| Heterocyclic Salt Synthesis and Rational Properties Tailoring (PREPRINT) |
23 Jun 2009 |
23 pages |
| Authors:
Scott A Shackelford; John L Belletire; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE
|
 | Chemical structure determines the inherent properties displayed by a given compound, and these properties, in turn, produce a specific performance behavior. Rationally designing chemical structure to predictably modify compound properties, such that performance behavior can be tailored in a controlled manner, defines the objective of a pertinent synthesis effort. Achieving this objective by introducing structural alterations in a neutral covalent compound offers only one approach for resultant properties modification. Heterocyclic ... |
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| Design of Energetic Ionic Liquids |
12-May-2009 |
9 pages |
| Authors:
Sharon Hammes-Schiffer; Jerry A Boatz; Mark S Gordon; Gregory A Voth; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE
|
| An essential need of the US Air Force is the discovery, development, and fielding of new, energetic materials for advanced chemical propulsion in space and missile applications. Some of the key factors driving the requirement for new chemical propellants include: (a) improved performance in terms of increased specific impulse and density, (b) reduced sensitivity to external stimuli such as impact, friction, shock, and electrostatic discharge, and (c) mitigation of environmental ... |
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| Critical Design Parameters for Pylon-Aided Gaseous Fuel Injection Upstream of a Flameholding Cavity |
Mar-2009 |
142 pages |
| Authors:
Mitchell R Pohlman; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH GRADUATE SCHOOL OF ENGINEERING AND MANAGEMENT
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| The Air Force Institute of Technology and the AFRL are investigating means to increase the efficiency of fuel-air mixing into supersonic flow. Previous work has shown much promise in increasing the penetration and mixing of a fuel-air mixture into the freestream by injecting fuel behind small triangular pylons. Pylon-aided fuel injection has also shown to lift the fuel plume off the combustor floor; this floor-gap prevents the ignition of fuel ... |
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| An Investigation into the Hypergolicity of Dicyanamide-based Ionic Liquid Fuels with Common Oxidizers (Preprint) |
Dec-2008 |
11 pages |
| Authors:
E Dambach; S Heister; I Ismail; S Schneider; T Hawkins; PURDUE UNIV LAFAYETTE IN
|
| Previous studies have demonstrated that substituted imidazolium dicyanamides are hypergolic with nitric acid. An investigation was conducted to study the hypergolicity of selected dicyanamides, commercially available 1-butyl-3-methyl-imidazolium dicyanamide and Air Force Research Laboratory developed AF-IL-617, with common oxidizers. Diluents, particularly water and methanol, were introduced to the fuel in an effort to understand the effect on the ignition delay. The water dilution limit at which ignition would still occur was ... |
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| Design of Energetic Ionic Liquids (Preprint) |
07-May-2008 |
6 pages |
| Authors:
Sharon Hammes-Schiffer; Jerry A Boatz; Mark S Gordon; Gregory A Voth; AIR FORCE RESEARCH LAB EDWARDS AFB CA SPACE AND MISSILE PROPULSION DIV
|
| An essential need of the US Air Force is the discovery, development, and fielding of new, energetic materials for advanced chemical propulsion in space and missile applications. Some of the key factors driving the requirement for new chemical propellants include: (a) improved performance in terms of increased specific impulse and density, (b) reduced sensitivity to external stimuli such as impact, friction, shock, and electrostatic discharge, and (c) mitigation of environmental ... |
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| Characterization and Fate of Gun and Rocket Propellant Residues on Testing and Training Ranges |
Jan-2008 |
597 pages |
| Authors:
Sonia Thiboutot; Richard Mantel; Dominic Faucher; Thomas F Jenkins; Alan D Hewitt; Susan R Bigl; Michael R Walsh; Marianne E Walsh; Isabelle Poulin; Sylvie Brochu; Susan Taylor; Guy Ampleman; Katerina M Dontsova; ENGINEER RESEARCH AND DEVELOPMENT CENTER VICKSBURG MS
