The Johns Hopkins University Chemical Propulsion … Johns Hopkins University Chemical Propulsion Information Agency Hu/1e tin ... Rocket Propulsion System ... CPIA retains copies

Mira 1.

‘‘‘112

The Johns Hopkins University

Chemical Propulsion Information Agency

Hu/1e tinFol. 19 . No. 3, Hal . 1993

The Propulsion Engineering Research Center atPenn State Offers State-of-the-Art Technolog yThe Pennsylvania State University' s

Propulsion Engineering Research Cen-ter (PERC) was established in 1988 a sthe result of a national peer-reviewedcompetition byNASA to establish SpaceEngineering Research Centers (SERCs )at universities across the U.S . Thepurpose of these centers is to train stu-dents with interests and expertise i nspace engineering to meet the nation' sfuture space technology needs . SERC swere established in such diverse spaceengineering categories as construction ,continued on page 14

DC-X Debuts as SSTO Prototyp e

Penn State's Propulsion Engineering Research Center .

The DC -X rolls out for inspection .

The Delta Clipper - Experimental(DC-X) launch vehicle was shown offto the aerospace world in early April atMcDonnell Douglas Aerospace's Hun-tington Beach, California Flight Opera -tions Control Center . Developed for theStrategic Defense Initiative Orga-nization's Single-Stage Rocket Tech-nology (SSRT) Program, the vertica ltakeoff and landing (VTOL) DC-X wil lundergo cold-flow, static-ground an dflight tests this summer at the WhiteSands Missile Range in New Mexico .This test series will include mission -duration engine firings, propellant load -ing, verification ofvehicle maintenanceprocedures, and ground and flight con-trol operations .

While the 1/3-scale size DC-X wil lnever achieve orbit, it will test the fea-sibility of single-stage-to-orbit (S STO )rockets, including the eventual DC-Y .Part of a suborbital S SRT test program ,the DC-X is fueled by liquid oxygen an dliquid hydrogen (LOX/LH 2 ) and pow-ered by four modified Pratt & Whitne ycontinued on page 1 2

Contents :Propellant Ingredients Update

Profile : Wickman Spacecraft &

Propulsion Compan y

Gelled Propellant s

JANNAF Events

Defense Conversion and the

Propulsion Industry

Recent CPlpulic"Chemical Propulsion Mailing List, "Mar 1993 .

"Selected Bibliographies, Handbooks ,Manuals, and Reviews," Apr 1993 .

CPA/1993 - Interim Issue A, Chemica lPropulsion Abstracts, Mar 1993 .

CPIA Pub . 593, "29th JANNAF Com-bustion Subcommittee Meeting," Vols .I-V (Vol . V is Confidential), Oct 1992 .

LS93-05 : Interior Ballistic Models fo rGun Systems ; period covered 1969-1993 ; 231 citations and abstracts .

LS93-06 : Non-Lead Catalysts for SolidPropellants ; period covered 1963-1993 ;266 citations and abstracts .

LS93-07 : Rocket Propulsion SystemStatic Testing; period covered 1961 -1993 ; 903 citations and abstracts .

LS93-08 : Combustion Instability inMinimum Smoke Propellants ; periodcovered 1969-1993 ; 63 citations an dabstracts .

LS93-10 : Pyrotechnics, Initiators, an dPropellant Actuated Devices ; period

covered 1960-1993 ; 1,059 citations andabstracts .

LS93-11 : Nozzle Recession (Super-sedes LS89-12) ; period covered 1961 -1993 ; 434 citations and abstracts .

LS93-12 : Carbon Composite Mate-rial Properties (Supersedes LS89-09) ;period covered 1969-1993 ; 623 cita-tions and abstracts .

LS93-13 : Hydrazine Fuels Compat-ibility (Supersedes LS84-10) ; periodcovered 1967-1993 ; 334 citations andabstracts .

CPIA's Technical/Bibliographic Inquirie s

Subjects covered in recent inquiriesinclude the following :

•MAPO (Methylaziridinyl phos-phine oxide) Availability and Alterna-tive Sources (see also LS92-14, "NewPropellant Ingredients" )

•Non-Catocene Bum Rate Modifi-ers for Ammonium Perchlorate Propel-lants (see also LS80-10, "Iron BurnRate Modifiers" and LS88-10, "Cop -per Burn Rate Catalyst" )

*RP-1 Specification and Availabil-ity (see also CPIA/M6, "AirbreathingPropulsion Manual")

•Hydrocarbon Binders (see als oCPTR 87-42, "New Solid Rocket Pro-pellant Polymer Binder Materials" )

•Space Transportation System Slag

•Data Sheet on LGP- 1845 (see als oCPIA/M4, Unit 32, "LGP-1846")

•Soviet Solid Rocket Launch Ve-hicle Performance Data (see also LS90 -12, "Foreign Propulsion Technology" )

•JA-2 Propellant

• Solid Rocket Motor Aging Effect s(see also LS91-02, "Accelerated Ag-ing")

•Liquid Propellants Used for Ga sGenerators, Guns, and Torpedoe s

•Mass Transport in Nitrocellulose-Based Propellants

•Nitroglycerin Lower Explosiv eLimit in Air (see also CPIA/M3, Uni t37, "NG")

•Sidewinder Missile Propellant .

CPIA invites inquiries via telephone ,fax, or letter . For further information,please contact Mr . Tracy Wilson at(410) 992-7306 .+

The Chemical Propulsion Informatio nAgency (CPIA) is a DoD Information Analysi sCenter administratively managed by the Defens eTechnical Information Center (DTIC) . CPIA i sresponsible for the acquisition, compilation, analy-sis, and dissemination of information and dat arelevant to chemical and electric propulsion tech-nology . In addition, CPIA provides technical an dadministrative support to the Joint Army-Navy-NASA-Air Force (JANNAF) Interagency Propul-sion Committee . The purpose of JANNAF is tosolve propulsion problems, effect coordination o ftechnical programs, and promote an exchange oftechnical information in the areas ofmissile, space ,and gun propulsion technology . A fee commen-surate with CPIA products and services is chargedto subscribers, who must meet security and need-to-know requirements .

The Bulletin is published bimonthly an dis available free of charge to the propulsion com-munity . Reproduction of Bulletin articles is per-missible, with attribution .

Ms. Catherine McDermott

EditorMs . Lorri Pickett

Associate Editor(410) 992-7307

Fax (410) 730-496 9

The Johns Hopkins University/CPI A10630 Little Patuxent Parkway, Suite 202Columbia, Maryland 21044-320 0

Operating under Contract N00014-91-C-000 1

Page 2

CPIA Bulletin/Vol . 19, No. 3, May 1993

Attention Structural Analysts :CPIA can meet your in formation needs!

