A DoD Information Analysis Center Sponsored by JANNAF and DTIC Vol. 35, No. 3 News and Information for the Greater Propulsion Community May 2009 PPrrooppuullssiioonn RReesseeaarrcchh AAccttiivviittiieess AAbboouunndd aatt AAuubbuurrnn UUnniivveerrssiittyy By Dr. Winfred A. “Butch” Foster, Dr. Roy Hartfi eld, and Dr. Brian Thurow Auburn University, Auburn, Alabama AA uburn University’s Aerospace Engineering Depart- of Richard Sforzini, a Morton Thiokol solid rocket motor ment is the site of many activities related to the pro- specialist, that marked the beginning of a major emphasis pulsion of aerospace vehicles. The study of propul- on propulsion, both in the academic curriculum and as a sion systems at Auburn began with the creation of the aero- major research topic. In 1967, two new rocket propulsion nautics curriculum for the 1931-1932 academic year, and the courses covering liquid propellant rockets and solid propel- fi rst graduates fi nished the program in 1933. Instruction and lant rockets were introduced into the undergraduate curricu- research associated with aircraft and rocket propulsion have lum as electives. Both courses provided a foundation for the been an integral part of what is now Aerospace Engineer- preliminary design and performance analysis of rocket mo- ing. While coursework related to propulsion had been in the tors. In the early 1970s, because of the intended use of solid curriculum since its inception in 1933 and specifi c courses rocket motor boosters on the Space Shuttle, NASA’s Mar- dealing with air breathing and rocket propulsion had also shall Space Flight Center (NASA/MSFC) needed to provide been added over a period of years, it was the 1966 arrival training in the area of solid rocket motors to engineers whose continued on page 4 PPuurrdduuee UUnniivveerrssiittyy PPrroommootteess PPrrooppuullssiioonn Inside This Issue EEdduuccaattiioonn aanndd RReesseeaarrcchh tthhrroouugghh UUnniiqquuee JANNAF Subcommittees to Convene in La Jolla, CA ..........................................3 TTeessttiinngg FFaacciilliittiieess Johns Hopkins University Sponsors 6th Annual Physics Fair..............................9 By Dr. Steven F. Son, Purdue University, West Lafayette, Indiana CU-Boulder Develops Drag and Atmo- PP spheric Neutral Density Explorer .....10 urdue University has a long tradition in propulsion research, and its unique JANNAF Meets in Las Vegas..............12 facilities enable hands-on education in combustion and aerospace sciences. A signifi cant part of propulsion testing facilities at Purdue are located at a JANNAF Journal Vol. 3, Call for Papers...16 Two Successful Motor Test Firings in remote location, away from the main part of campus, on a 24-acre site adjacent Support of IHPRPT............................17 to the Purdue University Airport. Rocket propulsion testing at Purdue began in In Memoriam 1948, under the direction of Dr. Maurice Zucrow. The Advanced Propellants and Frederick A. Boorady, Dr. Russell Reed, Combustion Laboratory (APCL) houses two control rooms and three test cells Jr., and Dr. Ralph Roberts.................18 (Cells A, B, and C) for propulsion testing, fuel coking studies, and propellant NASA Stennis Space Center Focuses on development. Another rocket test cell (Cell T) is now operational in the Propulsion Helium Conservation........................19 Laboratory. Test fi rings are conducted and observed from the control rooms. In Spotlight on SBIRs/SBTTs addition, there are several small-scale experimental labs throughout the Zucrow CSE Develops Optimization Tool for complex. Scramjet Applications........................20 continued on page 6 Rocket Test Group at NASA WSTF.......23 1st NCRES Held in So. Maryland......23 JANNAF Propulsion Meeting & Joint Subcommittee Technical/Bibliographic Inquiries...............2 Meeting held in Las Vegas – See page 12 Bulletin Board/Mtg.Reminders..................3 JANNAF Meeting Calendar...............back CPIAC’s Technical/Bibliographic Inquiry Service CPIAC offers a variety of services to its subscribers, including responses to technical/bibliographic inquiries. Answers are usually provided within three working days and take the form of telephoned, telefaxed, electronic, or written technical summaries. Customers are provided with copies of JANNAF papers, excerpts from technical reports, bibliographies of pertinent literature, names of The Chemical Propulsion Information Analysis recognized experts, propellant/ingredient data sheets, computer programs, and/ Center (CPIAC), a DoD Information Analysis or theoretical performance calculations. The CPIAC staff responds to nearly 800 Center, is sponsored and administratively managed by the Defense Technical Information inquiries per year from over 180 customer organizations. CPIAC invites inqui- Center (DTIC). CPIAC is responsible for ries via telephone, fax, e-mail, or letter. For further information, please contact the acquisition, compilation, analysis, and dissemination of information and data relevant Ron Fry