BULLETINPIA

NASP Generic High Speed Engine TestedA generic high speed engine

(GHSE) model has been successfullytested by The Johns Hopkins University/Applied Physics Laboratory(JHU/APL) and NASA/LangleyResearch Center (LaRC) in supportof the Technology Maturation Planof the National AeroSpace Plane(NASP) Phase II Program . Theprime test objective of demonstratinglow Mach number performance of a

engine model is installedLangley Combustion Heated Scramjet Test Facility.The JHU/APL NASP B-1

hydrogen-fueled scramjet enginedesigned to meet high speed perfor-mance requirements was achieved .The engine model was tested in asemi-freejet mode at simulated flightconditions between Mach 4 and 5 inthe Combustion Heated ScramjetTest Facility of NASA's LaRC.Follow-up tests to demonstrate the

Vol. 15, No. 5, August 1989

intermediate Mach number perfor-mance (Mach 5 to Mach 8) of theGHSE model in the NASA/LaRCArc Heated Scramjet Test Facilityare scheduled to begin in the firstquarter of 1990.

Phase II of the NASP program isan effort to acquire and demonstratethe technology required to developsingle-stage-to-orbit vehicles thattake off and land on conventional

at the NASA-

runways. Phase III will culminate inthe flight test of an experimentalvehicle, the X-30. Hydrogen-fueledscramjet engines for the X-30 arebeing developed by Rocketdyne andPratt & Whitney. Airframe con-figurations are being developed byGeneral Dynamics, McDonnellcontinued on page 2

PropellantIngredients UpdateReport #1

The following is a brief listing ofrecent developments in the area ofrocket and gun propellant ingre-dients availability :

The Olin Corporation recentlyreceived an Army contract to build amanufacturing plant for hydroxylam-monium nitrate (HAN) in Charles-ton, Tennessee . HAN is presentlyused as an ingredient in a number ofliquid gun propellants, but no largescale production capability is pre-sently available . The Olin plantshould be completed in the early1990s.

The Western ElectrochemicalCompany (formerly PEPCON)should complete its new ammoniumperchlorate (AP) manufacturingplant, located in Cedar City, Utah, inSeptember 1989 . Initial AP produc-tion should begin shortly, at 20 mil-lion lbs/year . Full capacity will be40 million lbs/year.

The Jet Propulsion Laboratoryhas developed a pilot plant capabilityfor manufacturing oxygen difluorideoxidizer at a rate of up to 5lbs/hour. Oxygen difluoride is aspace-storable, highly energetic oxi-dizer that is not currently availablecommercially.

The French company, Atochem,recently acquired Sartomer, manufac-turer of R-45M and other hydroxy-terminated polybutadiene (HTPB)polymer binder materials . Atochemis considering building a plant inFrance to manufacture HTPB.

continued on page 2

RecentCPA/1988, Interim Issue E, Chemi-cal Propulsion Abstracts, Jun 1989.

CPIAJM5, "Liquid Propellant EngineManual," Unit 222 (LR87-AJ-11,Titan IV, 1st Stage Engine), Apr1989 .

CPIA/M5, "Liquid Propellant EngineManual," Unit 223 (LR91-AJ-11,Titan IV, 2nd Stage Engine), May1989 .

CPIA Pub. 488, "Chemical Propul-sion Abstracts," 1987 Bound Volume,Jun 1989 .

continued from page 1

Douglas, and Rockwell International.The government-sponsored Phase IINASP Technology Maturation Planis supporting the NASP engine andairframe contractors by generatingthe technology base required todevelop the X-30 .

The GHSE model simulates thestrut/isolator, constant area combus-tor and a portion of the divergingcombustor for a generic engineconcept developed by JHU/APL.The strut/isolator and constant areacombustor are full length, partialwidth representations of those of theconcept engine . The constant areacombustor is followed by a divergingcombustor section which representsthe initial portion of internal expan-sion for the engine concept operat-ing at high speed. The strut/isolatorsection provides additional compres-sion and instream fueling capabilityand is designed to prevent unfavor-able combustor/inlet interactions .The inlet of the model is not repre-sentative of one required for flight,

CPIA Publications

NASP High Speed Engine Tested

CPIA Pub. 496, "1988 JANNAFRocket Nozzle Technology Subcom-mittee Meeting," Nov 1988.