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| Over the past two years, the U.S. Army Engineer Research and Development Center and the Defence R&D Canada Valcartier have partnered to develop an improved understanding of the distribution and fate of propellant residues on military training ranges in SERDP Project ER-1481. As a portion of this work, field studies have been conducted to estimate the mass of propellant residues deposited per round fired from various munitions. This research included ... |
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| Testing of LiAlH4 as a Potential Additive to Paraffin Wax Hybrid Rocket Fuel |
30 OCT 2007 |
23 pages |
| Authors:
John D. DeSain; Thomas J. Curtiss; Ronald B. Cohen; Brian B. Brady; Steven A. Frolik; AEROSPACE CORP EL SEGUNDO CA
|
| The burn rate of paraffin wax fuel was measured in air with and without addition of LiAlH4. The paraffin wax was mixed with 7-24% LiAlH4(lithium aluminum hydride) by weight. The wax was then molded into candles. The candles where lit in air, and the mass loss with time was recorded. The 24% LiAlH4 was found to enhance the burn rate of the candles by a factor of 14. LiAlH4 was ... |
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| Performance Characterization of the Free Molecule Micro-Resistojet Utilizing Water Propellant (Preprint) |
24 MAY 2007 |
12 pages |
| Authors:
R. H. Lee; A. M. Bauer; M. D. Killingsworth; T. C. Lilly; J. A. Duncan; Andrew D. Ketsdever; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE
|
| Advances in micro-technology manufacturing and capability have led to an increased interest in micro and nano-satellites. A propulsion system has been designed to meet the on-orbit attitude control requirements for nano-spacecraft. The Free Molecule Micro-Resistojet (FMMR), a low cost, low power, high propellant storage density, and green propulsion system, has been analyzed in this study to determine its ability to provide a slew maneuver for a typical 10 kg nanosatellite. ... |
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| Characterization and Fate of Gun and Rocket Propellant Residues on Testing and Training Ranges: Interim Report 1 |
JAN 2007 |
221 pages |
| Authors:
Thomas F. Jenkins; Judith C. Pennington; Guy Ampleman; Sonia Thiboutot; Michael R. Walsh; Emmanuela Diaz; Katerina M. Dontsova; Alan D. Hewitt; Marianne E. Walsh; Susan R. Bigl; Susan Taylor; Denise K. MacMillan; Jay L. Clausen; Dennis Lambert; Nancy M. Perron; Marie C. Lapointe; Sylvie Brochu; Marc Brassard; Rob Stowe; Roccio Farinaccio; ENGINEERING RESEARCH AND DEVELOPMENT CENTER HANOVER NH COLD REGIONS RESEARCH AND ENGINEERING LAB
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| The objectives of the research described in this report are to characterize the deposition and accumulation of propellant residues at the various types of firing points at military firing ranges, develop process descriptors to allow estimation of environmental transport rates of individual energetic chemicals from these residues, and collect lysimeter and groundwater monitoring well samples to experimentally assess off-site transport of residues. Estimates of residue deposition are presented for the ... |
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| Development of Co-Extrusion Technologies for Green Manufacture of Energetics |
APR 2006 |
50 pages |
| Authors:
Dilhan M. Kalyon; Halil Gevgilili; Hansong Tang; Moinuddin Malik; Arshad Mirza; E. Deminkol; Bert Greenberg; Duncan Park; Kristin Jasinkiewicz; Judith M. Mahon; STEVENS INST OF TECHNOLOGY HOBOKEN NJ HIGHLY FILLED MATERIALS INST
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| The manufacturing of co-extruded grains of highly filled propellant suspensions is a complicated operation, which requires a detailed and realistic understanding of the various types of interface, surface, and bulk instabilities. This understanding is necessary to be able to successfully manufacture fast core propellants using co-extrusion (ram or twin screw extrusion based). In this investigation, the fundamentals of the co-extrusion process were investigated by a combination of experimental and simulation ... |
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| Time Resolved Measurements and Reactive Pathways of Hypergolic Bipropellant Combustion |
31 MAR 2006 |
37 pages |
| Authors:
Jr Smith James E.; ALABAMA UNIV IN HUNTSVILLE
