indicate that the modeling of
    the injector and the combustion process needs improvement in these
    codes and flow visualization with a technique such as two-dimensional
    laser-induced fluorescence (LIF) would aid in resolving issues of flow
    symmetry and shear layer combustion processes. High temperature
    material fabrication processes are under development and small rockets
    are being designed, fabricated, and tested using these new materials.
    Rhenium coated with iridium for oxidation protection was produced by
    the Chemical Vapor Deposition (CVD) process and enabled an 800 K
    increase in rocket operating temperature. Performance gains with this
    material in rockets using Earth storable propellants (nitrogen
    tetroxide and monomethylhydrazine or hydrazine) were obtained through
    component redesign to eliminate fuel film cooling and its associated
    combustion inefficiency while managing head end thermal soakback.
    Material interdiffusion and oxidation characteristics indicated that
    the requisite lifetimes of tens of hours were available for thruster
    applications. Rockets were designed, fabricated, and tested with
    thrusts of 22, 62, 440 and 550 N. Performance improvements of 10 to 20
    seconds specific impulse were demonstrated. Higher performance
    propellants were evaluated. These propellants, defined as space
    storable propellants, include liquid oxygen (LOX) as.the oxidizer with
    nitrogen hydrides or hydrocarbons as the fuels. Specifically, a
    LOX/hydrazine engine was designed, fabricated, and demonstrated to have
    a 95% theoretical c-star which translates into a projected vacuum
    specific impulse of 345 s at an area ratio of 204:1. Further
    performance improvement can be obtained by the use of LOX/hydrogen
    propellants, especially for manned spacecraft applications, and
    specific designs must be developed and advanced through flight
    qualification.
 RP SCHNEIDER, SJ, NASA,LEWIS RES CTR,CLEVELAND,OH 44135.
 NR 0
 TC 0
 PU PERGAMON-ELSEVIER SCIENCE LTD
 PI OXFORD
 PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD, ENGLAND OX5 1GB
 SN 0892-9270
 J9 SPACE TECHNOL
 JI Space Tech.-Ind. Comm. Appl.
 PD JAN
 PY 1994
 VL 14
 IS 1
 BP 31
 EP 44
 PG 14
 SC Engineering, Aerospace
 GA NQ809
 UT ISI:A1994NQ80900004
 ER
 
 
 PT J
 AU SOVEY, JS
    CURRAN, FM
    HAAG, TW
    PATTERSON, MJ
    PENCIL, EJ
    RAWLIN, VK
    SANKOVIC, JM
 TI DEVELOPMENT OF ARCJET AND ION PROPULSION FOR SPACECRAFT STATIONKEEPING
 SO ACTA ASTRONAUTICA
 LA English
 DT Article
 AB Near term flight applications of arcjet and ion thruster satellite
    station-keeping systems as well as development activities in Europe.
    Japan, and the United States are reviewed. At least two arcjet and
    three ion propulsion flights are scheduled during the 1992-1995 period.
    Ground demonstration technology programs are focusing on the
    development of kW-class hydrazine and ammonia arcjets and xenon ion
    thrusters. Recent work at NASA Lewis Research Center on electric
    thruster and system integration technologies relating to satellite
    stationkeeping and repositioning will also be summarized.
 RP SOVEY, JS, NASA,LEWIS RES CTR,CLEVELAND,OH 44135.
 NR 0
 TC 0
 PU PERGAMON-ELSEVIER SCIENCE LTD
 PI OXFORD
 PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD, ENGLAND OX5 1GB
 SN 0094-5765
 J9 ACTA ASTRONAUT
 JI Acta Astronaut.
 PD JUL
 PY 1993
 VL 30
 BP 151
 EP 164
 PG 14
 SC Engineering, Aerospace
 GA LQ343
 UT ISI:A1993LQ34300015
 ER
 
