1、 Special ProjectAIAASP-084-1999Fire, Explosion, Compatibility, and SafetyHazards of Hypergols - HydrazineAIAA standards are copyrighted by the American Institute of Aeronautics andAstronautics (AIAA), 1801 Alexander Bell Drive, Reston, VA 20191-4344 USA. All rightsreserved.AIAA grants you a license
2、as follows: The right to download an electronic file of this AIAAstandard for temporary storage on one computer for purposes of viewing, and/or printingone copy of the AIAA standard for individual use. Neither the electronic file nor the hardcopy print may be reproduced in any way. In addition, the
3、electronic file may not bedistributed elsewhere over computer networks or otherwise. The hard copy print may onlybe distributed to other employees for their internal use within your organization.AIAA SP-084-19991Correction Log5 December 20011. Reference for ERP E515-80 on page 66 should be TR-226-00
4、1.2. Expression for liquid density obtained from Yaws on page 132 should reflect proper conversion forreduced temperature and proper exponent. The expression is replaced by the following equation:2/780.0)273.15K)/3(T(K)13L5380.3171x0.2)(Mg/m=(3. Table B.1 (that was actually for Monomethylhydrazine)
5、is replaced with the correct table for hydrazine.Please see page 2 of the correction log for the table.AIAA-SP-0842Table B.1 Thermodynamic properties of hydrazineTKPKPaVLm3/gVVm3/gHL(T,P)Sat. liquidJ/gHV(T,P)Sat. vaporJ/gSL(T,P)Sat. liquidJ/g KSV(T,P)Sat. VaporJ/g K288 0.99 9.98E-07 7.52E-02 -29.91
6、1379.03 0.0258 4.79298 1.86 1.00E-06 4.15E-02 0.00 1394.28 0.0000 4.68308 3.34 1.01E-06 2.39E-02 28.90 1409.16 -0.0202 4.58318 5.73 1.02E-06 1.44E-02 57.80 1424.59 -0.0311 4.49328 9.48 1.03E-06 8.96E-03 86.47 1440.25 -0.0351 4.40338 15.16 1.03E-06 5.77E-03 115.01 1456.14 -0.0332 4.33348 23.51 1.04E-
7、06 3.83E-03 143.51 1472.22 -0.0258 4.26358 35.47 1.05E-06 2.61E-03 172.09 1488.47 -0.0135 4.20368 52.16 1.06E-06 1.82E-03 200.84 1504.88 0.0030 4.15378 74.97 1.07E-06 1.30E-03 229.87 1521.40 0.0235 4.10388 105.51 1.08E-06 9.42E-04 259.30 1538.01 0.0475 4.06398 145.65 1.13E-06 6.97E-04 289.75 1554.62
8、 0.1422 4.02408 197.54 1.10E-06 5.25E-04 319.79 1571.30 0.1048 3.98418 263.59 1.11E-06 4.01E-04 351.05 1587.90 0.1376 3.95428 346.47 1.13E-06 3.10E-04 383.14 1604.40 0.1729 3.92438 449.14 1.14E-06 2.43E-04 416.15 1620.75 0.2104 3.89448 574.77 1.16E-06 1.93E-04 450.18 1636.88 0.2500 3.86458 726.81 1.
9、17E-06 1.54E-04 485.30 1652.73 0.2915 3.84468 908.90 1.19E-06 1.25E-04 521.62 1668.24 0.3350 3.82478 1124.88 1.21E-06 1.02E-04 559.20 1683.33 0.3801 3.80488 1378.76 1.23E-06 8.34E-05 598.11 1697.92 0.4270 3.78498 1674.68 1.25E-06 6.90E-05 638.43 1711.92 0.4754 3.77508 2016.89 1.27E-06 5.74E-05 680.2
10、2 1725.24 0.5254 3.75518 2409.71 1.30E-06 4.80E-05 723.54 1737.79 0.5770 3.73528 2857.46 1.33E-06 4.03E-05 768.43 1749.43 0.6301 3.72538 3364.48 1.36E-06 3.40E-05 814.96 1760.04 0.6847 3.70548 3935.03 1.40E-06 2.88E-05 863.17 1769.46 0.7409 3.69558 4573.25 1.44E-06 2.44E-05 913.13 1777.52 0.7987 3.6
11、7568 5283.16 1.49E-06 2.08E-05 964.90 1783.98 0.8583 3.66578 6068.57 1.54E-06 1.77E-05 1018.57 1788.59 0.9198 3.64588 6933.03 1.60E-06 1.51E-05 1074.28 1790.97 0.9835 3.62598 7879.81 1.68E-06 1.28E-05 1132.21 1790.65 1.0496 3.59608 8911.84 1.77E-06 1.09E-05 1192.69 1786.91 1.1188 3.57618 10031.63 1.