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| This research has improved the fundamental understanding of the physical mechanisms leading to the ignition and combustion of hypergolic propellants from high-speed visualization and combustion diagnostics. The laser diagnostic system for the measurement of hypergolic droplet mixing and combustion was further developed by controlling many relevant factors. These include: droplet size, impact, and mixing; fuel/oxidizer lead; fuel/oxidizer ratio; controlled atmosphere, chemical safety, and event timing and resolution. As a result, ... |
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| Steganalysis for Audio Data |
31 MAR 2006 |
39 pages |
| Authors:
Jana Dittmann; OTTO VON GUERICKE UNIV MAGDEBURG (GERMANY) INST FOR EXPERIMENTAL PHYSICS
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| The Audio WET system is a web-based evaluation system which provides the user the functionality of different watermarking algorithms (embedding and detecting) with a large database of audio signals (test material). The system also provides both single and profile attacks which can be used to evaluate the watermarking algorithms. The user has the choice to specify the watermarking algorithms with their parameters for embedding and the type of audio content. ... |
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| Production of Lunar Oxygen Through Vacuum Pyrolysis |
26 JAN 2006 |
71 pages |
| Authors:
John Matchett; GEORGE WASHINGTON UNIV WASHINGTON DC SCHOOL OF ENGINEERING AND APPLIED SCIENCE
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| Increasing efficiency of future space exploration will require that missions utilize non-terrestrial resources for propellant manufacture. The vacuum pyrolysis method of oxygen production from lunar regolith presents a viable option for in situ propellant production because of its simple operation involving limited resources from earth. Lunar regolith, the fine layer of pulverized rock across the entire lunar surface, is composed of approximately forty percent oxygen in the form of metal ... |
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| Highly Accurate Ignition Delay Apparatus for Hypergolic Fuel Research |
2006 |
6 pages |
| Authors:
Angelo J. Alfano; Jeffrey D. Mills; Ghanshyam L. Vaghjiani; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE
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| The efficient development of hypergolic fuels requires an interdisciplinary approach involving ab initio modeling, synthesis, and experimental physical chemistry. Candidate molecules must exhibit hypergolic ignition delay times that are fast enough to warrant further testing for safety and performance criteria. Hypergolic ignition delay apparatus has been mentioned in the open literature for six decades but accurate, detailed, modern ignition delay hardware that uses inexpensive laboratory building blocks and a minimum ... |
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| A Low Power, Novel Ignition of Fuels Using Single-Wall Carbon Nanotubes (SWCNTs) and a Camera Flash (POSTPRINT) |
14 NOV 2005 |
9 pages |
| Authors:
S. A. Danczyk; B. Chehroudi; A. D. Ketsdever; G. L. Vaghjiani; ENGINEERING RESEARCH AND CONSULTING INC (ERC INC) EDWARDS AFB CA
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| Many current industrial processes that utilize fuel/oxidizer chemical reactions often require an initiation stimulus, or an ignition source, to start the conversion of the chemicals to the products and release heat. A device which achieves this goal is a critical system component for most combustion processes especially in mobile and stationary power producing machines. For example, improper ignition during the firing of a rocket engine for lift-off can lead to ... |
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| Chemistry in Action: Space Shuttle Fuel Chemistry |
AUG 2005 |
32 pages |
| Authors:
Ghanshyam L. Vaghjiani; AIR FORCE RESEARCH LAB EDWARDS AFB CA SPACE AND MISSILE PROPULSION DIV
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| Energetic Materials Modeling for Rocket Propulsion |
AUG 2005 |
27 pages |
| Authors:
Jerry Boatz; Jeffrey Mills; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE
|
| OUTLINE: 1. Introduction; 2. Technical challenges in propellant design; 3. Modeling and Simulation (M&S) techniques & tools: (a) Quantum chemistry; (b) High Performance Computing (HPC); 4. Examples: (a) Identification of suitable target compounds; (b) Determination of viable intermediates; (c) Confirmation of successful synthesis; 5. Challenges and Bottlenecks; 6. Summary and Conclusions. |