The structural analysis of solid propellant rocket motors requires specialize dknowledge ofthe motor materials, loads, designs, and analytical techniques . TheCPIA maintains a number of publications that are intended to assist the moto rstructural analyst . Among these are JANNAF manuals, CPIA bibliographies,handbooks, JANNAF meeting papers, and other references on structural integrityanalysis . These include :

.r JANNAF Solid Propellant Mechanical Behavior Manual, CPIA Publica-tion 21, Aug 1972 ;

Handbook for the Engineering Structural Analysis of Solid Propellants ,CPIA Publication 214, May 1971 ;

JANNAF Solid Propellant Structural Integrity Handbook, CPIA Publica-tion 230, Sep 1972 ;

JANNAF Structures & Mechanical Behavior Subcommittee Report o nthe Linear Viscoelastic Round Robin Analysis, Sep 1987 (w/o pubnumber) ;

.t Fundamental Studies Relating to Systems Analysis of Solid Propellants ,Feb 1961, GALCIT SM 61-5 (reprint) ;

id- Solid Rocket Mechanical Behavior/Structural Integrity, 1983 JANNA FPropulsion Meeting Specialist Session, CPIA Publication 374 ;

Nonlinear Structural Analysis Methods, CPIA Publication 450, No v1985 (Structures & Mechanical Behavior Subcommittee Workshop) ;

go- Case/Grain Interaction in Composite Case Rocket Motors (1986 JANNA FPropulsion Meeting Specialist Session), CPIA Publication 458, Aug1986; and

Proceedings of the JANNAF Structures and Mechanical Behavior Sub -committee (1977-present) .

In addition to these, CPIA retains copies of hundreds of reports and document sfrom Government, industry, and academic sources on rocket motor and soli dpropellant grain structural analysis in our document library . We can rapidl ylocate and retrieve highly relevant information in these reports for you throughPIRS (CPIA's Propulsion Information Retrieval System) .

If you are a propulsion structural analyst and you need information on relate dtopics, please call either Dottie Becker at (410) 992-7302 to request copies of aspecific document, or Tracy Wilson at (410) 992-7306 to request a technica linquiry for answers to specific questions . +

CPIA Telephon eNumbers

These are direct dial Baltimore are aexchange numbers of CPIA staff mem -bers . If you call a busy line, your cal lwill cycle to another phone .

Area Code : (410)

i General Information

992-7300

Document Orders

7302

JANNAF Information

730 3

Technical Inquiries

730 6

FAX Number

730-496 9

Dottie Becker

992-730 2

Karen Brown

730 1

Chris Cameron

7307

Tom Christian

7300

Jim Cocchiaro

730 5

Sharon Counihan

7307

Debbie Eggleston

7300

I Jeff Filliben

730 5

Mary Gannaway

7304

Sharon Hasty

7304

Harry Hoffman

7304

Camille Hudson

730 5

Catherine McDermott

7307

Paul Myers

7307

Melissa Paul

730 3

Lorri Pickett

7307

ILee Piper

7303

Tom Reedy

7306

Tracy Wilson

7306

Clark Youmans

730 1

------------

CPIA Bulletin/Vol. 19, No. 3, May 1993

Page 3

Propellant Ingredients Update Report # 9The following is a brief listing o f

recent developments in the area of rocketand gun propellant ingredients avail -ability :

•Atochem doubled its sodiu mchlorate capacity at its plant nearGrenoble to 90,000 metric tons . So-dium chlorate is used as a chlorin ereplacement in paper and pulp bleach-ing, and in the production of sodiu mperchlorate used to make ammoniu mperchlorate (AP) . Atochem is th eworld's largest producer of sodiu mchlorate, and is the third largest pro-ducer of perchlorate. France's SNP EChemie has acooperative venture (calle dBupera) with Italy's SNIA BPD t omanufacture AP at a new plant in

Toulouse . SNPE is the world's secondlargest producer of nitrocellulose, and i talso produces hexamine for explosives ,hydrazines, and isocyanate curatives .

•Olin recently commissioned anisophorone diisocyanate (IPDI) plant inLake Charles, Louisiana, with a capac-ity of 15 million lbs/year, competingdirectly with Germany's Huls plant atTheodore, Alabama. Olin will als oproduce hexamethylene diisocyanate a tthis plant . Both companies convertisophorone nitrile feedstock into the dia-mine, followed by phosgenationto IPDI ,which is a commonly used curing agentin solid rocket propellants .

*Purdue University has developed alow-cost, nontoxic method for produc-

ing rayon fibers from low-grade cellu-lose feedstock . Rayon-based carbo nfibers have been used in the manufac-ture of a number of solid rocket moto rnozzles, including the Space Shuttle .Recently Lenzing, an Austrian rayo nfiber producer and this country's sec-ond largest, increased its productioncapacity at its Lowland, Tennessee plantby 25%. The largest U.S. producer,Courtaulds Fibers, had no plans fo rexpansion at its Mobile, Alabama plant.

For further information on thes eitems, or on the subject of propellantingredients availability, please contac tTracy D . Wilson (CPIA) at (410) 992 -7306, or FAX (410) 730-4969 . +

Recommended Reading :"Modern Engineering for Design

ofLiquid-Propellant Rocket Engines, "D. Huzel and D . Huang, RocketdyneDivision of Rockwell International, Vol .147 of Progress in Astronautics an dAeronautics, 1992 (AIAA) .

This detailed tome is an excellenthandbook for liquid rocket engine de-signers, as it transitions from require-ments definition and preliminary enginedesign, to component developmen t(thrust chamber, injector, propellant fee dsystems, tankage), and then to system /vehicle integration. Tailored aspects o fmain engine vs . reaction control sys-tem/attitude control system engine de -sign are covered . A chapter on enginecontrol and health monitoring system sis most timely .

"Solid Rocket Propulsion Technol-ogy, " A. Davenas (Editor), SNPE De-fense Espace, Paris, France, 199 2(Pergamon Press) .

This companion to the more com-monly recognized U .S. textbooks deal -

ing with rocket propulsion provides amuch-needed foreign perspective to th efield . Topics include grain design andstructural analysis, internal ballistic sand combustion, plume phenomena, in -sulation and liner materials, and safety/hazards . Both double-base and com-posite propellants are covered, as wel las propellants for integral rocketramjets .

"Rocket Propulsion," M. Barrere ,et al ., ONERA, Paris, France, 1960(Elsevier) .

Readers further interested in foreignaspects of propulsion technology maywish to attempt to locate this reference,particularly as it lends an interestinghistorical flavor to the topic .

"Chemical Rockets, and Flame andExplosives Technology, "R. Holzmann ,AIAA, Washington, DC, 1969 (Marce lDekker) .

Also of historical interest is this tex twhich may be useful as an introduction

to the field for new propulsion scientist sand engineers .