12、88E-06 9.14E-06 1256.32 1778.67 1.1919 3.54628 11241.30 2.03E-06 7.61E-06 1324.26 1764.03 1.2705 3.50638 12542.46 2.25E-06 6.21E-06 1399.38 1739.03 1.3584 3.44648 13936.22 2.68E-06 4.81E-06 1493.07 1692.16 1.4695 3.36Reference temperature = 298 KT = temperature HL= enthalpy, liquidP = pressure HV= e
13、nthalpy, vaporVL= specific volume, liquid SL= entropy, liquidVV= specific volume, vapor SV= entropy, vaporAIAASP-084-1999Special Project ReportFire, Explosion, Compatibility, and SafetyHazards of Hypergols - HydrazineSponsored byAmerican Institute of Aeronautics and AstronauticsApprovedAbstractThis
14、Special Project report presents information that designers, builders, and users of hydrazine systemscan use to avoid or resolve hydrazine hazards. Pertinent research is summarized, and the data arepresented in a quick-reference form. Further information can be found in the extensive bibliography.AIA
15、A SP-084-1999iiPublished byAmerican Institute of Aeronautics and Astronautics1801 Alexander Bell Drive, Reston, VA 22091Copyright 1999 American Institute of Aeronautics andAstronauticsAll rights reservedNo part of this publication may be reproduced in any form, in an electronicretrieval system or ot
16、herwise, without prior written permission of the publisher.Printed in the United States of AmericaAIAA SP-084-1999iiiContentsForeword viAcronyms viiiGlossary . ixTrademarks . xiii1 Introduction to hazard assessment 11.1 About this special report 11.2 Approach to performing a hazard assessment . 11.2
17、1 Fire hazards 31.2.2 Explosion hazards . 41.2.3 Material compatibility . 81.2.4 Exposure hazards . 91.3 Overall hazard . 102 Fire . 112.1 Hydrazine vapor 112.1.1 Flammability 112.1.2 Ignition 172.1.3 Flame velocity . 272.2 Liquid hydrazine 322.2.1 Flash and fire points 322.2.2 Burning rate and bur
18、ning velocity 332.3 Hydrazine mists, droplets, and sprays . 342.3.1 Flash and fire points 342.3.2 Burning rates . 343 Explosion 373.1 Deflagration. 373.1.1 Hydrazine vapor 383.1.2 Liquid hydrazine 403.2 Detonation 413.2.1 Detonation t heory 413.2.2 Hydrazine vapor 413.2.3 Liquid hydrazine 473.3 Ther
19、mochemical reaction 483.3.1 Thermodynamic instability . 483.3.2 Thermal runaway. 49AIAA SP-084-1999iv3.3.3 Rapid compression524 Hydrazine and material compatibilit y.584.1 Material degradatio n584.1.1 Test method584.1.2 Test conditions584.1.3 Material compatibility data.594.1.4 Alloy corrosion studi
20、es .604.2 Material e ffects on hydrazine.604.2.1 Test methods604.2.2 Test conditions714.2.3 Hydrazine decomposition data .724.2.4 Chemical reactivity of hydrazine in air804.3 Assessment examples .804.3.1 Estimation of relative decomposition rates for material applications for which thematerial respo
21、nse to hydrazine is well know n814.3.2 Effects of materials on the heat generation rate.834.3.3 Hazard analyses855 Safety.915.1 Hydrazine toxicit y915.1.1 Results of hydrazine exposur e.925.1.2 Inhalation935.1.3 Exposure to skin, eyes, and mucous membrane s945.1.4 Ingestion.945.1.5 Carcinogenicity.9
22、45.2 Environmental fate of hydrazin e955.2.1 Air.955.2.2 Water955.2.3 Soil.955.2.4 Bioaccumulation and biodegradation.965.2.5 Remediation965.3 Hydrazine exposure guidelines965.3.1 Threshold limit values of the American Conference of Gove rnmentalIndustrial Hygienists975.3.2 Guidelines of the Occupat
23、ional Safety and Health Administratio n975.3.3 The National Institute Of Occupational Safety And Healt h985.3.4 Emergency planning requirement s985.3.5 Spacecraft maximum acceptable concentration s.99AIAA SP-084-1999v5.3.6 Environmental regulations . 995.4 Hydrazine exposure reme diation and control
24、 . 1005.4.1 First aid . 1005.4.2 Personnel protection . 1035.4.3 Smell. 1035.4.4 Medical surveillance 1045.4.5 Evacuation procedures 1045.4.6 Protective apparel . 1045.4.7 Fire fighting . 1055.4.8 Spill cleanup 1055.5 Hydrazi ne handling 1065.5.1 Engineering design 1065.5.2 Storage containers 1075.5