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| All-Nitrogen Compounds as High Energy Density Materials |
15 JUL 2005 |
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| Authors:
Kurt Baum; Rodney L. Willer; Jeffrey Bottaro; Mark Petrie; Paul Penwell; Allen Dodge; Ripu Malhotra; FLUOROCHEM INC AZUSA CA
|
 | There is a continuing need for safe, versatile rocket propellants, which are stable, nonvolatile, energetic, and easily demilitarized. Ionic liquids constitute a research area that is little explored for propellant ingredients and provides potential to meet these requirements. Enhanced dissolving power, density and compatibilities with a wide range of propellant ingredients make ionic liquids a very attractive class of materials for advanced state-of-the-art propulsion systems. The extreme polarity of these ... |
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| Experimental and Numerical Study of Nozzle Plume Impingement on Spacecraft Surfaces |
13 JUL 2005 |
7 pages |
| Authors:
A. D. Ketsdever; T. C. Lilly; S. F. Gimelshein; A. A. Alexeenko; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE
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| An experimental and numerical effort was undertaken to assess the effects of a cold gas (To=300K) nozzle plume impinging on a simulated spacecraft surface. The nozzle flow impingement is investigated experimentally using a nano-Newton resolution force balance and numerically using the Direct Simulation Monte Carlo (DSMC) numerical technique. The Reynolds number range investigated in this study is from 0.5 to approximately 900 using helium and nitrogen propellants. The thrust produced ... |
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| Cryogenic and LOX Based Propulsion Systems for Robotic Planetary Missions |
13 JUL 2005 |
8 pages |
| Authors:
Dominique Valentian; SNECMA MOTEURS VERNON (FRANCE) MOTEURS SPATIAUX DIV
|
| Robotic planetary missions use almost exclusively storable propellants. However, it is clear that the use LOX/LH2 and LOX/HC combinations will offer a tremendous payload gain for most robotic missions. The perceived complexity of cryogenic propulsion, the need of cryogenic propellants active refrigeration to eliminate boil-off losses and the high acceleration imparted to spacecraft structure by high thrust cryogenic engines have prevented the use of cryogenic propulsion for robotic missions. Elaborated ... |
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| Monte Carlo Simulation of Plumes Spectral Emission |
07 JUN 2005 |
122 pages |
| Authors:
Sergey T. Surzhikov; RUSSIAN ACADEMY OF SCIENCES MOSCOW (RUSSIA) INST FOR PROBLEMS IN MECHANICS
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| Methods of spectral diagnostics of nonhomogeneous volumes of heated gases are the most challenging for investigation of exhaust plumes of the hydrogen and carbon-hydrogen fuels. Computing methods of calculation of spectral heat radiation emissivity are the components of the general problem. The numerical simulation of plumes radiation is a challenging problem because there is a large number of different factors which characterize the phenomena of the spectral radiation transfer in ... |
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| Structural Isomers of bis(pentazolyl)iron(II): A Theoretical Study |
22 APR 2005 |
27 pages |
| Authors:
Jerry A. Boatz; Karl Christe; Ashwani Vij; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE
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| The High Energy Density Materials (HEDM) Program objectives are: Identifying and developing advanced chemical propellants for rocket propulsion applications; specific impulse (Isp) is the major metric of a propellant's performance; density can also be a significant contributor. |
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| Materials Modeling for Rocket Propulsion |
APR 2005 |
23 pages |
| Authors:
Jerry Boatz; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE
|
| OUTLINE: 1. Introduction; 2. Technical challenges in propellant design; 3. Modeling and Simulation (M&S) techniques & tools: a) Quantum chemistry; b) Molecular dynamics; c) QSPR; d) High Performance Computing (HPC); 4. Examples: a) Identification of suitable target compounds; b) Determination of viable intermediates; c) Confirmation of successful synthesis; 5. Summary and Conclusions. |