CPIA Pub. 507, "Propellant Develop-ment and Characterization Subcom-mittee Handbook," Section 540.1(Determination of Percent PGDN, 2-NDPA, and DBS in OTTO Fuel IIby Capillary Gas Chromatography),May 1989.

CPIA Pub. 512, "Application ofInternal Flow Field Modeling toSolid Rocket Motor Design," Jul1988.

but has the sole function of provid-ing a flow representative of entranceconditions for the concept engine atthe simulated flight speed .

In the NASA/LaRC tests, thecombustor performance of theGHSE model was measured over arange of equivalence ratios usingtransverse sonic and tangentialsupersonic fuel injectors at variousengine stations . Staging these injec-tors was an effective means forcontrolling the heat release, thermalchoking, and combustor/inlet interac-tions . The effect of fuel tempera-ture on engine performance was alsoinvestigated . The dynamic responseof the engine to stepped changes infuel flow was measured using highresponse pressure transducers. Thehigh response data are applicable tothe evaluation of the combustionstability and the generation of thetransfer functions for fuel controlmodels being developed by NASA'sLewis Research Center .

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Update #1continued from page 1

A recent OSHA list of hazardousmaterials includes the propellantplasticizers resorcinol and propyleneglycol dinitrate, the nitrate esterplasticizer precursor ethylene glycol,the propellant stabilizer diphenyl-amine, and sodium azide used in theproduction of glycidyl azide polymer(GAP) .

The JANNAF Propellant Devel-opment and Characterization Sub-committee has initiated a round-robin effort on standard testmethods applied to six differentpropellant hydrazines . Propellantsamples are being provided by themanufacturer, Olin Corporation.The round-robin will evaluate thereproducibility of the test methodsincluded in the military specificationsby exchanging results between labor-atories, and will evaluate alternatetest methods, including some pro-vided by the manufacturer . Forfurther information, contact TracyWilson at (301) 992-7302 .

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JANNAF Meeting:CMCS/S&MBS

The second joint meeting of theJANNAF Composite Motor CaseSubcommittee (CMCS) and Struc-tures & Mechanical Behavior Sub-committee (S&MBS) is scheduledfor 6-9 November 1989 at the JetPropulsion Laboratory, Pasadena,California . The meeting is being co-chaired by Ted Hicks of NWC/ChinaLake for CMCS, and for theS&MBS by John Kapeles of NWCand Frank Tse of NOS/Indian Head .

Prior to the panel meetings, therewill be a Service Life workshop onMonday afternoon, 6 November .The meeting is scheduled to beunclassified, but attendance is limitedto U.S . citizens who have been in-vited by the subcommittees' technicalsteering groups . For further infor-mation, contact Ms. Suzanne Appel-baum at (301) 992-7304 .

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Upcoming Joint Army-Navy-NASA-Air Force Events

1989 RNTS Meeting to be Held atNSWCWhite Oak

The 11th JANNAF Rocket Noz-zle Technology Subcommittee(RNTS) meeting will be held on 17-19 October 1989 at the Naval Sur-face Warfare Center (NSWC)/WhiteOak, Silver Spring, Maryland . Jef-frey Warren, NSWC, will serve asthe meeting chairman . The overallsecurity classification of this meetingis Unclassified, but attendance islimited to U.S . citizens with ademonstrated need-to-know.