25、3 Storage areas 1085.5.4 Transportation . 1085.5.5 Monitoring equipment 1105.5.6 Waste disposal 1135.5.7 Current regulatory enforcement . 1145.5.8 Additional information 1155.6 Assessment example 115Annex A: Hazard assessment example . 121Annex B: Chemical, physical, and thermodynamic properties of
26、 hydrazine 130Annex C : References 138AIAA SP-084-1999viForewordHydrazine is a colorless, corrosive, strongly reducing liquid compound. Current aerospace applicationsinclude its use in the Space Transportation System as a fuel for the auxiliary power units, in satellites as amonopropellant for thrus
27、ters, and in jet aircraft as fuel for auxiliary power sources. Although hydrazine isimmensely useful in these applications, there are also drawbacks. For example, hydrazine vapor isflammable and detonable; both liquid and vapor hydrazine are corrosive, react with many materials, andare susceptible t
28、o catalytic decomposition; and hydrazine is highly toxic. The users and designers ofhydrazine systems must be aware of these hazards and safeguard against them.This AIAA Special Report preserves the text of NASA document RD-WSTF-0002 Rev A, December 17,1998, “Fire, Explosion, Compatibility, and Safe
29、ty Hazards of Hydrazine,” developed by the NASA WhiteSands Test Facility for the Propulsion and Power Division of the Lyndon B. Johnson Space Center andthe Air Force Space Division. In the interests of technology transfer, custody of the material wasassigned to AIAA through of Memorandum of Understa
30、nding dated February 1999. One of the purposesof this Memorandum is to provide broader distribution of the valuable information developed andpublished in the original manual.The authors of the NASA Revision A manual, dated December 16, 1998 are: Stephen S. Woods, DonaldB. Wilson, Dennis D. Davis, Mi
31、chelle Barragan, Walter Stewart, Radel L. Bunker, and David L. Baker.Authors to the earlier 1990 edition are: Michael D. Pedley, David L. Baker, Harold D. Beeson, Richard C.Wedlich, Frank J. Benz, Radel L. Bunker, and Nathalie B. Martin.AIAA Special Reports are a part of the AIAA Standards Program a
32、nd frequently serve as precursors toformal consensus documents. This publication is under the purview of the Liquid Propulsion Committeeon Standards, the group responsible for determining the future of the publication and for maintaining it ina technically current state.The AIAA Standards Procedures
33、 provide that all approved standards, recommended practices, andguides are advisory only. Their use by anyone engaged in industry or trade is entirely voluntary. There isno agreement to adhere to any AIAA standards publication and no commitment to conform to or beguided by any standards report. In f
34、ormulating, revising, and approving standards publications, the LiquidPropulsion Committee on Standards will not consider patents that may apply to the subject matter.Prospective users of the publications are responsible for protecting themselves against liability forinfringement of patents, or copy
35、rights, or both.At the time of publication, the members of the AIAA Liquid Propulsion Committee on Standards were:Robert Ash Old Dominion UniversityKyaw Aung Georgia Institute of TechnologyC. T. Avedisian Cornell UniversityCurt Botts Air Force, 45 th Space Wing, Patrick AFBPatrick Carrick Phillips L
36、aboratoryFred Cutlick California Institute of TechnologyTom Draus NASA Kennedy Space CenterIrvin Glassman Princeton UniversityHoward Julien AlliedSignal Technical ServicesChad Keller Hughes AerospaceCharles Leveritt Army Research LaboratoryDennis Meinhardt Primex Aerospace CompanyAIAA SP-084-1999vii
37、Mark Mueller Aerospace CorporationGregory Nunz Los Alamos National LaboratoryBryan Palaszewski NASA Lewis Research CenterSteven Schneider NASA Lewis Research CenterJoseph Shepherd California Institute of TechnologyTimothy Smith NASA Glenn Research Center at Lewis FieldBill St. Cyr NASA Stennis Space