 
 PT J
 AU ZUBE, DM
    MYERS, RM
 TI THERMAL NONEQUILIBRIUM IN A LOW-POWER ARCJET NOZZLE
 SO JOURNAL OF PROPULSION AND POWER
 LA English
 DT Article
 AB Emission spectroscopy measurements were made of the plasma flow inside
    the nozzle of a 1-kW-class arcjet thruster. The thruster propellant was
    a hydrogen-nitrogen mixture used to simulate fully decomposed
    hydrazine. Several 0.25-mm-diam holes were drilled into the 12-mm-long
    diverging section of the tungsten thruster nozzle to provide side-on
    optical access to the internal flow. Electron excitation for atomic
    species and molecular vibrational and rotational temperatures were
    determined for the expanding plasma using relative line ratio
    techniques. The atomic excitation temperature decreased from 18,000 K
    at a location 3-mm downstream of the constrictor to 9000 K at a
    location 9 mm from the constrictor, while the molecular vibrational and
    rotational temperatures decreased from 6500 to 3000 K and 8000 to 3000
    K, respectively, between the same locations. The electron density,
    measured using H(beta) line Stark broadening, decreased from
    almost-equal-to 10(21) m-3 to 2 x 10(20) m-3 during the expansion in
    the nozzle. The results show that the plasma is in a nonequilibrium
    state throughout most of the nozzle, with relaxation times close to or
    larger than the particle residence time.
 C1 SVERDRUP TECHNOL INC,NASA,LEWIS RES CTR GRP,CLEVELAND,OH 44135.
 RP ZUBE, DM, UNIV STUTTGART,INST RAUMFAHRTSYST,W-7000 STUTTGART 80,GERMANY.
 NR 31
 TC 14
 PU AMER INST AERONAUT ASTRONAUT
 PI RESTON
 PA 1801 ALEXANDER BELL DRIVE, STE 500, RESTON, VA 22091
 SN 0748-4658
 J9 J PROPUL POWER
 JI J. Propul. Power
 PD JUL-AUG
 PY 1993
 VL 9
 IS 4
 BP 545
 EP 552
 PG 8
 SC Engineering, Aerospace
 GA LN143
 UT ISI:A1993LN14300007
 ER
 
 
 PT J
 AU EICEMAN, GA
    SALAZAR, MR
    RODRIGUEZ, MR
    LIMERO, TF
    BECK, SW
    CROSS, JH
    YOUNG, R
    JAMES, JT
 TI ION MOBILITY SPECTROMETRY OF HYDRAZINE, MONOMETHYLHYDRAZINE, AND
    AMMONIA IN AIR WITH 5-NONANONE REAGENT GAS
 SO ANALYTICAL CHEMISTRY
 LA English
 DT Article
 ID PLASMA CHROMATOGRAPHY; H2O
 AB Hydrazine (HZ) and monomethylhydrazine (MMH) in air were monitored
    continuously using a hand-held ion mobility spectrometer equipped with
    membrane inlet, Ni-63 ion source, acetone reagent gas, and ambient
    temperature drift tube. Response characteristics included detection
    limit, 6 ppb; linear range, 10-600 ppb; saturated response, >2 ppm; and
    stable response after 15-30 min. Ammonia interfered in hydrazines
    detection through a product ion with the same drift time as that for
    MMH and HZ. Acetone reagent gas was replaced with 5-nonanone to alter
    drift times of product ions and separate ammonia from MMH and HZ.
    Patterns in mobility spectra, ion identifications from mass spectra,
    and fragmentation cross-sections from collisional-induced dissociations
    suggest that drift times are governed by ion-cluster equilibria in the
    drift region of the mobility spectrometer. Practical aspects including
    calibration, stability, and reproducibility are reported from the use
    of a hand-held mobility spectrometer on the space shuttle Atlantis
    during mission STS-37.
 C1 KRUG LIFE SCI INC,HOUSTON,TX 77058.
    NASA,TOX VAPOR DETECT LAB,KENNEDY SPACE CTR,FL 32899.
    NASA,LYNDON B JOHNSON SPACE CTR,BIOMED OPERAT & RES BRANCH,HOUSTON,TX 77058.
 RP EICEMAN, GA, NEW MEXICO STATE UNIV,DEPT CHEM,LAS CRUCES,NM 88003.
 NR 22
 TC 18
 PU AMER CHEMICAL SOC
 PI WASHINGTON
 PA 1155 16TH ST, NW, WASHINGTON, DC 20036
 SN 0003-2700
 J9 ANAL CHEM
 JI Anal. Chem.
 PD JUL 1
 PY 1993
 VL 65
 IS 13
 BP 1696
 EP 1702
 PG 7
 SC Chemistry, Analytical
 GA LJ380
 UT ISI:A1993LJ38000013
 ER
 