by e-mail to [email protected]. Representative recent inquiries include: to chemical, electric, and nuclear propulsion technology. In addition, CPIAC provides technical and administrative support to the TECHNICAL INQUIRIES Joint Army-Navy-NASA-Air Force (JANNAF) Interagency Propulsion Committee. The (cid:129) Synthesis of Trimethylolmethane Trinitrate (TMMTN) (Req. 26342) purpose of JANNAF is to solve propulsion problems, affect coordination of technical programs, and promote an exchange of (cid:129) Asbestos Content in Patriot Rocket Motor Insulation (Req. 26345) technical information in the areas of missile, space, and gun propulsion technology. A fee commensurate with CPIAC products and (cid:129) SRM Canted Nozzle Mechanism Design (Req. 26346) services is charged to subscribers, who must meet security and need-to-know requirements. (cid:129) Commercial Leak Detection Systems for Hypergolic Propellants (Req. The Bulletin is published bimonthly and is 26352) available free of charge to the propulsion community. Reproduction of Bulletin articles is permissible, with attribution. Neither the (cid:129) Small SRM Manufacturers in Northeast US (Req. 26380) U.S. Government, CPIAC, nor any person acting on their behalf, assumes any liability (cid:129) Current Environmental Ruling on the use of Ammonium Perchlorate resulting from the use or publication of the information contained in this document, (AP) (Req. 26379) or warrants that such use or publication of the information contained in this document will be free from privately owned rights. BIBLIOGRAPHIC INQUIRIES The content of the Bulletin is approved for public release, and distribution is unlimited. (cid:129) CPIA-LS79-6, "Underwater Vehicle Propellants," by Theodore Gilliland Paid commercial advertisements published in (Req. 26298) the Bulletin do not represent any endorsement by CPIAC. (cid:129) Understanding Flow Blockages in Small Thrusters, 1980 JANNAF Propul- Editor: Rosemary Dodds 410-992-1905, ext. 219; Fax 410-730-4969 sion Meeting (Req. 26358) E-mail: [email protected] Copy editor: Kelly Bennett (cid:129) DB Propellant Properties, DB Propellant Gassing and Composite Propellant The Johns Hopkins University/CPIAC Gassing (Req. 26360) 10630 Little Patuxent Parkway, Suite 202 Columbia, Maryland 21044-3286 CPIAC Director: Dr. Edmund K. S. Liu CPIAC is a JANNAF- and DTIC-sponsored DOD Information Analysis Center operated by The Johns Hopkins University Recent CPIAC Products and Publications Whiting School of Engineering under contract W91QUZ-05-D-0003 http://www.cpiac.jhu.edu JANNAF Journal of Propulsion and Energetics, Copyright © 2009 The Johns Hopkins University Volume II, April 2009. No copyright is claimed in works of the U.S. Government. Page 2 CPIAC Bulletin/Vol. 35, No.3, May 2009 JANNAF The Bulletin Board 43rd Combustion/ 31st Airbreathing Propulsion/ Various propulsion-related meetings are listed below. If you know of an event 25th Propulsion Systems Hazards that may be of interest to the propulsion community, please forward the details to [email protected]. Additional industry meetings are posted on the Joint Subcommittee Meeting CPIAC Web site, Meetings & Symposia: http://www.cpia.jhu.edu/templates/ December 7-11, 2009 cpiacTemplate/meetings/. The JANNAF Calendar appears on the back page. La Jolla, CA Fundamentals of Explosives The Joint Army-Navy-NASA-Air 5-7 May 2009 Force (JANNAF) 43rd Combustion/31st University of Rhode Island, Kingston, Rhode Island Airbreathing Propulsion/25th Propulsion POC: Dr. Jimmie Oxley, 401-874-210 or e-mail: [email protected] Systems Hazards Joint Subcommittee Meeting will be held December 7-11, 2009 Insensitive Munitions and Energetic Materials Technology 2009 in La Jolla, California. Unclassifi ed Symposium sessions will be conducted at the Hyatt 11-14 May 2009 Regency La Jolla; classifi ed sessions will Tucson, Arizona be held at the Naval Fleet Intelligence POC: www.ndia.org Training Center in San Diego. CPIAC distributed the meeting an- Sixth Mediterranean Combustion Symposium nouncement and call for papers in March. 7-11 June 2009 Abstracts are due May 25; proposals for Porticcio-Ajaccio, Corsica, France workshops are due June 8. The Hyatt Regency La Jolla at Aven- POC: www.ichmt.org/mcs-09/ tine is a luxury hotel located within walking distance of a variety of restau- 40th ICT Annual Conference rants and shopping, and within a 10-min- 23-26 June 2009 ute drive to beautiful beaches, the Birch Karlsruhe, Germany Aquarium, and the Torrey Pines golf POC: www.ict.fhg.de course. Visit the hotel’s Web site for a full description of available amenities: 45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit www.lajolla.hyatt.com. Room rates for 2-5 August 2009 this JANNAF meeting are $139 for gov- Denver, Colorado ernment and $209 for industry attendees. POC: www.aiaa.org Attendance at this JANNAF meeting is restricted to U.S. citizens whose orga- 7th International Workshop on Structural Health Monitoring 2009 nizations are registered with an appro- 9-11 September 2009 priately classifi ed contract with the De- Stanford University, Stanford, CA fense Technical Information Center and POC: http://young-sacl.stanford.edu/member.php certifi ed for receipt of export-controlled technical data with the Defense Logistics 2009 International Autumn Seminar on Propellants, Explosives and Information Service. Propellants Please contact Patricia Szybist at [email protected] or 410-992-7302, ext. 215, 22-25 September 2009 if you require additional information, or Kunming, Yunnan, China if you did not receive the meeting an- POC: http://www.iaspep.com.cn nouncement and call for papers. 