Fifty technical papers and oneworkshop are scheduled for thisthree-day subcommittee meeting.Technical presentations will focus onthe following areas : nozzle qualityassurance and nondestructive evalua-tion, thermostructural modelingtechniques, nozzle design and failureanalysis, materials characterization,carbon-composite processing science,and thrust vector control . In addi-tion to the regular technical sessions,a workshop on thrust vector control

CombustionSubcommittee toMeet at JPL

The 26th JANNAF CombustionSubcommittee meeting will be held23-27 October 1989 at the Jet Pro-pulsion Laboratory in Pasadena,California . The Program Chairmanis Dr. G. Burton Northam ofNASA/Langley.

In addition to the 24 sessionsplanned, there will be two technicalinterchange lectures on Tuesday andWednesday prior to the morning ses-sions . These interchange lectureswere organized by Dr. Leonard H.Caveny, Office of Secretary ofDefense/Strategic Defense InitiativeOrganization, to stimulate broaderinvolvement of combustion scientists

technologies and problem areas willbe held . The annual review of theNASA Solid Propulsion IntegrityProgram, Nozzle Workpackage, willalso be held in conjunction with thismeeting, on 16 October, at NSWC.

The proceedings of this meetingwill be published and distributed byCPIA to qualified subscribers inJanuary 1990 . Authors of papers arereminded that the deadline for thereceipt of manuscripts and paperclearance forms at CPIA is 26 Sep-tember 1989. Cleared papers notreceived by this date might beremoved from the program .

Meeting attendees are alsoreminded that the deadline for thereceipt of personal registration formsat CPIA is also 26 September 1989.Admittance to the meeting may bedelayed if your registration form isnot received in time. For furthermeeting information, please contactMelissa Paul at (301) 992-7302 .

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in important DoD research areas .The Tuesday lecture will be on ultra-violet radiation generation fromrocket plumes, and the Wednesdaylecture will be on chemical laserswith an emphasis on visible wave-lengths .

The program sessions will covertopics of current interest to thecombustion community, includingelectrothermal, liquid propellant, andsolid propellant gun technology;engine and rocket motor perfor-mance ; combustion instability ; com-bustion diagnostics ; airbreathingpropulsion; nitramines ; and steady-state combustion. In addition, therewill be a workshop on standardiza-tion of combustion instabilitymeasurement and reporting, and ameeting of the kinetics and relatedaspects of propellant combustion

3

chemistry panel.The overall security classification

of the meeting is Confidential andrequires a need-to-know in the areasof missile, space, or gun combustiontechnology. Attendance is limited toU.S . citizens and authorizedimmigrant aliens within the U.S .chemical rocket and gun propulsioncommunity. However, graduatestudents who can obtain theappropriate need-to-know maybeinvited to attend the Unclassifiedsessions. For further information,call Ms. Dottie Becker at (301) 992-7303 .

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NPS to Host EPTSMeeting

The Naval Postgraduate Schoolwill host the 18th JANNAF ExhaustPlume Technology Subcommittee(EPTS) Meeting on 14-16 November1989 in Monterey, California . TheProgram Chairman is Mr. ThomasA. Smith, Astronautics Laboratory.The meeting will be classified Secretand attendance will be restricted toU.S . citizens by invitation from theEPTS Technical Steering Group.

The three day program includessuch topics as plume flowfieldstructure and 3D modeling ; speciesanalysis of exhaust plumes ; and UVsignatures and plume measurementsin Minuteman, launch vehicles,Peacekeeper, and other propulsionsystems . A workshop is scheduledfor the 14th on 3D Plume Analysis .

The invitation package willinclude preliminary program, hotelinformation, and security clearanceforms . CPIA must receive thesecurity clearance forms by Friday,27 October. Admittance to themeeting may be delayed and will bedenied without the receipt of thisform by CPIA. For further informa-tion, please contact Ms. SuzanneAppelbaum at (301) 992-7304.