 
 PT J
 AU PALASZEWSKI, B
 TI METALLIZED PROPELLANTS FOR THE HUMAN EXPLORATION OF MARS
 SO JOURNAL OF PROPULSION AND POWER
 LA English
 DT Article
 AB Advanced chemical propulsion using metallized propellants can enable
    significant launch mass reductions for piloted Mars missions.
    Metallized propellants allow the density and/or the specific impulse
    (I(sp)) of the propulsion system to increase. These density and I(sp)
    increases can reduce the propellant mass and the propulsion system dry
    mass. Both of these effects are discussed and analyzed in the paper.
    Detailed mass scaling equations and estimates of the I(sp) for the
    metallized propellant combinations are presented. The most significant
    savings with metallized propellants are derived from increasing the
    payload delivered to Mars. For the same mass in low Earth orbit (LEO),
    a metallized Mars vehicle can deliver 20-22% additional payload to the
    surface. Using metallized propulsion can accelerate the delivery and
    construction of a Mars base or outpost. This 20% payload increase
    reduces the total number of Mars flights and, therefore, significantly
    reduces the number of space transportation system-cargo (STS-C)
    launches for the entire Mars architecture. Using metallized propellants
    to reduce the mass in LEO per flight is not as effective as increasing
    the payload delivery capacity. While over 20% more payload can be
    delivered to Mars per mission, the mass savings per flight (while
    delivering the same payload with a higher I(sp) system) is much
    smaller. Using metallized propellants in all of the Mars propulsion
    systems, a modest 3.3% LEO mass savings is possible. This translates
    into a savings of 38,000 kg over that required with O2/H2 propulsion.
    The Mars excursion vehicle (MEV) using Earth- or space-storable
    propellants for the ascent can be an alternative to storing cryogenic
    H-2 on Mars. There will be a mass penally for using these alternatives
    because of the lower I(sp) of these systems. A space-storable system
    using oxygen/monomethyl hydrazine/aluminum (O2/MMH/Al) delivered the
    lowest mass penalty over O2/H2. For the expedition case missions, the
    LEO mass penalty for using metallized O2/MMH/Al is only 3-5%.
 RP PALASZEWSKI, B, NASA,LEWIS RES CTR,DIV SPACE PROPULS TECHNOL,METALLIZED
    PROPELLANT PROGRAM,CLEVELAND,OH 44135.
 NR 22
 TC 6
 PU AMER INST AERONAUT ASTRONAUT
 PI RESTON
 PA 1801 ALEXANDER BELL DRIVE, STE 500, RESTON, VA 22091
 SN 0748-4658
 J9 J PROPUL POWER
 JI J. Propul. Power
 PD NOV-DEC
 PY 1992
 VL 8
 IS 6
 BP 1192
 EP 1199
 PG 8
 SC Engineering, Aerospace
 GA JY976
 UT ISI:A1992JY97600010
 ER
 
 
 PT J
 AU CURRAN, FM
    HAAG, TW
 TI EXTENDED LIFE AND PERFORMANCE-TEST OF A LOW-POWER ARCJET
 SO JOURNAL OF SPACECRAFT AND ROCKETS
 LA English
 DT Article
 AB An automated, cyclic life test was performed to demonstrate the
    reliability and endurance of a low-power dc arcjet thruster. Over 1000
    h and 500 on-off cycles were accumulated, which would represent the
    requirements for about 15 years of on-orbit lifetime. A
    hydrogen/nitrogen propellant mixture was used to simulate decomposed
    hydrazine propellant, and the power level was nominally 1.2 kW after
    the burn-in period. The arcjet operated in a very repeatable fashion
    from cycle to cycle. The steady-state voltage increased by
    approximately 6 V over the first 300 h, and then by only 3 V through
    the remainder of the test. Thrust measurements taken before, during,
    and after the test verified that the thruster performed in a consistent
    fashion throughout the test at a specific impulse of 450-460 s.
    Post-test component evaluation revealed limited erosion on both the
    anode and cathode. Other thruster components, including graphite seals,
    appeared undamaged.
 RP CURRAN, FM, NASA,LEWIS RES CTR,DIV SPACE PROPULS TECHNOL,MAIL STOP
    SPTO-1,CLEVELAND,OH 44135.
 NR 31
 TC 11
 PU AMER INST AERONAUT ASTRONAUT
 PI RESTON
 PA 1801 ALEXANDER BELL DRIVE, STE 500, RESTON, VA 22091
 SN 0022-4650
 J9 J SPACECRAFT ROCKET
 JI J. Spacecr. Rockets
 PD JUL-AUG
 PY 1992
 VL 29
 IS 4
 BP 444
 EP 452
 PG 9
 SC Engineering, Aerospace
 GA JK341
 UT ISI:A1992JK34100004
 ER
 
