| Materials Testing Capabilities |
07 Dec 2011 |
10 pages |
| Authors:
Mu-Jen Yang; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE
|
 | The objective of this task is to compile a list of materials testing capabilities suitable for testing the materials development for liquid rocket engines by the JANNAF liquid propulsion community in USA. Information has been collected on the materials testing capabilities in some of the commercial testing laboratories, academic research and development institutes, and government organizations; it has been compiled, and has been listed in Tables I, II and III, ... |
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| Intro & Basic R&D Overview for NRC RAP Administrator |
13 Jul 2011 |
17 pages |
| Authors:
LaDonna Davis; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE
|
| This presentation is an overview of basic Research & Development at the AFRL Propulsion Directorate, given to the National Research Council Research Associateship Programs. |
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| Air Force Research Laboratory, Edwards Air Force Base, CA |
27 Jun 2011 |
|
| Authors:
Mike Platt; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE
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| This presentation is an overview of the Air Force Research Laboratory at Edwards AFB, CA, as presented to the Boron Chamber of Commerce dinner/briefing in Boron, CA, 27 Jun 2011. |
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| Procedure Writing Aid |
29 MAR 2011 |
29 pages |
| Authors:
Daniel C. Harbour; Joseph N. Beasley; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIR/SPACE AND MISSILE PROPULSION DIV
|
| This report describes a best practice for writing procedures for test operations of solid motors and liquid engines based on two decades worth of test experience. The Air Force Research Laboratory at Edwards AFB, California, recently completed an effort to create procedure writing guidance for test operations. This procedure writing guidance is designed as an aid for new employees and as a reference document for those with test experience. The ... |
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| Green Hypergolic Bipropellants: H202/Hydrogen-Rich Ionic Liquids |
04 MAR 2011 |
20 pages |
| Authors:
Stefan Schneider; Tom Hawkins; Yonis Ahmed; Michael Rosander; Jeff Mills; Leslie Hudgens; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE
|
| The low vapor toxicity of ionic liquids (ILs) make them attractive replacements for hydrazine in rocket applications. However, ILs will fail to fulfill their revolutionary promise unless toxic oxidizers like HNO3 or N2O4 can be replaced with safer alternatives. By their very nature all rocket oxidizers are hazardous and so reducing those hazards, even though the resulting materials might not be completely harmless, is at the heart of green initiatives ... |
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| Basic Research Investigations into Multimode Laser and EM Launchers for Affordable Rapid Access to Space (Volumes 1 and 2) |
31 Aug 2010 |
350 pages |
| Authors:
Leik N Myrabo; Israel I Salvador; David A Kenoyer; RENSSELAER POLYTECHNIC INST TROY NY
|
| This basic research effort on pulsed airbreathing/rocket laser propulsion, investigates the physics of laser energy deposition into stationary and hypersonic working Ouids, inclusive of electrical breakdown, ignition of laser-supported detonation waves (LSD}, and blast wave propagation over thruster impulse-generating surfaces. The future application of AFOSR interest for this basic research endeavor is the laser launch of nano- and micro-satellites (i.e., 1-100 kg payloads} into Low Earth Orbit (LEO), at low ... |
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| Measurements of the Effectiveness of Concave Spherical Dimples for Enhancement of Hot-gas Side Heat Transfer |
02-Jun-2009 |
10 pages |
| Authors:
Stephen A Danczyk; Edward B Coy; AIR FORCE RESEARCH LAB EDWARDS AFB CA SPACE AND MISSILE PROPULSION DIV
|
| Measurements of the heat transfer enhancement effects of concave spherical dimples have been performed under hydrogen-oxygen hot-fire conditions in a subscale combustion chamber. Seven configurations were tested with a range of area densities from 15-70% and depth to diameter ratios of 0.111 to 0.333. Enhancements of 15-82% relative to a smooth surface were measured. Reynolds number was varied by a factor of 5 and was found to have an insignificant ... |
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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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| 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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| An Evaluation of High Velocity Wear |
MAR 2007 |
143 pages |
| Authors:
Gregory J. Cameron; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING AND MANAGEMENT
|