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| 248-NM Laser Photolysis of CHBr3/O-Atom Mixtures: Kinetic Evidence for UV CO(A)-Chemiluminescence in the Reaction of Methylidyne Radicals with Atomic Oxygen |
APR 2005 |
19 pages |
| Authors:
Ghanshyam L. Vaghjiani; AIR FORCE RESEARCH LAB EDWARDS AFB CA SPACE AND MISSILE PROPULSION DIV
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|
| Holloman High Speed Test Track Design Manual |
01 MAR 2005 |
83 pages |
| Authors:
TEST GROUP ( 46TH) HOLLOMAN AFB NM
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| The design of rocket sleds requires the engineer to evaluate complex loads and numerous load conditions which are imposed on the sleds as they travel along the track. This manual represents the combined effort of many Test Track engineers. In essence they have tried to document the current sled design practices that have lead to successful sled tests. This manual along with more current technical investigations and reports serve as ... |
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| The Influence of Particulates on Thruster Plume / Shock Layer Interaction at High Altitudes |
JAN 2005 |
13 pages |
| Authors:
Sergey F. Gimelshein; Alina A. Alexeenko; Dean C. Wadsworth; Natalia E. Gimelshein; UNIVERSITY OF SOUTHERN CALIFORNIA LOS ANGELES
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| A two-phase plume flow from a small aluminized propellant side thruster interacting with rarefied atmosphere at 120 km has been examined numerically. A three step continuum-kinetic approach has been used, with the Navier-Stokes equations solved inside the nozzle, and a 2D/3D DSMC method employed to compute the plume nearfield and then the plume-atmosphere interaction region. At each of these steps, a two-way gas-particulate coupling has been used. The DSMC implementation ... |
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| Impulse Pendulum with Adjustable Pivot Point for Measuring Coupling Coefficient |
OCT 2004 |
8 pages |
| Authors:
John S. Harchanko; Franklin B. Mead Jr.; C. W. Larson; AIR FORCE RESEARCH LAB EDWARDS AFB CA SPACE AND MISSILE PROPULSION DIV
|
| An impulse pendulum with significantly increased sensitivity compared to its predecessor is described. The problems associated with its predecessor are discussed and other pendulum designs are also presented. The design approach for the new pendulum is then presented along with the current mechanical design and photographs of the finished pendulum. The pendulum's performance is presented compared to its predecessor. Finally, other embodiments of the approach are presented. |
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| A Ground-Test Facility for High-Power Electric Thrusters Operating on Condensible Propellants |
SEP 2004 |
6 pages |
| Authors:
Lyon B. King; MICHIGAN TECHNOLOGICAL UNIV HOUGHTON DEPT OF MECHANICAL ENGINEERING AND ENGINEERING MECHANICS
|
| Work reported here resulted in the design and fabrication of a space- simulation facility used to test electric thrusters for spacecraft. The facility was specifically designed to accommodate thrusters using condensable metal propellants such as bismuth. Apparatus includes a large 2-m x 4-m vacuum vessel evacuated through three 2,000-liter-per-second turbomolecular pumps, a 20-kW DC power supply, a remote translation system, and computer data acquisition center. |
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| Quantum Simulations of Low Temperature High Energy Density Matter |
03 MAY 2004 |
8 pages |
| Authors:
Gregory A. Voth; UTAH UNIV SALT LAKE CITY DEPT OF CHEMISTRY
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| Solid hydrogen doped with energetic impurities may form the basis for HEDM to be used in rocket propulsion. A key research priority has been to investigate the equilibrium properties of a boron impurity and of an aluminum impurity trapped in solid parahydrogen. The simulation methods used in the study allow us to take into account the quantum nature of the HEDM in question. Using classical molecular dynamics simulations to evaluate ... |
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| The Structure of Secondary 2-Azidoethanamines: A Hypergolic Fuel vs. a Nonhypergolic Fuel |
APR 2004 |
46 pages |
| Authors:
Michael J. McQuaid; ARMY RESEARCH LAB ABERDEEN PROVING GROUND MD WEAPONS AND MATERIALS RESEARCH DIRECTORATE
|