Q

Other reference materials that read -ers may wish to consider include th efollowing :

"Research and Technology Pro -gram for Enhancing the Competitive-ness of the Current U.S. ExpendableLaunch Vehicle Fleet, " Department ofTransportation: Commercial SpaceTransportation Advisory Committee(COMSTAC), Innovation and Tech-nology Working Group, April 1992 .

"The Future of the US. SpaceLaunch Capability, " Vice President' sSpace Policy Advisory Board, Novem -ber 1992 .

"Nuclear Rocket Engine Optimiza-tion Program, " LEW-15474, from th eNASA Computer Software Technol-ogy Transfer Center (COSMIC) ; cal l(706) 542-3265 . +

Page 4


NondestructiveCharacterization o fMaterialsSymposium Wil lMeet in Hawai i

The Sixth International Symposium

on Nondestructive Characterization of

Materialswill convene at Oahu, Hawai i

on 7-1 1 June 1993 . Dr. Robert E .

Green, Jr ., of the Johns Hopkins Uni-

versity Center forNondestructive Evalu-

ation (NDE) and Dr. Clayton O . Ruud

of the Pennsylvania State Universit y

Materials Research Laboratory are the

principal organizers, as well as the

founders, of this symposia series .

This symposium will be of interest

to engineers and scientists concerne d

with manufacturing problems from raw

materials through final fabrication an d

in-service evaluation, as well as practi-

tioners of research and development .

What follows is a list of featured ses-

sions :

ACOUSTIC TECHNIQUE S

AIRCRAFT/AEROSPACE

BIOMIMETIC AND BIOTIC MATERIAL S

CERAMICS

ELECTRONIC MATERIALS/COMPONENT S

MATERIALS CHARACTERIZATION

MATERIALS PROPERTIES

OPTICAL PROPERTIES

PROCESS CONTROL

RESIDUAL STRES S

ULTRASONIC S

X-RAY TECHNOLOG Y

The proceedings ofthis symposium

will be published as "Nondestructiv e

Characterization of Materials VI" by

Plenum . For more information on at-

tending this event, contact its coordina-

tor, Ms. Debbie Harris ofJohns Hopkin s

University'sNDE center, at (410) 516-

5397 . v

The following are various meetings/events of which we have been apprised. Wewelcome all such announcements, so that the propulsion community can be bette rserved with timely information .

Sponsor Topic Dates Location(1993 )

ADPA : International Gun & Propellants(Meeting)

6/1-3 Dover, N J

Environmental Restoratio nOpportunities Conference

6/8-9 Munich, Germany

AGARD: Rocket Motor Plume Technology 6/7-8 Neubiberg, Germany(Lecture Series) 6/10-11 Ankara, Turkey

6/15-16 Monterey, C A

AIAA : Chemical Propulsion in theEnvironment (Course - i nConjunction with PropulsionConference)

6/26-27 Monterey, C A

29th AIAA/SAE/ASME/ASEE Join tPropulsion Conference

6/28-30 Monterey, CA

ASMI : Advanced Aerospace Materials /Processes Conference an dExposition (AeroMat '93)

6/7-10 Anaheim, CA

IRIA : 40th National Infrared InformationSymposium

5/25-27 Laurel, M D

JHU/CNDE: 6th International Symposium onNondestructive Characterization o fMaterials

6/7-11 Oahu, H I

NASA : 1993 Space Station Freedo mUtilization Conference

6/21-24 San Francisco, C A

NIMIC : Cookoff Workshop 6/23-25 Brussels, Belgiu m

Sensitivity of Energetic 7/19-21 Aberdeen Provin gMaterials When Fracture dor Granular (Workshop)

Grounds, M D

SEA: Nozzle Performance, Grain Design, &SRM Stability Prediction (Course)

5/17-21 Carson City, NV

ADPA = American Defense Preparedness Association, (703) 522-1820 .AGARD = Advisory Group for Aerospace Research and Development, (619) 939-2246 .AIAA = American Institute of Aeronautics and Astronautics, (202) 646-7400 .ASMI = ASM International, (216) 338-5151 .IRIA = Infrared Information Analysis Center, (313) 994-1200, x2323 .JHU/CNDE = Johns Hopkins University, Center for Nondestructive Evaluation, (410) 516-5397 .NASA = National Aeronautics & Space Administration, (202) 479-5242 .NIMIC = NATO Insensitive Munition Information Center, (32) (2) 728 .SEA = Software and Engineering Associates, Inc., (702) 882-1966 .


Page 5

Profile: Wickman Spacecraft & Propulsion Compan y

This is the first in an occasionalseries on small propulsion-related busi-nesses. For more information on theWickman Spacecraft and PropulsionCompany (WSPC), contact Mr . JohnWickman at (307) 265-5150 .

WSPC's initial project in the earl y1980's was the development of a zincoxide phase-stabilized ammonium ni-trate to be used in clean burning soli dpropellants . Under the tradename o fPSAN-I, it is now being sold to rocke tmanufacturers around the world . Theproject's principal investigator, Dr .Adolf Oberth, also discovered the useof magnesium as a combustion catalys tfor ammonium nitrate space booste rpropellants .

The company has been working on anoncryogenic liquid propellant oxidize rand will pursue patent options . It isnontoxic, environmentally friendly an dhypergolic with certain metallized fu-els . Engineers will begin testing thi soxidizer with kerosene in a ballistic

rocket motor this fall . Pressure-fed an dpump-fed engines using this oxidize rcould be put into production in 1995 ,subject to funding arrangements .

Last year, WSPC began research o nliquid oxygen (LOX) monopropellant susing fuels such as coal, kerosene, mo-tor oil, propane, natural gas, and rub-ber . The feasibility studies were funde dby NASA/Lewis Research Center(LeRC). Candidate monopropellant swere subjected to shock tests and ambi -ent pressure burn-rate tests . Coal andrubber were found to be too shock sen-sitive; propane and natural gas couldnot be uniformly mixed in the LOX .The best candidates were LOX/kero-sene and LOX/motor oil monopropel-lants . Neither were shock sensitive up toa maximum impact of 1,300 Joules (th elimit of the testing equipment) . Themaximum specific impulse for LOX /kerosene is 269 .4 seconds and for LOX/motor oil, 262 .5 seconds, at a chamberpressure of 3 .45 MPa. They also burne din a nonexplosive and steady manner .

The advantage of LOX monopro-pellant rocket engines over conventiona lbipropellant engines is the reduction inlaunch vehicle inert weight by eliminat-ing the fuel tank, feed lines, pump, andassociated hardware . Since the fuel andoxidizer are premixed, the LOX mono -propellant rocket engine has the advan-tage of operating at the optimum mix-ture ratio for all throttle settings . Aunique feature of these engines is theability of one engine to run on differentLOX monopropellants . For example,an engine could use LOX/kerosene forEarth to orbit and then be refueled inorbit with LOX/aluminum obtainedfrom processed lunar soil .