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1989 JANNAF Propulsion Meeting Highlights

Developments inBallistic and TacticalMissile SolidPropulsion

Many of the papers presented atthis year's JANNAF PropulsionMeeting (JPM), held in Cleveland,Ohio in May, reviewed developmentsin ballistic and tactical solid propul-sion technology . Developmentexperiences with large systems, suchas the Trident II (D5) and the SmallICBM (SICBM), and with smallersystems like SRAM-II, VerticalLaunch ASROC and the Tomahawkbooster, were discussed, covering abroad spectrum of component andprogram issues . Other, more gen-eral aspects of solid propulsionsystems were also presented, includ-ing the effects of treaties on systemdesigns and force structure, designtrends, and motor disposal .

Current areas of interest specifi-cally include : high-burn rate propel-lants for interceptor boost propul-sion and rapid response boosters forICBMs; application of high-tempera-ture filament wound cases to tacticalmotors ; pulse motor developmentfor performance optimization in air-to-air missile propulsion; and com-bined thrust vector/aerodynamic con-trols .

The requirement for asbestos-freeinternal and external insulationsystems continues to promote re-search on materials that can be usedto replace asbestos both as a hightemperature material and as a struc-tural reinforcement . Replacementsmust generally fulfill the same sys-tem needs as asbestos (e.g ., ablativeproperties, thermal properties, etc .),and also satisfy cost and proces-sibility goals. Several programs havebeen undertaken to qualify non-asbestos composite insulators for

systems already in production.Common approaches to asbestosreplacement include substitution withAramid fiber or pulp, or otherorganic fibers, as reinforcement toan elastomeric matrix. For eachsystem, extensive evaluation of ther-mal, mechanical, and bonding pro-perties is required . Systems forwhich replacements are currentlysought include Phoenix and StandardMissile Mk 30 Mod 3.

Over the past few years, variousinvestigators have developed novelmethods of motor ignition usinglasers in place of conventionalinitiators or squibs . Recent studiesindicate that many of the failuremodes of electronically operated in-tiators are obviated by laser. Inaddition, laser initiators may offercost and reliability improvements.

In the tactical area, the compet-ing goals of improved performanceand improved safety characteristicscontinue . On one side, the serviceshave determined a need for insensi-tive munitions while maintainingperformance . Programs developedas a response have focused on newingredients that may reduce thesensitivity of energetic motor com-ponents and on other means ofreducing the response of propulsionsystems to hazardous stimuli .

Alternatively, the need for opera-tional capability has not diminished.Therefore, many of the redesignedsystems must also meet requirementsfor minimum observables (exhaustsignature) while delivering acceptableor superior performance. Newoxidizers such as CL-20 may help tomeet these goals . Investigation ofphase-stabilized ammonium nitratehas continued, primarily to meet thelow observability goal . Other novelingredients, such as superfine ironoxide burning-rate modifiers, can beused to upgrade the performance of

continued on page 6

4

AP Hazards andSafety Issues

Current transportation and stor-age hazard testing efforts relating toammonium perchlorate (AP) werepresented in two specialist sessionsat the JPM. Dr . Jerry Ward, DoDExplosives Safety Board (DDESB),reported the results of hazard clas-sification tests conducted in accor-dance with the United Nations docu-ment, "Recommendations on 'theTransport of Dangerous Goods."These tests were conducted to clas-sify AP-filled articles, not the APitself. The series included singlepackage tests and external fire testson 55 gal steel drums and 5,000 lbaluminum bins .

For the 55 gal steel drums, singlepackage tests were conducted withNo. 8 blasting cap and black powder ;in both cases, sandbag confinementswere used. The blasting cap tests,by and large, did not result in fire .The black powder initiation tests allresulted in fire, which lasted forapproximately 30 seconds .An external fire stack test was

also conducted on the 55 gal steeldrums . This test calls for five testarticles banded together in a closepack . The article stack is suspendedby a steel crib and surrounded bydiesel-fuel/motor-oil drenched wood.The wood stack is ignited remotely,and is expected to burn for 30minutes. During the test, two drumswere ejected from the stack andtheir lids were blown off, there wasa very small fireball, but noexplosion was observed.