| In an attempt to find structural features of 2-azidoethanamines that correlate with their hypergolic ignition delays, density functional theory (DFT) -based quantum mechanics calculations were performed to characterize equilibrium configurations of two secondary 2-azidoethanamines: 2-azido-N- cyclopropylethanamine (CPAZ) and 2-azido-N-methylethanamine (MMAZ). The former is hypergolic with inhibited red fuming nitric acid, while the latter is not. Geometries and normal modes for 23 MMAZ conformers and 42 CPAZ conformers are presented, compared ... |
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| Polynitrogen and High Nitrogen Chemistry: A New World of Challenges |
25 MAR 2004 |
85 pages |
| Authors:
Ashwani Vij; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE
|
| Polynitrogen compounds contain only nitrogen atoms and are expected to have unusual properties. Most important among these are: High endothermicity Green propellant combustion product is only gaseous N2 High density High Isp values when compared to other monopropropellants or bipropellants High detonation velocity |
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| Transport in Plasma Thrusters Using Complex Propellants |
01 MAR 2004 |
80 pages |
| Authors:
Peter J. Turchi; OHIO STATE UNIV COLUMBUS DEPT OF AEROSPACE ENGINEERING APPLIED MECHANICS ANDAVIATION
|
| Theoretical modeling of ablation-fed, pulsed plasma thrusters (PPTs) with the MACH2 code has shown that after repeated pulsed operation, the total expelled mass is due to ablation during the discharge and solid decomposition that persists long after the pulse. The latter mass does not considerably contribute to the impulse-bit thus degrading thruster performance. For the rectangular PPT geometry, optimizing current waveforms in combination with channel widths are presented, that utilize ... |
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| Upper Stage Flight Experiment (USFE) Integral Structure Development Effort |
2004 |
11 pages |
| Authors:
Jim Guerrero; Brent Hamilton; Randy Burton; Dave Crockett; Zach Taylor; AIR FORCE RESEARCH LAB KIRTLAND AFB NM SPACE VEHICLES DIRECTORATE
|
| The Air Force Research Laboratory's Space Vehicle Directorate (AFRL/VS) has established a customer focused Composite tankage development program that is targeted to existing and future aerospace applications. AFRL/VS is developing a wide range of tank concepts that include linerless cryogenic tankage, self-healing cryogenic tankage, hydrogen peroxide compatible tankage, volumetrically efficient toroidal (donut shaped) geometries, and more. This paper will summarize the Upper Stage Flight Experiment (USFE) composite integral structure development ... |
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| Multi-Scale Approach to Investigate the Tensile and Fracture Behavior of Nano Composite Materials |
08 SEP 2003 |
18 pages |
| Authors:
C. T. Liu; AIR FORCE RESEARCH LAB EDWARDS AFB CA SPACE AND MISSILE PROPULSION DIV
|
| For presentation at the AFOSR Materials and Mechanics Program Review in Santa Fe, New Mexico, 8 September 2003. |
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| High Energy Density Materials |
SEP 2003 |
52 pages |
| Authors:
David Bomberger; Jeffrey C. Bottaro; Mark Petrie; Paul E. Penwell; Allen L. Dodge; SRI INTERNATIONAL MENLO PARK CA
|
| Synthetic pathways to the nitroazoxyamine, pentazole-N-oxide, and triazanitrate anions have been explored at a fundamental level. The reaction of nitrene equivalents such as organic azides, N-haloamines, N-acyl hydroxylamines N,O-diacyl hydroxylamines, and amides in the presence of lead tetra-acetate or phenyliodine diacetate, acting on N,N dialkylnitrosoamines in an attempt to generate alkylazoxyamines have all been examined. Initial results were not encouraging; in response to this, the N,N-dialkylnitrosoamine was silylated, methylated, and ... |
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| Improved Strand Burn Rate Reproducibility Using a New Preparation Methodology for Paint-Based Inhibitors |
SEP 2003 |
|
| Authors:
Andrew H. Hart; Raoul A. Pietrobon; DEFENCE SCIENCE AND TECHNOLOGY ORGANISATION SALISBURY (AUSTRALIA) SYSTEMS SCIENCES LAB
|
| Small-scale ballistic characterisation of composite rocket propellants is a critical step in the development of rocket motors and is achieved by measuring linear strand burning rates determined using the Crawford strand burning technique. To utilise this technique, the propellant strands must burn with an end-burning configuration, which is achieved through the application of a water-based acrylic paint as an inhibitor. To be effective, the inhibitor needs to be of such ... |