 
 PT J
 AU MEYER, D
    WEBER, K
    SCOTT, W
 TI ELECTRIC AUXILIARY POWER UNIT FOR SHUTTLE EVOLUTION
 SO JOURNAL OF PROPULSION AND POWER
 LA English
 DT Article
 AB The Space Shuttle Orbiter currently uses three hydrazine-fueled
    auxiliary power units (APUs) to provide hydraulic power for the vehicle
    aerodynamic surface controls, main engine thrust vector control,
    landing gear, steering, and brakes. Electric APUs have been proposed as
    possible replacements to the hydrazine APUs. Along with the potential
    advantages, this paper describes an electric APU configuration and
    addresses the technical issues and risks associated with the subsystem
    components. In addition, characteristics of an electric APU compared
    with the existing APU and the direction of future study with respect to
    the electric APU are suggested.
 C1 NASA,LYNDON B JOHNSON SPACE CTR,APU SUBSYST PROGRAM,HOUSTON,TX 77058.
    SUNDSTRAND AEROSP,DEPT 741F6,ROCKFORD,IL 61125.
 RP MEYER, D, SUNDSTRAND AEROSP,DEPT 710E6,4747 HARRISON AVE,ROCKFORD,IL
    61125.
 NR 3
 TC 0
 PU AMER INST AERONAUT ASTRONAUT
 PI RESTON
 PA 1801 ALEXANDER BELL DRIVE, STE 500, RESTON, VA 22091
 SN 0748-4658
 J9 J PROPUL POWER
 JI J. Propul. Power
 PD JAN-FEB
 PY 1992
 VL 8
 IS 1
 BP 233
 EP 239
 PG 7
 SC Engineering, Aerospace
 GA GZ467
 UT ISI:A1992GZ46700032
 ER
 
 
 PT J
 AU COYNE, L
    MARINER, R
    RICE, A
 TI AIR OXIDATION OF HYDRAZINE .1. REACTION-KINETICS ON NATURAL KAOLINITES,
    HALLOYSITES, AND MODEL SUBSTITUENT LAYERS WITH VARYING IRON AND
    TITANIUM-OXIDE AND O-CENTER CONTENTS
 SO LANGMUIR
 LA English
 DT Article
 ID ELECTRON-SPIN RESONANCE; DOPED SYNTHETIC KAOLINITE; PARAMAGNETIC
    RESONANCE; LUMINESCENCE; SPECTRA; SURFACE; SPECTROSCOPY; MOSSBAUER
 AB Air oxidation of hydrazine was studied by using a group of kaolinites,
    halloysites, and substituent oxides as models for the tetrahedral and
    octahedral sheets.  The rate was found to be linear with oxygen.  The
    stoichiometry showed that oxygen was the primary oxidant and that
    dinitrogen was the only important nitrogen-containing product.  The
    rates on kaolinites were strongly inhibited by water.  Those on
    three-dimensional silica and gibbsite appeared not to be. That on a
    supposedly layered silica formed from a natural kaolinite by acid
    leaching showed transitional behavior - slowed relative to that
    expected from a second-order reaction relative to that on the gibbsite
    and silica but faster than those on the kaolinites. The most striking
    result of the reaction was the marked increase in the rate of reaction
    of a constant amount of hydrazine as the amount of clay was increased.
    This increase was apparent (in spite of the water inhibition at high
    conversions) over a 2 order of magnitude variation of the clay weight.
    The weight dependence was taken to indicate that the role of the clay
    is very important, that the number of reactive centers is very small,
    or that they may be deactivated over the course of the reaction. In
    contrast to the strong dependence on overall amount of clay, the
    variation of amounts of putative oxidizing centers, such as structural
    Fe(III), admixed TiO2 or Fe2O3, or O- centers, did not result in
    alteration of the rate commensurate with the degree of variation of the
    entity in question. Surface iron does play some role, however, as
    samples that were pretreated with a reducing agent were less active as
    catalysts than the parent material. These results were taken to
    indicate either that the various centers interact to such a degree that
    they cannot be considered independently or that the reaction might
    proceed by way of surface complexation, rather than single electron
    transfers.
 C1 SAN JOSE STATE UNIV,DEPT CHEM,SAN JOSE,CA 95192.
    ENGLISH CHINA CLAYS INT,SANDERSVILLE,GA 31082.
 RP COYNE, L, NASA,AMES RES CTR,MAIL STOP 239-4,MOFFETT FIELD,CA 94035.
 NR 42
 TC 1
 PU AMER CHEMICAL SOC
 PI WASHINGTON
 PA 1155 16TH ST, NW, WASHINGTON, DC 20036
 SN 0743-7463
 J9 LANGMUIR
 JI Langmuir
 PD AUG
 PY 1991
 VL 7
 IS 8
 BP 1660
 EP 1674
 PG 15
 SC Chemistry, Physical
 GA GC040
 UT ISI:A1991GC04000019
 ER
 