38、 CenterRay Traggianese OlinMark Underdown NASA GoddardStephen Woods AlliedSignal Technical ServicesThe Standards Executive Council accepted the document for publication on April 30, 1999.AIAA SP-084-1999viiiAcronymsA, E a Arrhenius parametersACGIH American Conference of Governmental and Industrial H
39、ygienistsAHJ Authority Having JurisdictionAPU Auxiliary power unitARC Accelerating rate calorimeterASME American Society of Mechanical EngineersCERCLA Comprehensive Environmental response, Compensation, andLiability ActC-J Chapman-JouguetCPIA Chemical Propulsion Information AgencyDDT Deflagration to
40、 detonation transitionDOT Department of TransportationDOT Department of TransportationEIS Electrochemical Impedance SpectroscopyEPA Environmental Protection AgencyFDCA Food, Drug, and Cosmetics ActGI GastrointestinalHAZMAT Hazardous MaterialsHZ HydrazineIDLH Immediately Dangerous To Life or HealthIR
41、FNA Inhibited Red Fuming Nitric AcidJANAF Joint-Army-Navy-Air ForceJANNAF Joint-Army-Navy-NASA-Air ForceLEPC Local Emergency Planning CommitteeLFL and UFL Lower and Upper Flammability LimitMIE Minimum Ignition EnergyMMH MonomethylhydrazineMSDS Material Safety Data SheetNIOSH National Institute of Oc
42、cupational Safety and HealthNPDES National Pollutant Discharge Elimination SystemOSHA Occupational Safety and Health AdministrationPEL Permissible Exposure LimitsRCRA Resource Conservation and Recovery ActREL Recommended Exposure LimitRQ Reportable QuantitySARA Superfund Amendments and Reauthorizati
43、on ActSERC State Emergency Response CommissionSI International System unitsSMAC Spacecraft Maximum Acceptable ConcentrationSTEL Short Term Exposure LimitSTS Space Transportation SystemTLD-1 Toxic Level Detector 1TLV Threshold Limit ValueTLV-TWA Threshold Limit Value - Time Weighted AverageTOMES Toxi
44、cology, Occupational Medicine, and Environmental SeriesTPQ Threshold Planning QuantityTRI Toxic Release InventoryTSCA Toxic Substances Control ActAIAA SP-084-1999ixGlossaryActivation Energy (or Apparent Activation Energy): In absolute-rate theory, the energy associatedwith the formation of an activa
45、ted complex intermediate between the reactant(s) and product(s) of anelementary reaction. An “apparent” activation energy is used as the parameter E a in an Arrheniusfunction when the exact kinetic mechanism is unknown.Adiabatic: A process in which the system changes state without thermal energy exc
46、hange between thesystem and the surroundings.Adiabatic Compression: Mechanical work transferred to a system under conditions where there is anincrease in the internal energy of the material for a static system or an increase in the enthalpy for adynamic system. If the process is also reversible (in
47、the thermodynamic definition), this change is alsoisentropic.Adiabatic Factor: The temperature change that occurs when all the limiting reactant is completelyconsumed (normalized extent of reaction equals 1 when the reaction system is operated adiabatically).This factor is useful for comparing exoth
48、ermicity or endothermicity of several reactions.Adiabatic Flame Temperature: The temperature of thermodynamic equilibrium in a reaction or in a setof reactions that occurs in a process operating adiabatically.Arrhenius Function: A mathematical model for defining the temperature dependency of an obse
49、rvedmacroscopic kinetic reaction rate. The rate is equal to Aexp(-E a /RT), where A is the preexponentialfactor, E a is the apparent activation energy, R is the ideal gas law constant, and T is the absolutetemperature.Authority Having Jurisdiction (AHJ): Organization, office, or individual responsible for “approving”equipment, an installation, or a procedure. The designation is used in a broad manner becausejurisdiction and “approval” agencies vary, as do their responsibilities. Where public safety is primary, theAHJ may be a federal, state, local, or other regional department
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