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| Advanced Rocket Propulsion Technologies Boron Vapor Source for HEDM |
JUN 2003 |
33 pages |
| Authors:
Paul C. Nordine; CONTAINERLESS RESEARCH INC EVANSTON IL
|
| The research reported here is directed to the development of a boron vapor source for application in HEDM research. Specific goals of the research were (i) a boron vapor flux that allows formation of transparent solid pH2 with high concentrations of boron dopant species, up to 5 molar %, (ii) a design for integration with the cryo-solid spectroscopy equipment at AFRL/PRSP, Edwards Air Force Base. The boron vapor source was ... |
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| Matchmaking in Polynitrogen Chemistry: Search for Prospective Anions for Combination with N+5 |
21 APR 2003 |
36 pages |
| Authors:
Vij Ashwani; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE
|
| This document is a report of the matchmaking in polynitrogen chemistry: search for prospective anions for combination with N+5. |
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| First-Principles Calculations of the Adsorption of Nitromethane and 1,1- Diamino-2,2-dinitroethylene (FOX-7) Molecules on the Al(111) Surface |
31 MAR 2003 |
33 pages |
| Authors:
Dan C. Sorescu; Jerry A. Boatz; Donald L. Thompson; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE
|
| First-principles calculations based on spin-polarized density functional theory (DFT) and the generalized gradient approximation (GGA) have been used to study the adsorption of nitromethane (NM) and 1,1-diamino-2,2- dinitroethylene (FOX-7) molecules on the Al(111) surface. The calculations employ (3x3) aluminum slab geometries and 3D periodic boundary conditions. Based on these calculations, we have determined that both dissociative and nondissociative adsorption mechanisms are possible, depending on the molecular orientation and the particular ... |
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| Spectrally Analyzed Embedded Infrared Fiber Optic Diagnostic of Advanced Composite Propellant Combustion |
31 MAR 2003 |
35 pages |
| Authors:
Joda Wormhoudt; AERODYNE RESEARCH INC BILLERICA MA
|
| This is the final report for a program to extend an embedded- infrared-fiber propellant strand burning diagnostic by replacing bandpass filter detection by spectral detection. This work builds on previous investigations into the chemical and physical processes occurring in the condensed phases of nitramine advanced composite propellants, in which we observed decomposition product gases by infrared absorption in a small volume below the flame front. Detection of infrared absorption spectra ... |
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| Towards New Polynitrogen Species: The Search for Viable Precursors |
29 JAN 2003 |
28 pages |
| Authors:
Karl Christe; Ralf Haiges; Stefan Schneider; Thorsten Schroer; Ashwani Vij; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE WEST
|
| The presentation slides for the briefing concerning, Towards New Polynitrogen Species: The Search for Viable Precursors are presented. |
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| Material Applications Research Within the Propulsion Directorate of the Air Force Research Laboratory |
27 JAN 2003 |
35 pages |
| Authors:
Shawn H. Phillips; AIR FORCE RESEARCH LAB EDWARDS AFB CA
|
| Viewgraphs for presentation on materials research and development conducted by the Air Force Research Lab Propulsion Directorate, Edwards AFB, California, and its subdivisions. |
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| Technical Evaluation Report Meeting on Advanced Rocket Performance Life and Disposal |
05 NOV 2002 |
10 pages |
| Authors:
Ronald L. Derr; OFFICE OF NAVAL RESEARCH ARLINGTON VA
|
| The Specialists' Meeting on Advanced Rocket Performance Life and Disposal was held 23-26 September 2002. This was the second meeting on rocket motors organized by the Applied Vehicle Technology (AVT) Panel since it was created in 1996. The aim of the meeting was achieved in that a snapshot of the state-of-the-art in areas covered by the meeting was accomplished. This evaluation report catalogs results along topic areas defined in an ... |
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| Composite Propellants with Bi-Plateau Burning Behaviour |
NOV 2002 |
|
| Authors:
Kym M. Ide; DEFENCE SCIENCE AND TECHNOLOGY ORGANISATION SALISBURY (AUSTRALIA) SYSTEMS SCIENCES LAB
|
| The literature describing the mechanism of combustion in composite rocket propellants exhibiting hi-plateau burning has been reviewed. A wide distribution of AP particle size in a definite coarse/fine ratio is required to ensure adequate interstitial spacing resulting in abnormally depressed burning due to interference of the fine AP fraction combustion by the binder melt layer. Titanium dioxide added to the formulation acts to increase the binder melt layer viscosity restoring ... |
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| Next Generation Diode Lasers for Wavelength Multiplexed Propulsion Sensors |
15 SEP 2002 |
4 pages |
| Authors:
R. K. Hanson; STANFORD UNIV CA HIGH TEMPERATURE GASDYNAMICS LAB
|
| Equipment listed in the report was purchased under the Department of Defense University Research Instrumentation Program (DURIP). |
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| 'Green' Propulsion - A US Air Force Perspective* |
AUG 2002 |
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| Authors:
Tom W. Hawkins; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE WEST
|
| Recent U.S. Air Force programs are aiming to develop reduced toxicity propellants. These programs focused on both solid and liquid propellant systems. In solid propulsion, investigation was performed for alternatives to ammonium perchlorate-based, space launch propellant. This was principally conducted under the auspices of the Strategic Environmental Research and Development Program (SERDP). This program was recently successfully concluded with a finding that green', ammonium nitrate-based propellant could be produced with ... |
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| The Performance of a Hybrid Rocket With Swirling GOx Injection |
JUL 2002 |
|
| Authors:
Tsong-Sheng Lee; A. Potapkin; NATIONAL CHENG KUNG UNIV TAINAN (TAIWAN)
|
| With the developed HTPB curing process a 10-Kg thrust hybrid rocket was built and passed several static firing tests here in ASTRC. The motor was designed similar to the classical one with an aft-mixing chamber. The purpose of preset study is then to develop the enhancement mechanism for oxidizer and fuel vapor mixing and flame holding to assess the necessity of aft-mixing chamber that is usually employed in a classical ... |
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| Synthesis and Structural Characterization of Nitrogen Containing High Energy Density Materials |
18 JUN 2002 |
3 pages |
| Authors:
Karl O. Christe; Ashwani Vij; Vandana Vij; William W. Wilson; Fook S. Tham; ENGINEERING RESEARCH AND CONSULTING INCEDWARDS AFB CA
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| In this paper we report the crystal structures of the novel N5+ cation in N5+Sb2F11-, which is the first stable polynitrogen species to be discovered in a century since the discovery of the azide ion. |
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| First Principles Calculations of Nitro Compounds with the A1 (111) Surface. DoD UGC, 10-14 Jun 02, Austin, TX |
14 JUN 2002 |
26 pages |
| Authors:
Jerry Boatz; AIR FORCE RESEARCH LAB EDWARDS AFB CA SPACE AND MISSILE PROPULSION DIV
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| The objective of the research is to identify, develop and transition new propellants and advanced concepts for propulsion applications, such as hydrocarbon fuels for liquid boost, liquid and solid oxidizers for boost and upper stages, monopropellants for spacecraft and upper stages, cryogenic propellants for upper stages and laser light craft for microsatellite and other applications. |
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| T* (sub Epsilon) Integral of a Particulate Composite |
22 MAY 2002 |
12 pages |
| Authors:
J. H. Jackson; H. Lu; A. S. Kobayashi; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE WEST
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| Digital image correlation data and the Osgood-Ramberg constitutive relation were used to evaluate the T*(sub epsilon) integral of a particulate composite SEN specimen subjected to stable crack growth. The domain size independency of the T*(sub epsilon) integral of this rubbery composite subjected to large deformation was also assessed with varying inner contours ranging from 2.0 to 5.0 mm with domain sizes of 0.25, 0.50, and 0.75 mm. The near field ... |
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Rocket Propellants