None of the single packageignition tests for the 5,000 lb alumin-um bins, either the black powder orthe No. 8 blasting cap, resulted inexplosions. One of the three blast-

continued on page 6

Insensitive Munitions

Efforts in the Insensitive Muni-tions (IM) area have been directedtowards developing both new insensi-tive formulations and effective miti-gation concepts . The developmentof insensitive propellant formulationsfor rugged nondetonable minimumsignature application has been anongoing Army research effort. Newrugged nondetonable minimumsmoke propellant formulationsdeveloped by the U.S . Army MissileCommand (MICOM), Aerojet, andThiokol use a PSAN oxidizer, anenergetic or inert binder, and ener-getic plasticizers to produce formula-tions that have Isps of about 230 s .They are considered insensitivebecause they give negative results inthe card gap test.

Another area of interest in IMpropellant formulation is the devel-opment of energetic thixotropic gels .In general, thixotropic gels produceburning results in both the fast cook-off test and the bullet impact test,which are acceptable from the IMviewpoint . Research into this areahas been conducted at MICOM, theNaval Weapons Center (NWC),Comarco Inc ., and Talley Industries .

In order to assess a new formula-tion's possible application as an IMpropellant, its sensitivity propertiesare first determined using small-scaletests . The NOL Card Gap Test isuniversally used by much of thecommunity to determine the shocksensitivity of energetic materials .Because an appropriate card gap testshould be chosen relative to thepropellant's critical diameter,Atlantic Research Corp. (ARC) alsouses the Expanded Large-Scale GapTest to better simulate the condi-tions seen by rocket motors in astorage configuration during asympathetic detonation scenario . To

JPM Highlights (Continued)determine critical diameters, ARChas successfully used an "inverted"wedge test .

Investigators associated withMICOM have used the bullet impacttest to determine the relative shockand impact sensitivities of tacticalrocket propellants . Dr. ThomasCost, with the University of Alabamain Huntsville, has developed amethod to correlate card gap testresults with bullet impact test resultsfor a given propellant and attenua-tion material . Other researchershave discovered a transient shockreaction in the bullet impact initia-tion mechanism .

Ordnance items can also achieveIM status by using mitigation devicesthat are either forward fit (designedin the rocket motor assembly) orretrofit . Much of the work in thisarea for the Navy occurs at theNWC, where the effectiveness oftactical missile mitigation devices hasbeen assessed . Other NWC testshave compared the effectiveness ofpressure release devices and casesagainst standard steel and compositerocket motor cases . These tests in-cluded fast cook-off, slow cook-off,and bullet impact . A case and/ormitigation device should be chosenbased upon an evaluation of boththe propellant's sensitivity propertiesand probable life-cycle hazards .

Also of extreme importance arethe efforts to gather and makeaccessible the large quantity of datarelevant to IM testing and mitigationconcepts. Ms. Carolyn Dettling,NWC, has been active in the devel-opment of various IM-relevantdatabases including the MunitionsStatus Information Center (MSIC),Insensitive Munitions EngineeringTechnology (IMET), and the Ener-getic Materials Information Center(EMIC) . MSIC contains large-scaleIM test information on several air-launched missile components and is

5

scheduled to be released byNAVSEA at the end of GFY 1989.IMET contains information on IMtest results and their relevance tomitigation devices and concepts.This database may eventually givethe user some indication as to thedegree of technical maturation ofexisting mitigation devices and con-cepts . When completed, EMIC willcontain information on physical,thermodynamic, sensitivity, and otherproperties for propellants, explosives,and pyrotechnics .

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~`f Wit. ~f

Liquid Propulsion

The liquid propulsion sessionscovered chemical propulsion technol-ogy, propellants, and propulsionsystems .