WSPC plans to test the kerosene/LOX monopropellant in their ballisti cmotor by fall of 1993 . This same engin ewill also be used to conduct further test swith the aluminum/LOX monopropel-lant . Dependent upon contract awards ,pressure-fed, LOX/kerosene monopro-pellant rocket engines would be readyfor production in 1995 . More powerful ,pump-fed engines could be put intoproduction in 1998 .

Under an earlier contract withNASA/LeRC, the company formulateda rocket propellant composed entirelyof elements which could be obtainedfrom processed lunar soil . It has beendesignated as Lunar Soil Propellant, orLSP. The propellant consists of LOXand fuel premixed to form a monopro-pellant . The research project began inan effort to find a rocket propellant tha tused ingredients found entirely on th emoon, making a lunar base self suffi-cient for its propulsion needs .

Potential lunar fuel candidates werealuminum, silicon, magnesium, tita -

Ballistic motor test of PSAN-I space booster propellant . The same motor willbe used to test the LOX/kerosene monopropellant .

Page 6

CPIA Bulletin/Vol. 19, No . 3, May 1993

WSPC 's new facilities near Casper, Wyoming.

nium, and iron . The major difficulty i nmaking a working engine was finding away to get the metal powders into th erocket combustion chamber in a con -trolled manner. WSPC chose to inves-tigate the approach ofmixing the meta lpowder with LOX to form a slurry o rmonopropellant. The monopropellantwould then be pumped into the combus -tion chamber . However, this approac hhad the potential for explosive burnin gof the monopropellant, propagation o fthe flame front up the propellant fee dtube, propellant shock sensitivity, andsettling ofthe fuel powder in the propel -lant.

As part of their research, WSPCengineers mixed aluminum, aluminum/magnesium (80/20 by weight) and sili -

Wickman 's burn-rate test of theirLOX/kerosene monopropellant.

con with LOX. Cab-O-Sil (2% byweight) was added to the aluminum andaluminum/magnesium formulations forgelling, while the silicon formulationused 3%. Test results showed none ofthe formulations detonated when ig-nited. Within a 7-hour period, settlingwas detected only in the 29% aluminumand 29% aluminum/magnesium formu-lations .

The monopropellants were thenburned in an open-ended aluminum cyl -

inder which was partially submerged i na liquid nitrogen bath . Experimenta ldata at ambient pressure indicated thatthe monopropellants were extinguishedwhen the flame front reached region ssubmerged under the liquid nitrogen .The monopropellants burned in a pul-sating manner, with the aluminum/mag-nesium appearing to have a more steadycombustion. The silicon monopropel-lant burned with an orange glow an dwas not energetic .

A subscale rocket engine was buil tto test the aluminum/LOX monopropel-lant. The engine underwent a series o ftests in June of 1991 with various burndurations and was throttled from idle t omaximum thrust . No flashback of th eflame front from the combustion cham -ber to the propellant tank occurred inany of the tests .

The company relocated from Sacra-mento, California to Casper, Wyomin gin February of this year . The newfacility consists of 60 acres with 22,00 0square feet of building space and thecapability to test rocket engines up to25,000 pounds of thrust. Additionalland will be acquired in the comingyears for testing of larger engines .

WSPC plans to set aside 20 acres fo ra visitor's center at its facility in Casper .Interested parties will be able to watc hrocket engine firings from the contro lroom . The center will contain an exhi -bition of future space vehicles, an

IMAXTM theater, hands-on experimentsillustrating space flight and propulsio nconcepts. A full-scale, working mode lofa lunar base will be built that will als obe open to the public . In the late 1990's ,the center will be expanded to include aneducational summer program that wil lafford access to real rocketry facilities ,rather than simulators .

The company plans to develop andproduce a reusable, educational sound -ing rocket suitable for use by highschools and colleges . A PC-compatibl eguidance computer along with parts fo rcustomizing the rocket will be sold byWSPC. The solid rocket engines for th esounding rocket are removable and wil lbe sold by the company so that studentswill not have to mix and cast propel-lants . WSPC will work with educator sin the development of this rocket toensure that it reaches its full potential a sa teaching aid . v

If your company qualifies as asmall business, and you would like t ohave it profiled in the CPIA Bulletin ,let us hear from you! We will be gladto publish your article (subject toediting) and feature your areas ofpropulsion expertise . For more in-formation, contact Catherin eMcDermott (Editor) at (410) 992 -7307 .


Page 7

Gelled Propellants Hold Promise as Insensitive Munition sOffering many of the advantages of both liquid and soli d

propellants, gelled propellants are becoming a new option fo rfuture DoD and NASA missions . When compared to liqui dsystems, gelled propellants offer reduced hazards associate dwith leaks or spills of high energy propellants . They can bea means of improved performance by incorporating hig henergy metallic fuels such as aluminum .

When compared with solid propellant systems, they offe rthe potential of improved energy management through vari-able thrust or on-off motor operation . Metallized storablegelled systems offer comparable energy/density to solid mo-tors in many applications. Non-metallized gelled propellantscan provide high energy minimum signature exhaust systems .Gelled propulsion systems also provide a means to meet th ejoint service requirements for insensitive munitions .

Gels are formed from liquid propellants through the addi -tion of gelling agents and surfactants . There are two genera lclasses of gelling agents, particulates and swellable polymers .The particulate gelling agents are insoluble in the carrie rliquid, have large surface areas, and possess sufficient attrac -tive forces at their surfaces to impart a gel structure to th eliquid . The swellable polymers are partially soluble in th eliquid carrier but maintain sufficient structure to provide th efluid with gel properties .

In programs conducted in the 1960's and early 1970's, avariety ofthe swellable polymer gelling agents were shown to

be effective in gelling hydrazine-based (monomethylhydrazine ,MMH; and unsymmetrical dimethylhydrazine, UDMH) an dmixed-amine storable fuels . Similarly, most of the storabl eoxidizers such as nitric acid and nitrogen tetroxide could b egelled with particulate agents such as finely divided silica .

The U .S . Army Missile Command (MICOM), Huntsville ,Alabama, has built on these early efforts by sponsoring anumber of recent development programs to characterize andevaluate in detail storable metallized and non-metallize dgelled propellants . Table 1 shows examples of the types offuel and oxidizer gels that are of interest . The fuel, designatedMICOM gel, consists of about 60 weight/percent aluminumdispersed in MMH containing 2% of gellant/stabilizer . Theoxidizer consists of about 65% inhibited red fuming nitric aci d(IRFNA) with about 30% lithium nitrate as a high densit yadditive and 5% gellant . These fuel and oxidizer gels ar ehypergolic, and they will only react violently when they com einto contact with each other . Relevant MICOM programshave included extensive vibration, compatibility, expulsio nsystem, and hot-fire testing. The organizations involve dinclude Aerojet Propulsion Division, TRW Systems, Talle yIndustries, the Naval Air Warfare Center, as well as th eMICOM Huntsville laboratories .