 
 PT J
 AU COYNE, LM
    SUMMERS, DP
 TI SURFACE ACTIVATION OF AIR OXIDATION OF HYDRAZINE ON KAOLINITE .2.
    CONSIDERATION OF OXIDIZING REDUCING ENTITIES IN RELATIONSHIP TO OTHER
    COMPOSITIONAL, STRUCTURAL, AND ENERGETIC FACTORS
 SO LANGMUIR
 LA English
 DT Article
 ID CLAY-MINERALS; LUMINESCENCE; OXIDE; IRON; DEHYDRATION; RESONANCE;
    CATALYSTS; SPECTRA; CENTERS
 AB The rates (previously reported) for the air oxidation of hydrazine on
    kaolinite and substituent oxides of kaolinite showed a complex
    dependence on the relative amounts of several structural
    oxidizing/reducing entities within the reaction-promoting solids. The
    rates indicated an important role of the clay but no dominant role of
    any one of the oxidizing/reducing entities. In this paper we review (a)
    the reaction-promoting activity of these centers as studied in other
    systems, (b) various spectroscopic results showing interaction between
    these entities in clays and (c) reported spectroscopic studies ot the
    complexation between hydrazine and aluminosilicate surfaces as a whole,
    in an effort to propose a mechanism for the reaction.  Whereas some
    uncertainties remain, the present synthesis concludes that a mechanism
    operating through single electron/hole transfers and hydrogen atom
    transfers by discrete centers is adequate to explain the observed rate
    behaviors including the observed second order dependence of the
    oxidation rate on catalyst amount. The effects of these operations on
    the catalyst can result in no alteration of, or complete or partial
    electronic relaxation of its contingent of trapped separated charge
    pairs. The degree to which surface complexation as a whole,
    intercalation, or luminescent processes may also be associated with the
    reaction cannot be adequately assessed with the information in hand.
 C1 SAN JOSE STATE UNIV,DEPT CHEM,SAN JOSE,CA 95192.
 RP COYNE, LM, NASA,AMES RES CTR,PLANETARY BIOL BRANCH,MAIL STOP
    239-4,MOFFETT FIELD,CA 94035.
 NR 51
 TC 2
 PU AMER CHEMICAL SOC
 PI WASHINGTON
 PA 1155 16TH ST, NW, WASHINGTON, DC 20036
 SN 0743-7463
 J9 LANGMUIR
 JI Langmuir
 PD AUG
 PY 1991
 VL 7
 IS 8
 BP 1675
 EP 1688
 PG 14
 SC Chemistry, Physical
 GA GC040
 UT ISI:A1991GC04000020
 ER
 