The technology sessions includedpresentations on the regenerativecooling limits of nitrogen tetroxideand monomethylhydrazine for upperstage storable liquid engines, thedevelopment status of the XLR-132engine, large low cost titanium liquidpropellant tanks, and low cost stora-ble upper stage engines based onhigh performance derivatives of theAgena engine . The potential of theexpander cycle engine to meet ge-neric advanced space mission re-quirements was explored . The Path-finder chemical transfer propulsionprogram will define technology issuesthat are essential and peculiar to aspace-based, reusable, fault-tolerant,man-rated liquid oxygen/liquid hydro-gen expander-cycle engine for futurespace exploration. A liquid oxygentoroidal tank for high energy upperstages was described, and spacetransfer vehicle engine integratedcontrols and health monitoring werediscussed .

The propellants and combustionprocesses session addressed the useof ethylene dihydrazine and itshydrazine blends as high perfor-mance fuels for future propulsionsystems. Also covered were spraycharacterization of liquid/liquid im-pinging injectors, combustion devicesfor oxygen/hydrocarbon engines, andthe effect of propellant flow rate andpurity on carbon deposition in liquidoxygen/methane gas generators .

The session on chemical propul-sion systems applications looked atthe potential for using a Space Shut-tle-launched storable liquid propel-lant powered space transfer vehiclefor delivering payloads to geosyn-chronous earth orbit. The impact ofadvanced auxiliary propulsion systemtechnology on the payload capabilityof advanced earth-to-orbit vehicleswas covered, and the pertinentaspects of earth and space storablepropellants as they apply to futurespace vehicles were explored .

The spacecraft chemical propul-sion session considered the enablingtechnology for a new class of long-life, high-performance, radiation-cooled bipropellant thrusters capableof operation at temperatures greaterthan 4,000°F. Also discussed wasthe feasibility demonstration of a 100lbf nitrogen tetroxide/monomethyl-hydrazine rocket engine using a highperformance injector coupled withan iridium-lined rhenium thrustchamber. Finally, Space Stationpropulsion technology which vali-dates the propulsion system conceptwas summarized .

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AP Hazardscontinued from page 4

ing cap tests and one of the blackpowder ignition tests resulted infires . All three black powder testsresulted in the ejection of AP.

JPM Highlights (Continued)The external fire test consisted of

five 5,000 lb aluminum bins bandedtogether, for a total of 25,000 lbs ofAP. The AP burned for approxi-mately 4 minutes, and the fireballdid not extend beyond the witnessscreens--no explosion or hazardousfragments.

AP storage tests were reported byDr. Claude Merrill, AstronauticsLaboratory, Edwards AFB. The testsequence included a 5 gal containerexterior ignition test, a 5 gal con-tainer interior ignition test, and a500 lb drum propagation distancetest .

Mr . Thomas Boggs, NWC, report-ed on an extensive effort to charac-terize the thermal, physical, andsensitivity properties of AP. Theseinclude activation energy, thermaldecomposition, reaction products,ballistic heating, differential scanningcalorimetry, accelerated rate calori-metry, ignition temperature of gas-eous products, adiabatic flametemperature, drop weight impact,and card gap results.

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Missile Propulsioncontinued from page 4

systems that may meet the hazardrequirement. New thermoplasticbinder materials may improve pro-ducibility and structural reliability oftactical motors .A new driver may have to be

considered by those planning advan-cement of ballistic missile propulsiontechnologies through research anddevelopment. Recent developmentsin weapons treaties and in ongoingtalks on limiting or eliminatingwhole classes of delivery systemsmay lead to consideration of meansof propulsion system disposal as anengineering issue in the designphase. The intertheater nuclearforces treaty resulted in the destruc-tion of all Pershing motors. Many

6

systems currently in the field may besubject to disposal or demilitarizationin the near future . Added to thoseare motors produced in the 1960swhich may require disposal due toaging out. Finding environmentallyacceptable and cost-effective meansof disposal, while at the same timemeeting any relevant treaty obliga-tions, will be a difficult task .