Aerojet is pursuing this technology through the Army' sStrategic Defense Command to develop a gelled rocket stag efor a future high-speed interceptor missile . This major gelledpropulsion development program is afour-year, multi-million

Table 1. Characteristics of Representative Tactical Gelled Propellant s

MICOM Fuel Gel IRFNA Oxidizer Gel

Compositio n(Wt%)

Aluminum - 60Monomethylhydrazine - 3 8

Gellant/Stabilizer - 2

Lithium Nitrate - 3 0IRFNA - 65Gellant

- 5

Density (g/cc)770F 1 .49 1 .7 8

Freezing Point -65°F < -65° F

Stability No settling after 30 minutes at 500 gacceleration

No settling after 30 minutes at 500 gacceleration

Sensitivity Shock - NegativeCompression - Negative

Shock - Negativ eCompression - Negative

Page 8


dollar effort . The program will culmi-nate with full-scale ground tests whic hwill demonstrate restart and throttlin gcapability.

Of particular significance were in -sensitive munitions tests conducted atthe Naval Air Warfare Center at ChinaLake, California, on storable gels in atactical missile tankage configuration .These tests included slow cookoff, fas tcookoff, and bullet penetration . Thepropellants met the military standardsfor insensitive munitions, exhibitin gonly burning with no explosions . Nocurrent tactical motors can meet all o fthe guidelines called for by the JointService Requirements for InsensitiveMunitions .

100

o.ll0000

Shear Rate, 1/se cloo 1000 100000 1000000

10

1

MMH/AL t MMH GEL A IRFNA

While gelled propellants offer manyadvantages, they also pose new techni-cal challenges because of their unusualrheological characteristics . Gelled pro -pellants fall into the class of time-dependent non-Newtonia nfluids, known as thixotropic fluids . Newtonian fluids arethose which show a linear relation of stress versus strain, s othat the viscosity is a constant. Since the viscosity is aconstant, designers of flow systems can predict pressure drop sof a fluid throughout a piping system with a degree o fconfidence.

With non-Newtonian fluids, the shear stress varies withthe rate of shear and the viscosity is a function of shear rate an dsometimes previous shear history . In addition, gelled propel -lants exhibit a solid-like characteristic at zero shear rate . Theyresist flow until a minimum shear stress is reached which i scalled the yield point . As shear rate increases, shear thinnin gtakes place (as shown in Figure 1), which gives the apparentviscosity of MMH and IRFNA gels as a function of shear rate .

To overcome these difficulties, gelled propellant develop -ers rely on special flow characterization facilities to develo pa database for gelled propellant candidates . These facilitiesusually include temperature conditioning, pressurization andmass-flow measurement systems which allow calibration o fflow-through realistic feed system components such as tankoutlets, various diameter tubes, bends, and valve and injectorsystems .

With the progress made over the past several years an dsignificant ongoing development programs, gelled propulsio nsystems are becoming a practical alternative for many tactica lapplications . CPIA is preparing a Chemical PropulsionReview Article that will cover this technology in more detail .Watch for its announcement in an upcoming issue ofthe CPI ABulletin .v

Figure 1 . Apparent viscosity of candidate gelled propellants as a function o fshear rate .

Since the shear rate varies greatly throughout a typica lengine feed system, from the tank outlet to the injector, th eprediction of pressure drops and mass flow becomes ver ycomplicated if not intractable . Because of this, maintainin gthe proper oxidizer-to-fuel mixture ratio in the engine can b edifficult .


Page 9

This article was written by Thomas L. Reedy(Associate Director of CPIA), the in-house tech-nical specialist with 30 years' experience i nramjet and solid rocket propulsion technology.He is also the CPIA Technical Representative o nthe JANNAF Airbreathing Propulsion Subcom-mittee. Mr. Reedy can be reached at (410) 992 -7306.

Joint Army-Navy-NASA-Air Force EventsS&EPS to Meet at NASA/White Sand sTest Facility

Siegel ReceivesJAN NAF Award

Mr. David S . Siegel of the Office ofNaval Research is the recipient of the1993 JANNAF Certification of Recog-nition. This award is presented annu-ally to selected propulsion scientistsand engineers in recognition of theirefforts to further the objectives of theJANNAF Interagency Propulsion Com-mittee (IPC) and their contributions t oadvance chemical and electrical propul-sion technology .

Since 1986, Mr. Siegel has servedon the Executive Committee, the gov-erning body ofthe JANNAF IPC, as on eof the two official U .S. Navy represen-tatives. From November 1990 to Octo-ber 1992, he chaired the JANNAF Ex-ecutive Committee (EC) . During histenure as chairman, new policies andprocedures were adopted that greatl yimproved the operations ofthe JANNA FIPC and its ten technical subcommit-tees. Mr. Siegel spearheaded the 199 1effort to have the JANNAF Agreementand Charter updated and approved . Healso educated the JANNAF EC on th egoals and mission of Project Relianc eand has brought members of both ProjectReliance and the JANNAF IPC into acloser relationship .v

The 1993 JANNAF Safety & Envi -ronmental Protection Subcommittee(S&EPS) Meeting will be held on 10-1 2August at NASA's White Sands TestFacility, Las Cruces, New Mexico . Mr .John A. E . Hannum of the Office of theChief of Naval Operations will serve a sthe meeting chairman .

This meeting will include technica lsessions on propellant, explosives, an dpyrotechnics (PEP) reclamation, dis-posal, and demilitarization ; environmen -tal impacts of propellant operations ;explosive safety; atmospheric hazard sand modeling ; propellant vapor detec -tion and rocket exhaust monitoring in -strumentation ; propellant toxicity an d

The 1993 JANNAF Propulsio nMeeting (JPM) will be held on Mondaythrough Thursday, 15-18 November inMonterey, California . Attendance i slimited to U.S. citizens whose organiza-tions are certified with the Defense Lo-gistics Services Center to obtain ex-port-controlled technical data . Partici-pation in classified sessions is restricte dto individuals who possess a persona lsecurity clearance of at least Confiden -tial with a need-to-know in the areas o frocket, missile, space, or gun propul-sion . Unclassified sessions ofthe meet -ing will be held at the Hyatt Hotel ;classified sessions will be conducted atthe Naval Postgraduate School (NPS )in Monterey, California . This year' smeeting is hosted by the Naval Air

industrial hygiene issues; and PEP wastetreatment and hazardous waste control .

The security level of the meeting i sUnclassified . Attendance is limited toU .S. citizens and authorized immigrantaliens employed by DoD, NASA, or aDoD/NASA contractor registered wit hthe Defense Technical Information Cen -ter (DTIC) or the Defense Logistic sServices Center (DLSC) .