6th International Symposium on Beamed Energy Propulsion 1-5 November 2009 Scottsdale, Arizona POC: http://aibep.org/ISBEP_6/ISBEP_6.htm 8th International Symposium on Special Topics in Chemical Propulsion 2-6 November 2009 Cape Town, South Africa POC: Prof. Ken Kuo at [email protected], or call (1-814) 863-6270 Poolside at the Hyatt Regency La Jolla CPIAC Bulletin/Vol. 35, No. 3, May 2009 Page 3 AAuubbuurrnn UUnniivveerrssiittyy....continued from page 1 background had historically been lim- MSFC for a computer code that could aluminum particles to seed the fl ow. ited to liquid propellant rocket engines. be used on relatively small computers, Igniters with both single- and multiple- NASA MSFC chose to use an expanded which would be able to match results port confi gurations were evaluated. A version of the solid rocket motor course from more sophisticated internal bal- subset of these experiments included being taught at Auburn for this training listics codes to within 5% for such an effort to evaluate plume interactions program, and it was taught onsite on variables as thrust, specifi c impulse, for multi-port igniters. The model used two occasions. Additional and expand- total impulse, etc. A so-called simpli- for the slots along with the igniter mod- ed graduate courses in propulsion were fi ed internal ballistics computer code els tested for the ASRM are shown in introduced beginning in the late 1960s. was developed to meet these objec- Fig. 1. The vast majority of research at Au- tives. In fact, this code was accurate burn in the area of rocket propulsion has to within 3% in general and to within been related to performance prediction, 1% for certain parameters. It formed preliminary design, and optimization of the basis for much of the work done solid rocket motors. The modeling and at Auburn over the next 15 years. This optimization effort has been supple- work included a Monte Carlo thrust mented by experimental investigations imbalance prediction code which uti- in facilities on campus and at NASA/ lized 41 variables for the Space Shut- MSFC. Liquid rocket and air breath- tle solid rocket boosters. The simpli- ing propulsion research has included fi ed code also served as the basis for preliminary design and optimization the development of design and design of ramjet and scramjet combustors and optimization codes based on a pattern ramjet- and scramjet-powered vehicles, search technique for solid rocket mo- Figure 1. Model used for the slots and nonintrusive, instream measurements tor preliminary design. Other uses of igniter models tested for the ASRM. of critical fl ow parameters in nonreact- the simplifi ed code include studies of ing combustor geometries, and the on- off-design performance and reverse Scramjet Combustor Design going development of advanced mea- engineering analyses to evaluate mo- surement diagnostic techniques. tor characteristics based on fl ight or The study of fuel-air mixing in a The research areas at Auburn are var- test data. An expanded version of the supersonic cross-fl ow has been inves- ied and cover many of the major areas simplifi ed internal ballistics code, the tigated extensively as a test case for a of interest associated with both rocket Solid Rocket Motor Multiple Options scramjet combustor geometry. With and air breathing propulsion. Several Program, included the capability to the development of computing tech- of the individual research activities at account for propellant grain deforma- nology, it is possible to develop opti- Auburn are described in the following tion effects, circumferential grain tem- mized preliminary designs for scramjet sections. perature distributions, and the effects combustors using a computational fl uid of circular perforated grain ovality dynamics (CFD) solver and a Genetic Solid Rocket Motor Performance and centerline misalignment. These Algorithm (GA). Experimental results and Design last two effects are not known to be from research conducted in the 1990s Solid rocket motor research activi- accounted for in any other internal have been used for the validation of the ties at Auburn University have been ballistics code today. On two occa- CFD solutions. The experiments were ongoing for the last forty years. This sions, experimental efforts have been highly focused on developing accurate research has been primarily directed conducted at NASA/MSFC to obtain data sets