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S&EPS CM CreditsThe American Board of Industrial

Hygiene has reported their review ofthe technical content of the 1989Annual Meeting of the JANNAFSafety and Environmental ProtectionSubcommittee (3-6 April 1989).They assigned 0.5 continuing main-tenance (CM) credits for attendanceat each half day of the meeting.They also assigned 0.5 CM pointsfor attending the workshop onRCRA compliance and enforcement.Certified industrial hygienists whoattended these meetings may assignthese points to their accumulatedbalance for periodic recertification.a

ASTM MeetingThe American Society for Testing

and Materials (ASTM) will hold theHazard Potential of ChemicalsCommittee Meeting (E-27) on 7-9November 1989 at the Disney WorldVillage in Orlando, Florida. ForDetails, call Rose Dougherty(ASTM) at (215) 299-5487.

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9th Detonation SymposiumThe Ninth Symposium (Intern-

ational) on Detonation will be heldfrom 28 August through 1 Septem-ber 1989 in Portland, Oregon. Forfurther information, contact WandaJ. Ohm (NSWC) of the OrganizationCommittee at (202) 394-4414.

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Disposal of Solid Rocket Motor Propellants

In 1972, deep water/ocean dump-ing of excess propellants was prohib-ited . Open burning/open detonation(OB/OD) disposal of propellants,currently the least costly of disposaloptions, came under increasing scrut-iny following passage of the Re-source Conservation and RecoveryAct (RCRA) laws of the early 1980s,and is allowed only under specialexemptions from individual states .These exemptions will be increasing-ly difficult to obtain from state andfederal authorities if it cannot bedemonstrated that OB/OD does notcontribute to ground water and airpollution . Current and prospectivestrategic missile arms control trea-ties, as well as aged-out propellantaccumulation, may lead to overload-ing existing disposal facilities .Therefore, the Department ofDefense will be impelled to selectalternate propellant disposal method-ologies, such as controlled incinera-tion or extraction and reclamation ofpropellant ingredients .

The resale of missiles is limitedto a small number per year ; land filldisposal of pyrotechnics, explosives,and propellants (PEP) is prohibited.The disposal problem is briefly sum-marized in the box below .

Any disposal method needs to becritically evaluated against multiplecriteria, including the following:disposal efficiency; technical feasi-

bility; adaptability ; complexity; rawmaterials processing; scale-upcapability; safety; environmentalimpacts; and construction and opera-ting costs .

Propellant aging issues are animportant facet of the disposal prob-lem . Some hazardous propellantsmay have to be disposed of onsite toavoid inherent transportation haz-ards . Mobility would also be anattractive feature of a prospectivedisposal system .

OB/OD and static firing havebeen the disposal methods of choicefor some 30 years, due to their lowcost and high reliability, and arecurrently being utilized as the dis-posal method for the Pershing fleetcovered under the INF treaty .While specific weather criteria aremaintained to assure rapid dilutionof the exhaust gases, and theunburned solid residues are collectedand buried in landfills, thesemethods are only allowed by specialwaivers granted by individual states .

Therefore, alternate methods arein development, including controlledincineration (rotary kiln and fluidizedbed) and ingredient extraction andreclamation . Neither route is with-out its flaws . For example, incin-erators require supplemental fuel tooperate and need scrubbers to con-trol their airborne effluents, but

Excess missile disposition1) Other uses (resale, space launch, test motor, slurry explosives)2) Destruction as is (OB/OD, static firing)

Excess missilewith hardwareremoved

propellant removal

-from case1) machining2) hydraulic washout3) chemical removal4) thermal removal

propellant disposal1) destruction

thermalchemicalphysicalbiological

2) reclamationsolvent extractionbinder solvolysis

scrubbers generate liquid waste.Ingredient reclamation is only costeffective for high cost or low availa-bility materials, and once theingredient is reclaimed it must berequalified, which is a lengthy pro-cess . Other methods are being pur-sued, such as binder solvolysis, wetair oxidation, supercritical fluid ex-traction and/or oxidation, and biode-gradation methods .