The preliminary program includingregistration information will be distrib -uted in June . For further information ,contact Ms. Camille Hudson (CPIA) at(410) 992-7305.v

(see S&EPS table Egr)

Warfare Center Weapons Divisio n(NAWCWPNS), China Lake, Califor-nia. Mr . C . Franklyn Markarian ,NAWCWPNS, is the Meeting Chair-man. Further information about theJPM can be obtained by calling Ms .Debra Eggleston, CPIA, at (410) 992 -7300 .

During the same week of 15-19 No -vember, the JANNAF Combustion Sub-committee (CS) will conduct its 1993meeting, also at the NPS . The technicalsessions for these two meetings will b eorganized to minimize conflict and al-low attendance at both meetings . Formore information about the CS meet-ing, contact Ms. Mary Gannaway at(410) 992-7304 . +

Mr. David S. Siegel

id\

1993 JPM and Combustion Subcommitte eMeeting Will Coincide in Monterey

Page 10


JANNAF Safety & Environmental Protection Subcommittee Meeting - August 1993

Sessions

Papers to be Presented

Atmospheric andOther Hazards

Hot Spills Computer Model for Evaluating Chemical Fires

Instrumentation

Evaluation of the MDA/Polymetron Analyzer as a Monitorfor Hydrazine Vapor Samples

Characterization of the Exhaust Cloud of a 37-Inc hMagnesium Fueled Rocket Motor

The Fluorescence Detection of Hydrazine an d

Monomethylhydrazine via Derivatization with2,3-Naphthalene Dicarboxaldehyoe and

2,3-Anthracene Dicarboxaldehyde

Field Analysis and Measurement of pH and HydrazineContent in Rainwater Containment Troughs at Kenned ySpace Cente r

Field Test and Storage Stability of a Dosimeter System forUnsymmetrical Dimethylhydrazine ,Monomethylhydrazine and Hydrazine

EnvironmentalProtection

Realities of Working with a 1940's Plant in the 1990' s

Conceptual Design for Biological Denitrification of By -Product from the Manufacture of HMX and RD X

Denitration of Nitrate Ester Contaminated Wastewater inExplosive Production Operation

Photocatalyzed Decomposition of Nitroglycerin -Contaminated Air Streams

Assessment of Potential Environmental Risks of OpenBuming/Open Detonation of Propellants, Explosives, andPyrotechnics

Evaluation of Hydrazine Spill-Control Procedures Usin gMaterials Containing Copper (II) Oxide s

Separation of Nitrocellulose Fines by a Bench-Scale Fla tSheet Cross-Flow Microfiltration Unit

Detoxification of 2,4,6-Trinitrotoluene in a Liquid Phas e

Bioreacto r

Biotreatment of Explosives-Contaminated Soils in SlurryReactor s

Biodegradation of Nitrate Esters

Industrial Hygieneand Toxicology

Glove Screening for Protection from Specific Chemica lHazards

Respirator Cartridge Service Life Studies : I . Nitroglycerin

Vapor

Toxicity Evaluation of Alternative Lead-Free BallisticModifiers

Cadmium Exposures During the Refurbishment of SolidRocket Booster Component s

Compatibility Issues in the Manufacture of Slurry Explosive sfrom Recycled Gun Propellants

Going Bulk, Minimizing Hypergol Operations via th eGeneric Propellant Transfer Unit

Explosive Safetyand Hazards

Methodology for Metallized Cryogenic Gelled

Monopropellant Classification

HYKIN: A Computer Program for Relating Thermal an dPressure Hazards of Hydrazine Decompositions

Lessons Relearned from Recent Navy Explosive Mishap s

Flash Vaporization of Liquids into a Space-Like Vacuum

Hazards Evaluation of a Rusted M-2 Tool Steel Gear i nthe Shuttle Improved Auxiliary Power Unit

Hazardous MaterialsControl, Hazardou sWaste Management ,Waste Minimization

Development of Compact Waste Incinerators Based onAerospace Propulsion Technology

USBI Company Pollution Prevention Program Update

Extraction of Various Materials with Supercritical Carbo n

Dioxide

Hazardous Waste Minimization of Ordnance-Relate d

Waste StreamsPropellant Recycling

Demilitarization andReclamationTechnologies

Reformulation/Reuse of Explosives and Propellants fo r

Commercial Applications

Biodegradation of Ammonium Perchlorate Wastewate r

Solid Propellant Ingredient Reclamation and Reuse

Pyrotechnics Incineration

Removal of Lead and Copper from Double-Base Propellants

Supercritical Fluid Extraction of Depleted Stabilizers fro mSingle Base Propellant and Adding New Stabilizers

Munition Cryofracture Testing

Contained Thermal Treatment Uni t

Cryogenic Washout of Solid Rocket Propellant s

Resource Recovery System for Rocket Propellan t

Evaluation of Plasma Arc Pyrolysis for the Destruction o f

Thermal Batteries and Proximity Fuze s

Process Engineering Development for Rocket MotorDemilitarization and Ingredient Recovery

This table is a preliminary listing of sessions and papers to be presented, but it is subject to change . For the lates tinformation on sessions and papers, contact Camille T . Hudson (CPIA) at (410) 992-7305.


Page 1 1

DC-Xcontinued from page 1

RL10A-5 rocket engines, each of whichgenerates 13,500 lbf. The experimentalvehicle stands at 42 feet, has an emptyweight of over 22,000 lbs, and weigh s41,630 lbs when fully loaded with pro-pellants .

The DC-X' s hydraulic system con-sists of standard jet-liner, aircraft-typecomponents to drive the vehicle's fiveaerodynamic flaps and eight gimbal ac -tuators (two per engine) . Its aeroshel land base heat shield are made of graph-

ite epoxy composite, and the main pro-pellant tanks are 2219 aluminum . Thelanding gear is made of steel and tita-nium, and the main structural supportsare aluminum .continued on page 1 3

Defense Conversion and the Propulsion Industr yDr. William D. Stephens, Director of the Propulsion Directorate, U.S. Army Missile Command, Redstone Arsenal,

Alabama, and Chairman of the JANNAF Executive Committee, contributed his views for this editorial .

Many Government defense bureaucrats are busily en -gaged in efforts to implement the defense technology conver -sion policies of our new administration . The "beating o fswords into plowshares" is a process which we can envisio neasily with illustrations like the Soviet tank factory that isconverted to produce tractors and earth-moving equipment .But in the rocket and missile propulsion business, conversio nto a civilian product or nondefense application is much mor edifficult .

In a recent Army survey of the solid propellant industry ,the idea was developed that certain industries which are solelydependent upon markets within the DoD should be affordedsome degree of protection in order to maintain an industria lbase to support propulsion technology innovations . No on erecommends dismantling the entire U .S . industrial propulsionbase, for instance, but today's reality is that neither domesti cnor international socioeconomic conditions are what theywere just a few years ago . The post-World War II propulsionindustry must adjust to the end of the Cold War and enter th enew technological age, and not presume the right to a "goldenparachute . "

There is a tendency to view the conversion of militar yrocket and missile propulsion to civilian application as aconcept that is in the "too tough" pile . One possible reasonfor this is that most ofthe technology work is applied researc hand development, aimed towards a specific military endproduct . But couldn't certain propulsion-gained expertis ealso be applied to the civil transportation, energy conversion ,and environmental protection fields ?