 
 PT J
 AU DAVIS, DD
    WEDLICH, RC
    MARTIN, NB
 TI TRANSITION-METAL CATALYSIS OF THE HETEROGENEOUS DECOMPOSITION OF
    HYDRAZINE - ADIABATIC KINETICS BY ACCELERATING RATE CALORIMETRY
 SO THERMOCHIMICA ACTA
 LA English
 DT Article
 ID AMMONIA-SYNTHESIS; SURFACE; ENERGY; ADSORPTION; MECHANISM; OXYGEN;
    FILMS; CO2
 AB The thermochemical kinetics of the transition-metal-catalyzed
    decomposition reaction of hydrazine have been studied using
    accelerating rate calorimetry.  The reaction stoichiometry was
    determined by both product analysis and thermochemical balance.  In the
    range 350-515 K when both liquid and vapor hydrazine are present, the
    decomposition proceeds according to:
 C1 NASA,LOCKHEED ENGN & SCI CO,WHITE SANDS TEST FACIL,LAS CRUCES,NM 88004.
 RP DAVIS, DD, NEW MEXICO STATE UNIV,DEPT CHEM,LAS CRUCES,NM 88003.
 NR 52
 TC 2
 PU ELSEVIER SCIENCE BV
 PI AMSTERDAM
 PA PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS
 SN 0040-6031
 J9 THERMOCHIM ACTA
 JI Thermochim. Acta
 PD MAR 15
 PY 1991
 VL 175
 IS 2
 BP 175
 EP 188
 PG 14
 SC Chemistry, Analytical; Chemistry, Physical
 GA FE279
 UT ISI:A1991FE27900006
 ER
 
 
 PT J
 AU DAVIS, DD
    KILDUFF, JE
    KOONTZ, SL
 TI DIFFUSE REFLECTANCE INFRARED FOURIER-TRANSFORM (DRIFT) SPECTROSCOPIC
    STUDY OF ADSORBED HYDRAZINES
 SO SPECTROCHIMICA ACTA PART A-MOLECULAR AND BIOMOLECULAR SPECTROSCOPY
 LA English
 DT Article
 AB Diffuse reflectance spectroscopy of fuel hydrazines adsorbed on silica,
    silica-alumina, alumina and ferric oxide surfaces indicates that the
    primary surface-hydrazine interaction is hydrogen bonding.  Hydrazine,
    on adsorption to a deuterated silica surface, undergoes a rapid H/D
    exchange with deuterated surface silanol (Si-OD) groups.  Adsorption
    equilibria are rapidly established at room temperature. 
    Monomethylhydrazine and 1,1-dimethylhydrazine are similarly adsorbed. 
    On adsorption, the C-H stretching and methyl deformation modes of the
    methylhydrazines are shifted to higher frequencies by 10-20 cm-1. 
    These shifts are postulated to be due to changes in the lone-pair
    electron-density on the adjacent nitrogen-atom.  From a linear
    relationship of the electronegativities and deformation frequencies it
    is estimated that adsorption results in a 5% increase in
    electronegativity of the H-bonded atom.
 C1 NASA,LOCKHEED EMSCO,JOHNSON SPACE CTR,WHITE SANDS TEST FACIL,LAS CRUCES,NM 88004.
 RP DAVIS, DD, NEW MEXICO STATE UNIV,DEPT CHEM,LAS CRUCES,NM 88003.
 NR 21
 TC 2
 PU PERGAMON-ELSEVIER SCIENCE LTD
 PI OXFORD
 PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD, ENGLAND OX5 1GB
 SN 0584-8539
 J9 SPECTROCHIM ACTA PT A-MOL BIO
 JI Spectroc. Acta Pt. A-Molec. Biomolec. Spectr.
 PY 1991
 VL 47
 IS 2
 BP 299
 EP 308
 PG 10
 SC Spectroscopy
 GA EZ868
 UT ISI:A1991EZ86800016
 ER
 
 
 PT J
 AU WEDLICH, RC
    DAVIS, DD
 TI NONISOTHERMAL KINETICS OF HYDRAZINE DECOMPOSITION
 SO THERMOCHIMICA ACTA
 LA English
 DT Article
 C1 NEW MEXICO STATE UNIV,DEPT CHEM,LAS CRUCES,NM 88003.
    NASA,LOCKHEED ENGN & SCI CO,WHITE SANDS TEST FACIL,LAS CRUCES,NM 88004.
 NR 25
 TC 5
 PU ELSEVIER SCIENCE BV
 PI AMSTERDAM
 PA PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS
 SN 0040-6031
 J9 THERMOCHIM ACTA
 JI Thermochim. Acta
 PD NOV 24
 PY 1990
 VL 171
 BP 1
 EP 13
 PG 13
 SC Chemistry, Analytical; Chemistry, Physical
 GA EK644
 UT ISI:A1990EK64400001
 ER
 