for a single-case fl ow situa- at the development of analytical tools a better understanding of the fl ow fi eld tion. This effort builds on this single for solid rocket motor internal ballistic induced by an igniter in the head-end validated case by considering geomet- analysis, optimization of solid rocket star grain slots. This work included ric variations of the combustor design, motor powered missiles, and struc- the design and fabrication of 1/10th- solving for the fl ow, and arriving at a tural analysis of solid rocket motor scale models for the reusable solid geometry which is optimized for mix- hardware. One of the earliest major rocket motor (RSRM) and advanced ing effi ciency with minimum total efforts began in the early 1970s to sup- solid rocket motor (ASRM) head-end pressure loss under the direction of a port NASA/MSFC efforts to evaluate star grains. Measurements included GA. Sample results for the validation the internal ballistic performance of oil smear data, pressure data, heat case are shown in Fig. 2. the Space Shuttle’s solid rocket motor transfer, laser doppler velocimetry boosters. There was a need at NASA/ data, and fl ow visualization data, using continued on page 5 Page 4 CPIAC Bulletin/Vol. 35, No.3, May 2009 AAuubbuurrnn UUnniivveerrssiittyy....continued from page 4 Figure 3. Optimized solid boosted ramjet missile system (left) and an aerodynamically enhanced launch vehicle (right). Figure 2. Sample results for the validation case. Rocket and Ramjet Propelled Vehicle Design Recent vehicle design optimization efforts have focused on multiple-stage solid propellant vehicles, single- and mul- tiple-stage liquid propellant vehicles, solid motor boosted ramjets, and solid motor boosted scramjets. Successful dem- onstrations of a two-stage all-solid propellant-kinetic weapon system and a solid motor-boosted air breathing vehicle have supported the U.S. Army’s mission to develop advanced weapon systems. A substantial program to develop solid propellant-fueled launch vehicles has resulted in an optimized version of the minotaur launch vehicle and vehicles that include enhanced perfor- mance using aerodynamic lifting during early fl ight. During this effort, the performance of the basic wingless vehicle was found to be enhanced by varying the geometric defi nition of the attached wing structure and the internal propellant. Initial system weights and propellant mass fractions were found to decrease for a given payload even with the addition of the wing structure. Figure 3 shows representations of an optimized solid boosted ramjet missile system and an aerodynamically enhanced launch vehicle. Diagnostic Technique Development for Propulsion Flows Recently, researchers at Auburn have been developing high-speed advanced laser diagnostics suitable for measurements in high-speed and/ or reacting propulsion-related fl ows. The centerpiece of this development is a home-built pulse-burst laser system capable of producing high energy Figure 4. 3-D imaging technique used to visualize (>10 mJ/pulse) laser pulses at repetition rates exceeding 1 MHz and fl ow of a turbulent jet. wavelengths ranging from 266 nm to 1064 nm. Used in conjunction with a high-speed camera capable of 500,000 fps, the laser can be used to take high-speed fl ow measurements using techniques such as planar laser-induced fl uorescence to simple fl ow visualization. Perhaps the most unique application of the system, however, has been for the acquisition of 3-D fl ow images. For 3-D imaging, a galvanometric scanning mirror is used to scan the high-repetition laser sheet through the fl ow fi eld with a high-speed camera recording the image at each scan location. A 3-D image can then be reconstructed from the stack of 2-D images. The overall acquisition process can be completed in tens of microseconds. An example of the technique used to visualize the fl ow of a turbulent jet is shown in Fig. 4. For additional information on propulsion research and activities at Auburn University, visit the Aerospace Engineering Department’s Web site: http://eng.auburn.edu//programs/aero/. CPIAC Bulletin/Vol. 35, No. 3, May 2009 Page 5 PPuurrdduuee UUnniivveerrssiittyy....continued from page 1 Gelled Propellant Lab (GPL) access, and a top window of one of the vessels is confi gured The GPL is Purdue’s newest propulsion laboratory being for the use of a Zinc Selenide (ZnSe) top window that al- developed in support of an Army Research Offi ce (ARO) lows ignition studies using a CO laser. High-speed digital Multidisciplinary University Research Initiative (MURI) 2 microscopic imaging and visible/IR spectroscopy are used program on spray and combustion of gelled hypergolic in combustion studies. Electostatic discharge (ESD) and propellants, which was awarded last year to Purdue and its impact testing is used to quantify sensitivity of new propel- partners. The GPL houses a control room and a laboratory lants. Material ball milling, cutting, and polishing, along space dedicated to small-scale testing with