If one starts mining the lode, it is possible to find severa lgems that fit the patterns for technology transfer or conver-sion . Because these finds are difficult to locate, there is atendency to abandon the process rather than to attempt to

influence it. But technology transfer neither fits into norprovides neat molds for entrepreneurs . Industry must activelyanticipate and enact innovative solutions to emerging employ -ment trends and technological frontiers . The opportunity toinfluence change towards a constructive, productive, an dbeneficial situation exists right now .

Under President Clinton's "Technology for America' sEconomic Growth" proposal, if companies decide to form amanufacturing R&D consortium, the SEMATECH/DoDmatching funds model will probably be the operative venue .One industry representative recently commented that hi scompany was unlikely to participate, since they could simplynot afford the ante . Well, there never was a free lunch, bu twhat's wrong with Dutch treat ?

Other less expensive or free opportunities do exist (seeside bar), and we would all do well to examine the possibili -ties in the current environment of restructure, reduction, andopportunity . Independent of Government funding sources ,the Administration also plans to reform antitrust laws t opermit more conglomerate pooling of resources, and th eresearch and experimentation tax credit will be made apermanent fact of life .

The Government offers the opportunity of tapping int otechnology networks, but the technology markets must still b ecreated by industry . Government can create neither supplynor demand, but it is fostering a business atmosphere tha tencourages cooperation and information sharing : technologytransfer. Working together, as our competitors abroad do, ca nonly bolster our technology preeminence and better prepare u sfor the workplaces of tomorrow. The products and marketsto be created are only limited by the creativity ofthe producer sand the fluidity of the marketplace . v

Page 12


The reusable Delta Clipper, featur-ing safe abort and return to Earth capa-bility, is designed to transfer people an dcargo to and from space in a rapidturnaround environment . This VTOL/SSTO launch vehicle will be powere dby eight rocket engines, and measure130 feet tall and 40 feet in diameteraround its base . Capable of boostin g20,000 lbs to low Earth eastward orbi tand 10,000 lbs to polar orbit, the Delta

Electrical line is installed at the bas eof the DC-X oxygen tank .

Clipper will also use LOX/LH2 as pro-pellants for its main engine .

McDonnell Douglas Aerospace i sthe prime contractor leading an assort-ment of subcontractors that helped turnout the DC-X in 18 months . The teamalso includes Douglas Aircraft Co ., Pratt& Whitney, Scaled Composites, Aeroje tPropulsion Div ., Allied Signal Aero-space Co ., Harris Corp., Honeywell ,Martin Marietta, Deutsche Aerospace ,Fluor Daniel, SpaceGuild, Chicag oBridge and Iron Services, General Con-nector, Integrated Systems, and Pro-cess Fabrication, Inc .v

The Pentagon's Advanced Research Projects Agency (ARPA) will re-double its efforts to encourage and fund the creation of dual-use technologie sthat will spin off new products (703-696-2444) .

Call to get a free copy of ARPA's "Program Information Package forDefense Technology Conversion, Reinvestment, and Transition Assistance "(1-800-DUAL-USE).

The NASA-sponsored National Technology Transfer Center (NTTC )links more than 700 federally funded labs to industry, as well as to the federal ,state, and local governments (1-800-678-NTTC ; marketing, 304-243-2456) .The NTTC is the umbrella for the six Regional Technology Transfer Centers(RTTCs), which provide access to federally sponsored technologies . RTTCstailor database searches and analyze corporate requirements and potentia lapplications of relevant technology (varying fees ; 202-358-0723) .

The Federal Laboratory Consortium for Technology Transfer (FLC )refers any inquirer to the relevant lab(s) according to subject-specific topic ,providing for person-to-expert contacts . The FLC also provides training ,develops and tests tech-transfer methods, and facilitates the process with it sLegal Networking Subcommittee . The FLC has six regional offices (free ; 206 -683-1005) .

Current Federal Programs

IAir Data Boor n

Deployable Nos eCa p

Aeroshel l

Parachut eCaniste r

Avionics Rac k

L0 2 Tank

Inter-tank

L0 2 Feed Line s

LH2 Tan k

Flap s

Thrust StructureLH2 Feed Lines

The Department of Commerce's (DoC) Advanced Technology Programwill expand and continue to contribute monies to selected industry initiative s(National Institute of Standards and Technology (NIST) ; industry shares costs :301-975-2636) .

DoC' s Manufacturing Technology Centers Program will be expanded t oall-size industries ; any company will be able to tap into readily adaptabletechnologies, training programs, and testing facilities (NIST ; may be a fee : 301 -975-5020) .

L

CPIA Bulletin/Vol. 19, No . 3, May 1993

Page 1 3

Configuration of the DC-X, courtesyof McDonnell Douglas Aerospace .

Penn State continued from page 1

Graduate student Harry Ryan explains to visitors how experiments usin gPERC 's high-pressure acoustic chamber relate to rocket engine combustio ninstability.

mining, communications, structures ,health monitoring, electronics, robot-ics, and propulsion. Penn State waschosen to be NASA's Space Engineer -ing Research Center in Space Propul-sion .

PERC is primarily housed in its ownlaboratory/office building; labs forlarge-scale or high-pressure experiment sare located remotely on the Penn Stat ecampus . Eighteen faculty members fromthe College of Engineering and the Col -lege of Science (Physics Department)are involved in the center . Overall, th efaculty work in groups and individuallyto direct research and mentor the disser -tation efforts of both our graduate an dundergraduate students .

The center has had a dramatic im-pact on the number and quality of U .S .students pursuing research and class -room studies in propulsion . About 7 5graduate and 25 undergraduate studentsare presently involved in space propul -sion research . The primary focus in th egraduate program is at the Ph .D . level,

where enrollments are predominantlyU .S. citizens . Undergraduates are in-volved in research projects both duringthe academic year and in a focusedsummer undergraduate program . Ahighly successful program to help inter-est minority undergraduate students inpropulsion is starting to impact enroll-ments in our graduate program. Centergraduates have done well in findingpropulsion-related positions in NASA ,industry, and academia, despite recen tlulls in related employment .

PERC's research program is de -signed to cover a spectrum of propul-sion issues to promote interdisciplinar ystudy and to provide a comprehensiv estudent educational program . It encom-passes both current propulsion system sand advanced propulsion concepts . Thespace propulsion focus includes liqui drocket engines, solid rocket motors ,hybrid engines, combined cycle propul -sion, electrothermal thrusters, and anti-matter propulsion . Most ofthe effort i sdevoted toward chemical space propul -sion . A strong complementary research

program in airbreathing and automo-tive propulsion also exists .