 
 PT J
 AU STONE, DA
    WISEMAN, FL
    KILDUFF, JE
    KOONTZ, SL
    DAVIS, DD
 TI THE DISAPPEARANCE OF FUEL HYDRAZINE VAPORS IN FLUOROCARBON FILM
    ENVIRONMENTAL CHAMBERS - EXPERIMENTAL-OBSERVATIONS AND KINETIC MODELING
 SO ENVIRONMENTAL SCIENCE & TECHNOLOGY
 LA English
 DT Article
 C1 NASA,WHITE SANDS TEST FACIL,LAS CRUCES,NM 88004.
    NEW MEXICO STATE UNIV,DEPT CHEM,LAS CRUCES,NM 88003.
    USAF,CTR ENGN & SERV,DIV ENVIRON,ENGN & SERV LAB,TYNDALL AFB,FL 32403.
 NR 15
 TC 5
 PU AMER CHEMICAL SOC
 PI WASHINGTON
 PA 1155 16TH ST, NW, WASHINGTON, DC 20036
 SN 0013-936X
 J9 ENVIRON SCI TECHNOL
 JI Environ. Sci. Technol.
 PD MAR
 PY 1989
 VL 23
 IS 3
 BP 328
 EP 333
 PG 6
 SC Engineering, Environmental; Environmental Sciences
 GA T4691
 UT ISI:A1989T469100014
 ER
 
 
 PT J
 AU DAVIS, DD
    WEDLICH, RC
    BENZ, FJ
 TI NON-ISOTHERMAL KINETIC-STUDIES OF HYDRAZINE DECOMPOSITION
 SO ABSTRACTS OF PAPERS OF THE AMERICAN CHEMICAL SOCIETY
 LA English
 DT Meeting Abstract
 C1 NEW MEXICO STATE UNIV,DEPT CHEM,LAS CRUCES,NM 88003.
    NASA,JOHNSON SPACE CTR,WHITE SANDS TEST FACIL,LAS CRUCES,NM 88003.
 NR 0
 TC 0
 PU AMER CHEMICAL SOC
 PI WASHINGTON
 PA 1155 16TH ST, NW, WASHINGTON, DC 20036
 SN 0065-7727
 J9 ABSTR PAP AMER CHEM SOC
 JI Abstr. Pap. Am. Chem. Soc.
 PD JUN 5
 PY 1988
 VL 195
 PN Part 2
 BP 221
 EP PHYS
 PG 0
 SC Chemistry, Multidisciplinary
 GA P9362
 UT ISI:A1988P936201186
 ER
 
 
 PT J
 AU AKKERMAN, JW
 TI HYDRAZINE MONOPROPELLANT RECIPROCATING-ENGINE DEVELOPMENT
 SO JOURNAL OF ENGINEERING FOR INDUSTRY-TRANSACTIONS OF THE ASME
 LA English
 DT Article
 RP AKKERMAN, JW, NASA,LYNDON B JOHNSON SPACE CTR,HOUSTON,TX 77058.
 NR 0
 TC 0
 PU ASME-AMER SOC MECHANICAL ENG
 PI NEW YORK
 PA 345 E 47TH ST, NEW YORK, NY 10017
 SN 0022-0817
 J9 J ENG IND
 JI J. Eng. Ind.-Trans. ASME
 PY 1979
 VL 101
 IS 4
 BP 456
 EP 462
 PG 7
 SC Engineering, Mechanical
 GA HX846
 UT ISI:A1979HX84600011
 ER
 
 
 PT J
 AU STIEF, LJ
    PAYNE, WA
 TI ABSOLUTE RATE PARAMETERS FOR REACTION OF ATOMIC-HYDROGEN WITH HYDRAZINE
 SO JOURNAL OF CHEMICAL PHYSICS
 LA English
 DT Article
 C1 NASA GODDARD SPACE FLIGHT CTR,EXTRATERR PHYS LAB,ASTROCHEM BRANCH,GREENBELT,MD 20771.
 NR 22
 TC 24
 PU AMER INST PHYSICS
 PI WOODBURY
 PA CIRCULATION FULFILLMENT DIV, 500 SUNNYSIDE BLVD, WOODBURY, NY 11797-2999
 SN 0021-9606
 J9 J CHEM PHYS
 JI J. Chem. Phys.
 PY 1976
 VL 64
 IS 12
 BP 4892
 EP 4896
 PG 5
 SC Physics, Atomic, Molecular & Chemical
 GA BW208
 UT ISI:A1976BW20800013
 ER
 
 
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