hypergolic with microscopy, are also available for sample character- propellants such as NTO, IRFNA, and hydrazine-based ization. An environmentally controlled glovebox is used to fuels. The versatility of the mechanical and data acquisition keep nanometals pristine. A light gas gun, explosive blast systems as well as the dedicated air ventilation and chambers, and initiator testing facilities are also currently monitoring systems installed at GPL make this laboratory used. Purdue also maintains active Class 1.1 and 1.3 bun- particularly well-suited for testing of hypergolic systems and kers for remote storage of energetic materials as part of the fi re/vapor suppressant systems, as well as other small-scale Zucrow Laboratory complex. Many other small-scale labo- experimental activities. ratory research projects are also located at Zucrow Labs, in- LOX-LCH Facility cluding hydrogen storage, combustion, spray dynamics, and 4 The LOX-LCH facility is being developed to provide a fl uid dynamics. 4 known-temperature liquid cryogenic fl uid to a test article. High Pressure Lab (HPL) Standard gaseous oxygen and methane cylinders are used Originally constructed in the mid-1960s in support of the to supply pressurized gases into cyrogenic chilling tanks Apollo program, HPL provides the most substantial capa- to produce and store liquid propellants for test operation. bilities for rocket and airbreathing combustion and nozzle Each system can be independently temperature-controlled studies with two large test cells classed to 10,000 lbf thrust with a goal to deliver specifi ed temperature propellants to levels. A 6000 psi nitrogen system serves for pressurizing the test hardware. The facility is designed to test small- facility tanks, and 5000 psi liquid oxygen, gaseous hydro- scale thrusters and ignition work in addition to fundamental gen, kerosene, hydrogen peroxide, and cooling water capa- instability research of LOX-LCH . bilities exist to the 10,000 lbf thrust level. A gas-fi red heat 4 Solid Propellant Mixing and Combustion Lab exchanger provides airfl ows heated to 1000Ο F at fl owrates Purdue’s solid propellant mixing facility utilizes a Ross on the order of 10 lb/s to simulate airbreathing combustor model DPM-1 Quart double planetary mixer that has a mix- inlet conditions, and roughly 5 tons of high-pressure air ing range of ½ pint to 1 quart with stirrer speeds of 22-98 storage is available from the lab air system. There are also rpm with cooling or heating control, and vacuum to about several unique large-scale testing facilities at Zucrow Labs. 0.5 psia. The Ross mixer can be operated remotely from a Pulse denotation and high-pressure gas turbine combustor control room. The facility includes two windowed pressure test rigs are currently in place at HPL. The airbreathing com- vessels (Crawford bombs) for combustion studies of propel- bustor rig provides optical access for diagnostic access to the lants and energetic materials. Pressures up to 6000 psi can combustor. The HPL Annex is the newest building within be considered. Sapphire windows allow access to infrared the HPL complex. This 1400-sq ft structure provides large continued on page 7 Figure 1. Hydrocarbon fi lm cooling test on 10 klbf thrust stand at Purdue High Pressure Laboratory (left). On the right, is a fi tted heat fl ux measurement for a HO combustor. Different lines within each pressure grouping refer to measurements at different azimuthal locations. Page 6 CPIAC Bulletin/Vol. 35, No.3, May 2009 PPuurrdduuee UUnniivveerrssiittyy....continued from page 6 fl ow capabilities for airbreathing combustion and nozzle ex- lbf thrust stand in the High Pressure Lab (shown in Fig. 1) periments (see Ref. 1 for details). during a liquid hydrocarbon fi lm cooling test conducted for In the past decade or so there has been a reinvigoration of the Air Force Research Laboratory (AFRL) and its SBIR the facilities and increase in personnel at Purdue directing contractor, Sierra Engineering. Axially- and circumferen- efforts in propulsion, as well as in related areas of energy tially-resolved heat fl ux measurements in a seven-element and combustion. Additional details about the facilities can HO combustor at 1000 psia are also shown in Fig. 1; mea- be found at https://engineering.purdue.edu/AAE/Research/ surements like these are being used by NASA to learn how ResearchFacilities/LabFacilities, https://engineering.purdue. to accurately compute the 3-D reacting fl owfi eld inside high- edu/Zucrow/index.html and in Refs. 2 and 3. pressure rocket combustors. Current Research Topics A major effort to develop a methodology for a priori pre- diction of liquid rocket combustion instability comprises a Research pertaining to propulsion is inherently multidis- hierarchy of analysis, experiments, and computations. ciplinary and therefore includes elements from numerous or- Experiments using an unstable model rocket combustor ganizations within the Schools of Engineering and Science are used to validate the high-fi delity (e.g., LES) computa- at Purdue University. More than a dozen professors, specifi - tions, and those results are used to derive reduced-order cally within the Schools of Mechanical Engineering (ME) combustion response models for use in engineering-level and Aeronautics and Astronautics (AAE), are involved with models for stability prediction. This work is being conducted propulsion research at Purdue. This faculty advises over 75 for AFRL, AFOSR, and its subcontractor, INSpace. Studies graduate students and postdocs in the AAE and ME depart- to examine the combustion stability of LOX/LCH engines ments with annual research expenditures in the $5 million/ 4 for NASA lunar missions are also underway. year range. The faculty and students are supported by sever- Most recently, Purdue was awarded a MURI from ARO al staff members, including a Senior Engineer and a Techni- for a comprehensive study of gelled propellants. The pro- cal Services Supervisor. Recently, testing and collaborative gram includes the development of models for gel rheology research programs have been conducted with funding from and internal fl ow, as well as studies of spray formation, hy- Rolls Royce Allison, Aerojet, Pratt & Whitney, Northrop pergolic ignition, and drop burning of the gelled propellant. Grumman Space Technologies, Precision Combustion Inc., The culmination of this program is the integration of these General Kinetics, ATK, NASA Marshall Space Flight Cen- results into a time-accurate computational model of rocket ter (MSFC), Stennis Space Center (SSC), Dryden Flight Re- combustor processes, ranging from fl ow into the injector ele- search Center (DFRC), and Glenn Research Center (GRC), ments to combustion product fl ow out the nozzle, that is vali- Orbital Sciences Corporation, Air Force Offi ce of Scientifi c dated by a benchmark experiment conducted at the Gelled Research (AFOSR), Army Research Offi ce (ARO), Offi ce Propellant Laboratory. of Naval Research (ONR), Naval Research Offi ce (NRO), Missile Defense Agency (MDA), Ensign-Bickford Aero- Solid Propellants and Energetic Materials space and Defense Company (EBA&D), Defense Advanced Although solid propellant studies are not new to Purdue, Research Projects Agency (DARPA), and others. Liquid/ there has been a recent increase in solid propellant research. gelled, solid propellant, and airbreathing propulsion are all Currently, there are seven graduate students working in this being studied. area. With the development of propellant mixing, combus- Additional information about the faculty and staff is tion, and characterization capabilities, researchers can now available on the following Web sites: https://engineering. systematically develop and study new solid propellants, as purdue.edu/Zucrow/People/faculty.html; https://engineering. well as produce standard propellants for testing. Some cur- purdue.edu/AAE/Research/ByProfessor/Propulsion; and rent projects that have been funded include a study of erosive https://engineering.purdue.edu/Zucrow/People/index.html. burning (NASA); development and characterization of a new Liquid and Gelled Propulsion propellant binder system (MDA); high burning rate propel- lants (EBA&D); dynamic combustion of nano-aluminized Research in liquid rocket propulsion includes studies of propellants (AFOSR-STTR); development and testing of the ignition and chemical kinetics of hypergolic propellants; advanced propellants, including Al-ice (ALICE) propellants gelled propellants; development of a combined analytical- (AFOSR/NASA); and aluminum droplet dynamics in realis- experimental-computational testbed for combustion instabil- tic environments (AFOSR-STTR). Related research topics ity; and detailed computations of the hydrodynamics inside on energetic materials, including nanoscale composite en- injector elements, rocket-based combined-cycle engines, ergetic materials, are actively pursued in laboratories in the and measurement of heat fl ux in a few-thousand lbf thrust Propulsion and Combustion Buildings. multi-element oxygen-hydrogen combustor. Large-scale rocket studies are conducted on the 10,000 continued on page 8 CPIAC Bulletin/Vol. 35, No. 3, May 2009 Page 7 PPuurrdduuee UUnniivveerrssiittyy....continued from page 7 Figure 2. 3-D Fan Performance CFD Analysis Conducted for a Supersonic Business Jet Flowfi eld (left). On the right is an image from Purdue’s compressor research facility aimed at investigating tip leakage effects on the last stage of a highly loaded Rolls-Royce outlet guide vane and pre-diffuser confi guration. Airbreathing Propulsion pressor followed by a pre-diffuser and combustor plenum The propulsion group at Purdue University maintains a features a highly loaded outlet guide vane and adjustable ro- substantial research effort in airbreathing propulsion. Pur- tor tip clearance rings. The third test cell is dedicated to due also maintains the nation’s only Rolls-Royce University investigating techniques to mitigate forced response issues Technology Center (UTC) in the area