A specific research strength is com-bustion . The similarity of the funda-mental combustion issues in space ,airbreathing, and automotive propul-sion has provided strong synergism upo nwhich much ofPERC's success is built ,including computational and experimen -tal programs in sprays and spray com-bustion in both subcritical an dsupercritical regimes. Experimental labsare well equipped with state-of-the-ar tinstrumentation, and center researchersare leaders in applying advance dnonintrusive optical and X-ray diag-nostic techniques to combustion prob-lems. A strong supporting effort incomputational fluid dynamics (CFD)modeling of steady and unsteady react -ing flows complements the experimen-tal work . CFD capabilities are en-hanced by the center's network of 2 0RISC workstations that are used asstand-alone systems, as entries for na-tional supercomputer access, and forimplementing distributed parallel algo -rithms for large problems .

A major research capability that wascreated as part of the NASA SERCeffort is the Cryogenic Research Labo -ratory . This unique lab was develope dto enable fundamental experimental re -search under realistic conditions withcryogenic propellants such as liquidoxygen and hydrogen (LOX/H2) . Amajor emphasis at the Cryogenic Lab i sthe development and application of ad-vanced diagnostic techniques that canbe used in hostile environments likerocket thrust chambers. Other experi-mental facilities co-located with theCryogenic Lab foster solid propellan tand hybrid rocket studies at realisticconditions .

Active research projects in materi-als compatibility and turbomachinery

Page 14


are also underway at PERC . Of par-ticular interest is the development o flaminar barriers for reducing wall tem-perature and hydrogen permeation intothe structural material . Turbomachineryefforts include projects in foil bearingsand electromagnetic bearings encom-passing both experimental and analyti-cal facets aimed at improving the capa-bilities ofthese noncontact bearings fo rrocket engine turbomachinery applica-tions . Other significant turbomachineryefforts include application ofCFD tech-niques to the aero/hydro aspects ofturbomachinery, and development ofadvanced turbulence models forturbomachinery flow paths . These ef-forts are enhanced by other major re-search programs in materials andturbomachinery at Penn State that ar enot part of the center .

The research on current propulsionsystems is balanced by projects in elec-trothermal and nuclear thermal propul-sion, combined cycle propulsion, and

inertial confinement fusion (ICF) pro-pulsion . ICF is a magnetically directedplasma propulsion concept driven byuranium-hydrogen pellet microex-plosions, and is a potential answer to th ehigh thrust and high specific impulserequirements of interplanetary manne dspaceflight . Center researchers areworking to demonstrate ignition of th euranium-hydrogen pellet by antiproton-induced fission . The primary objectiveof this work is to determine the appro-priate antiproton beam energy and em it -tance for penetration into the dens eplasma and subsequent antiproton an-nihilation on the surface of the com-pressed target . Proof-of-principle ex-periments planned at the SHIVA Sta rfacility at the Phillips Laboratory(Kirtland AFB, New Mexico) coul dlead to a program of full target experi-ments with direct applications to pro-pulsion needs .

The newest PERC program ad-dresses fundamental combustion and

flow processes in hybrid rocket engines .Expertise in solid and liquid rockets i scombined in this detailed experiment onLOX/hybrid fuel combustion processes .Companion CFD analyses are beingconducted to assess scale-up issues us-ing lab-scale data obtained here as wel las intermediate-scale data gaine dthrough industry testing .

A primary objective of the center i sto effectively transfer research result sto the propulsion community throug hboth formal and informal interactions .The broad research program attractsmany welcome visitors from the propul-sion industry . Recently, PERC hoste dthe First International Symposium o nLiquid Rocket Combustion Instability ,with over 60 participants from ten coun -tries . Especially noteworthy were pre-sentations by people from the forme rSoviet Union and also China that pro-vided detailed technical informatio nnever publicly received in the U .S . Visi -tors are especially invited to participatein PERC' s Fifth Annual Symposium o n8-9 September, which will highlight th ecenter's research, students, and labs . Alist of expected graduates and their spe-cific areas of interest and expertise canbe obtained upon request .

CPIA will occasionally feature ar-ticles on federally funded, university-operated propulsion laboratories, an dwe hope that our readers will takeadvantage ofand/or contribute to thes efacilities . This article was submittedby Dr. Charles L. Merkle, Director,and Mr. Bill Anderson, Assistant Di-rector, of the Propulsion EngineeringResearch Center at The PennsylvaniaState University (814-863-6272) . Ad-ditional information is available fro mProfessor Merkle at 104 ResearchBuilding East, The Pennsylvania StateUniversity, University Park, P A16802 . v

This windowed research combustor is used in LOX/H 2 coaxial injector tests atthe Cryogenic Lab . Measurements are taken to validate CFD-based designanalysis codes .

CPIA Bulletin/Vol . 19, No. 3, May 1993

Page 15

JANNAF MEETING CALENDA R

1993 Meeting Type Location Sec. ClassAbstract/Paper

Deadline

10-14 May JANNAF Propulsion Systems Conference/ Fort Lewis, WA Unclassified/ Past PastHazards Subcommittee Meeting Workshops Limited

9-13 Aug JANNAF Safety & Environmental Conference/ WSTF, Las Unclassified/ Past 26 Ju l

18-22 Oct

Protection Subcommittee Meetin g

JANNAF Rocket Nozzle

Workshop s

Conference/

Cruces, NM

MICOM,

Limited

Unclassified/ 10 May 4 Oct

18-22 Oct

Technology Subcommittee Meeting

JANNAF Structures & Mechanical

Workshop s

Conference/

Huntsville, AL

MICOM,

Limited

Unclassified/ 10 May 4 Oct

15-18 Nov

Behavior Subcommittee Meetin g

JANNAF Propulsion Meeting

Workshop s

Conference/

Huntsville, AL

Hyatt Hotel &

Limited

Confidential/ 15 Feb 18 Oct

15-19 Nov JANNAF Combustion

SpecialistSessions

Conference/

NPS, Monterey,CA

NPS, Monterey,

Limited

Confidential/ 24 May 25 OctSubcommittee Meeting Workshops CA Limited &

Unlimited

Attendance at JANNAF Conferences and Workshops is by invitation only .

MEETING CALENDAR SUBJECT TO CHANGE . FOR LATEST DETAILS, CONTACT CPIA at (410) 992-7303 .

Printed on recycled paper.

Cp

CHEMICAL PROPULSIONBulle tin INFORMATION AGENC Y

AThe Johns Hopkins University10630 Little Patuxent Parkway, Ste . 202, Columbia, MD 21044-3200

ADDRESS CORRECTION REQUESTED

Time Dated Material

U. S. POSTAGE

PAIDCOLUMBIA, MARYLAND

PERMIT No. 425NONPROFIT ORGANIZATION

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