Since no optimum disposalmethod is apparent, a combinationof methods will probably be requiredto attain complete destruction ofPEP waste materials . For example,solvent extraction and reclamation ofa particular propellant ingredient willlikely be followed by incineration ofthe PEP residues .

It appears that if OB/OD disposalis restricted, then some form ofincineration (fluidized bed or rotarykiln) is probably the most technicallymature alternative . If expensive orlow availability ingredients are con-tained in the waste propellant, someform of ingredient reclamation maybe cost effective .

For disposal or reclamation ofpropellants by these new techniques,the propellant must be removedfrom the motor case and reduced insize . While only disposal methodsare discussed here, further informa-tion on propellant removal techni-ques, such as hydraulic and mechani-cal methods, can be found in CPIALS88-09, "Removal of Solid Propel-lant from Rocket Motor Cases."

Further information on propellantdisposal technologies will be pub-lished in an upcoming ChemicalPropulsion Technology Review, tobe published in September 1989.

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CP/A

Attendance At JANNAF Conferences and Workshops is by imitation only.

MEETING CALENDAR SUBJECT' TO CIIANGE. FOR LATEST DETAILS, CONTACT CPIA at (301) 992-7306.

CHEMICAL PROPULSIONINFORMATION AGENCY

THE JOHNS HOPKINS UNIVERSITY - APPLIED PHYSICS LABORATORYJOHNS HOPKINS ROAD, LAUREL, MARYLAND 20707

The Bulletin is published bimonthly by the Chem-ical Propulsion Information Agency (CPIA) . CPIAis a DoD Information Analysis Center responsiblefor the acquisition, compilation, analysis, and dis-semination of information and data relevant to chem-ical and electric propulsion technology . In addition,CPIA provides technical and administrative supportto the Joint Army-Navy-NASA-Air Force (JAN-NAF) Interagency Propulsion Committee. The pur-pose of JANNAF is to solve propulsion problems,coordinate technical programs, and promote an ex-change of technical information in the areas of mis-sile, space, and gun propulsion technology . A feecommensurate with CPIA products and services ischarged to subscribers . Also, subscribers must meetsecurity and need-to-know requirements .

The Johns Hopkins UniversityApplied Physics LaboratoryJohns Hopkins RoadLaurel, Maryland 20707-6099(301) 953-5850Operating under Contract N00039-87-C-5301

Ms . Catherine McDermott

EditorMs . Lorri A . Pickett

Associate EditorMs . Brenda R . Prater

Pasteup

U .S. POSTAGE

PAI DLAUREL,MARYLANDPERMIT No.1885

NONPROFIT ORGANIZATION

19139 Meeting Type Location Sec. ClassAbstract/Paper

Deadline

15-16 Aug Nitrocellulose Problem Areas Workshop VPI&SU Unclassified/ N/A N/ABlacksburg, VA Limited

17-19 Oct JANNAF Rocket Nozzle Technology Conference/ NSWC Unclassified/ Past 26 SepSubcommittee Meeting Workshops White Oak, MD Limited

23-27 Oct JANNAF Combustion Subcommittee Conference/ JPL Confidential/ Past 9 OctMeeting Workshops Pasadena, CA Limited

6-9 Nov JANNAF Joint Composite Motor Conference/ JPL Unclassified/ Past 6 OctCase Subcommittee/Structures & Workshops Pasadena, CA LimitedMechanical BehaviorSubcommittee Meeting

14-17 Nov JANNAF Exhaust Plume Technology Conference/ NPS Secret Past 6 OctSubcommittee Meeting Workshops Monterey, CA

28 Nov-1 Dec JANNAF Propellant Development Conference/ JHU/APL Unclassified Past 10 Novand Characterization Workshops Laurel, MDSubcommittee Meeting

1990

2-6 Apr JANNAF Propulsion Systems Conference/ JIIU/APL Confidential/ 23 Oct TBAHazards Subcommittee Meeting Workshops Laurel, MD Limited