of high Mach propul- in a 3-stage compressor designed by GE-Energy. sion. Ongoing UTC work involves the study of high tem- Of course, the most important product of Purdue’s propul- perature fuel systems and fuel coolant confi gurations to pro- sion program is its well-educated and trained student body. vide turbine cooling air for high Mach applications. Studies Purdue is one of the few schools to offer propulsion as a ma- in coking of JP fuels, endothermic potential of JP-10, fuel/ jor fi eld of study and courses in airbreathing and rocket pro- air heat exchangers, fuel system thermoacoustic instabilities, pulsion at both the undergraduate and graduate level. These and injection and mixing of supercritical fuels are currently unique educational opportunities provide Purdue graduates underway within the UTC. In addition, a large group within with the tools necessary for advancing the propulsion state the UTC is studying inlet and exhaust systems for supersonic of the art as professional engineers. Recognition of Purdue’s business jet applications with Rolls-Royce and partner Gulf- position and impact on the fi eld of propulsion was evidenced stream Aerospace Corp. Computational studies (Fig. 2) are last year when the University topped the Aviation Week list being conducted on both inlet and exhaust system concepts, of preferred institutions from which the aerospace and de- and advanced confi gurations are being studied to enhance fense industry recruits. propulsion system performance and to minimize noise. A References substantial test facility (BiAnnular Nozzle Rig, or BANR) 1Matsutomi, Y., Hein, C., Chenzhou, L., Meyer, S.E., Merk- has been developed for this project to support hotfi re testing le, C., and Heister, S. D., “Facility Development for Testing of turbofan nozzle confi gurations. The BANR can simulate of Wave Rotor Combustion Rig,” AIAA-2007-5052, 43rd turbine and fan exit conditions to nozzle pressure ratios of 6 AIAA/ASME/SAE/ASEE Joint Propulsion Conference and with overall fl ows of 30-50 lb/s. Exhibit, Cincinnati, OH, July 8-11, 2007. Experimental facilities are also available for studying tur- 2Pourpoint, T.L., Meyer, S.E., Ehresman, C.M., “Propulsion bomachinery fl ows. A unique high-speed rotating compres- Test Facilities at the Purdue University Maurice J. Zucrow sor research facility has received recent driveline upgrades, Laboratories,” AIAA 2007-5333, 43rd Joint Propulsion including 1400 hp motors controlled with variable frequency Conference, July 2007. drives for each of the three high-speed test cells. Current 3Heister, S. D. et al., “Propulsion Educational and Research research efforts are investigating fl ow through a high-per- Programs at Purdue University,”AIAA 2007-, 43rd Joint formance Rolls-Royce centrifugal compressor assembly. A Propulsion Conference, July 2007. gearbox featuring a gear ratio of 30:1 provides the required 52,000 rpm shaft speed. Axial compressor research is aimed at investigating rear core performance issues, including ef- forts to desensitize tip leakage fl ows from the relatively high clearances experienced in the geometrically small stages in the rear of the core. The last stage of a Rolls-Royce com- Page 8 CPIAC Bulletin/Vol. 35, No.3, May 2009 TThhee JJoohhnnss HHooppkkiinnss UUnniivveerrssiittyy SSppoonnssoorrss 66tthh AAnnnnuuaall PPhhyyssiiccss FFaaiirr!! CPIAC Joins in the Outreach Effort for Next Generation Scientists T he Henry A. Rowland Department of Physics and Astronomy at The Johns Hopkins University sponsored its 6th Annual Physics Fair on Saturday, April 25, 2009, from 11:00 am until 5:30 pm. The fair featured a Balloon Rocket Contest and more than 200 active science demonstrations, as well as interactive astronomy exhibits and activities including the Hubble Space Telescope exhibit. Students in elementary and middle school as well as high school competed individually in the Science and Physics Challenge Contests. Team competitions similar to “It’s Academic” were offered through the Physics Bowl and Science Bowl. Prizes were awarded for all of the events. In ad- dition, the Maryland Space Grant Observatory was open for tours, and visitors were able to observe sun spots and activity of the sun’s corona using the Morris W. Offi t Telescope. Michael McPherson of Aerojet Culpeper presented his Adven- tures in Aerospace demonstration of various scientifi c principles to fair attendees. Ably assisted by Dr. Edmund Liu, CPIAC’s director and Zhuohan Liang, a JHU physics department graduate student, they entertained and educated scores of young visitors. CPIAC Director Ed Liu shows student visitors how to skewer CPIAC staff member Patricia Szybist greeted visitors at the a balloon without popping it! CPIAC booth and distributed bookmarks, t-shirts and NASA stick- ers provided by Mr. McPherson. TDK’04™ The JANNAF Standard for Liquid Engine Performance Prediction Just Got Better The TDK’04TM code uses the JANNAF methodology plus enhancements to compute thrust chamber performance. FEATURES: • Planar or Axially Symmetric Flow • Linkage to TECPLOT™ • Transpiration or Tangential Mass Injection • Equilibrium Radiation Heat Transfer • Pitot Tube Option • Linkage to SPF 2 or SPF 3 • Dual Bell Option • Summary Output Files for Each Module • Scarfed, Plug, and Scramjet Nozzle Configurations • Upper and Lower Wall Simulation • Accepts High Temperature NASA Thermodynamic Data • New Algorithms for improved accuracy and robustness • Increased Number of Kinetic Species and Reactions • Electron Charge Balance Calculation for Improved Ions Analysis • Nozzle Contour Optimization Routine with Kinetics, • Treats Internal/External Flow Interaction (Plug Nozzle) Boundary Layer, and Regen Effects along with a Base Pressure Correlation Improved Usability Graphics Post Processor Runs on Linux and on PC's under Win 95/98/NT/2000/XP Available only from SEA, Inc. at just $10,995 for a single user license Special Upgrade Offers Available to Current Owners of TDK Purchased from SEA, Inc. For more information: Software & Engineering Associates, Inc., 1802 N. Carson Street, Suite 200,Carson City, NV 89701-1238 contact: email: [email protected] Telephone: (775) 882-1966 FAX: (775) 882-1827 Visit our website at: http://www.seainc.com Copyrighted by SEA, Inc. 2009 All Rights Reserved. CPIAC Bulletin/Vol. 35, No. 3, May 2009 Page 9 SSttuuddeennttss aatt tthhee UUnniivveerrssiittyy ooff CCoolloorraaddoo aatt BBoouullddeerr DDeevveelloopp DDrraagg aanndd AAttmmoosspphheerriicc NNeeuuttrraall DDeennssiittyy EExxpplloorreerr ((DDAANNDDEE)) By Kyle D. Kemble, Lee E. Jasper, and Marcin D. Pilinski University of Colorado, Boulder, Colorado TT he Drag and Atmospheric Neutral Density Explorer (DANDE) is a 50-kg, spherical spacecraft being de- veloped by students at the University of Colorado at Boulder (CU-Boulder) through the Colorado Space Grant Consortium (COSGC) in partnership with the Aerospace Engineering Science Department (ASEN). The mission of the DANDE is to provide an improved understanding of the satellite drag environment in the lower thermosphere at low cost. Attempting to study the Earth’s upper atmosphere is not a new endeavor, which is of great benefi t to the team because leaders in the fi eld who are located in Colorado are available Figure 2. Body frame of DANDE illustrating the rise of to advise student efforts at the University. Project Starshine, the drag force. run out of offi ces in Monument, Colorado, consisted of a se- ries of passive spheres that were monitored from the ground show how the DANDE spacecraft identifi es them. A novel to observe their orbits’ decay before reentry. The fi rst sphere accelerometer instrument is on board that rotates navigation was launched from the Shuttle Discovery during STS-96; grade accelerometers in and out of the ram vector producing the next two were launched in 2001 – one during STS-108 a sinusoidal wave of acceleration readings. By implementing and the other on an Athena launch vehicle. The CHAMP this system to register the accelerations on the satellite, the (CHAllenging Mini-satellite Payload) satellite, which was instrument is capable of submicro-g resolution. Additionally, launched in 2000, is designed to study the gravity fi eld of the satellite is equipped with a Neutral Mass Spectrometer Earth and has the ability to probe the Earth’s upper atmo- (NMS) that can register the wind on orbit along with atmo- sphere for climate modeling. The images in Fig. 1 show the spheric density. DANDE, with its dual instrument approach, radically differerent forms these satellites took on with their is considered an active sphere and will help with the valida- intended missions. tion of the current atmospheric drag models that can vary at present by anywhere from 300 to 800%. Drag is one of the few disturbances that can affect sat- ellites while in low Earth orbit (LEO) and becomes more prominent with the increase in atmosphere as altitude de- creases. Figure 3 illustrates how the altitude of the Interna- tional Space Station (ISS) fell dramatically after a solar fl are hit the Earth’s atmosphere. The reason behind the solar fl are Figure 1. At left, Starshine Director Gil Moore is shown holding a mockup of the Starshine 1 & 2 Payloads.1 At right, illustration of the CHAMP satellite2 while on orbit. Each of these satellites was designed with a mission to monitor one variable of the drag equation. In the case of Starshine, the parameter was atmospheric drag. CHAMP monitored the upper atmosphere, effectively providing den- sity readings. DANDE is unique in studying the lower ther- mosphere for the degradation of satellite orbits because it is designed to study two important parts of the drag equa- tion simultaneously. A basic layout of the drag equation is shown in Fig. 2, with the individual variables called out to Figure 3. Orbit degradation of the ISS and the infl uence of 1http://nasascience.nasa.gov/missions/champ the atmosphere. 2http://azinet.com/starshine/index.html continued on page 11 Page 10 CPIAC Bulletin/Vol. 35, No.3, May 2009