| The Holloman High Speed Test Track (HHSTT) is a rocket-powered sled track facility used for testing a variety of hypervelocity aerospace applications. The current speed record is 6,453 miles per hour. While this seems fast there are customers at the track that have requirements demanding even faster speeds. Significant research has been conducted in the area of rail gouging as it relates to the test track, and efforts are under ... |
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| Plume Characteristics of the Busek 600 W Hall Thruster |
12 JUL 2006 |
11 pages |
| Authors:
Jared M. Ekholm; Jr. Hargus William A.; C. W. Larson; Michael R. Nakles; Garrett Reed; Carrie S. Niemela; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE
|
| To better characterize the potential impacts of the operation of a Busek Company, Inc. BHT-HD-600 laboratory Hall thruster on spacecraft, a number of plume properties have been measured. These include current density using a Faraday probe, ion energy distribution using a retarding potential analyzer, and ion species fractions using an E x B probe. The BHT-HD-600 Hall thruster is a nominally 600 W xenon Hall thruster developed by Busek Co. ... |
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| Reduce Manufacturing Costs of Ultra-High Temperature Rhenium Pintle/Throat Combinations |
28 JUN 2006 |
2 pages |
| Authors:
NATIONAL CENTER FOR DEFENSE MANUFACTURING AND MACHINING LATROBE PA
|
| Controllable thrust propulsion for the next generation of tactical missiles (NLOS PAM) is providing significant mission flexibility and increasing the system's capability in terms of precision performance. Thrust propulsion within a tactical missile is controlled by a pintle/throat configuration. The purpose of the pintle/throat configuration is to maximize the thrust within the rocket motor to successfully propel the missile. Rhenium, due to its high thermal and mechanical properties, is the ... |
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| A Comparative Analysis of Single-Stage-To-Orbit Rocket and Air-Breathing Vehicles |
JUN 2006 |
100 pages |
| Authors:
Benjamin S. Orloff; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH DEPT OF AERONAUTICS AND ASTRONAUTICS
|
| This study compares and contrasts the performance of a variety of rocket and air breathing, single-stage-to-orbit, reusable launch vehicles. Fuels considered include bi-propellant and tri-propellant combinations of hydrogen and hydrocarbon fuels. Astrox Corporation's HySIDE code was used to model the vehicles and predict their characteristics and performance. Vehicle empty mass, wetted area and growth rates were used as figures of merit to predict the procurement, operational and maintenance cost trends ... |
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| Comparative Analysis of Two-Stage-to-Orbit Rocket and Airbreathing Reusable Launch Vehicles for Military Applications |
MAR 2006 |
254 pages |
| Authors:
Joseph M. Hank; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING AND MANAGEMENT
|
| The Department of Defense (DoD) has identified operationally responsive, low-cost access to space as vital to maintaining U.S. military supremacy. Reusable Launch Vehicles (RLVs) will allow the U.S. to keep a technological advantage over our adversaries, and advances in airbreathing propulsion technology have made it feasible for use in space launch vehicles. This study considers two-stage-to-orbit (TSTO) RLV configurations, each using combinations of propulsion including pure rocket, pure turbine, rocket-based-combined-cycle ... |
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| Experimental and Numerical Analysis of Transpiration Cooling of a Rocket Engine Using Lamilloy (Trademark) Plates (PREPRINT) |
18 NOV 2005 |
13 pages |
| Authors:
T. P. Auyeung; R. Cohn; E. Coy; S. A. Danezyk; C. Papesh; P. Sweeney; NORTHROP GRUMMAN SPACE AND MISSILE SYSTEMS CORP REDONDO BEACH CA SPACE TECHNOLOGY
|
| Transpiration cooling of rocket engine thrust chamber walls has the potential for improving the performance of liquid rocket engines by reducing the required cooling flow. For the TR107 hydrocarbon booster engine, it is estimated that replacing the proposed chamber wall film cooling with transpiration cooling could result in an engine Isp increase of 2% to 3%, which provides the potential to increase the maximum booster delivery capability by 4000-5000 lbm. ... |
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| Trajectory Simulations, Qualitative Analyses and Parametric Studies of a Laser-Launched Micro-Satellite Using OTIS |
13 SEP 2005 |
13 pages |
| Authors:
Sean D. Knecht; Jr. Mead Franklin B.; Michael M. Micci; C. W. Larson; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE
|
| This paper will discuss Air Force Research Laboratory (AFRL) Propulsion Directorate's theoretical and computational results regarding trajectory simulations, qualitative analyses and parametric studies of a 25-cm focal diameter Laser Ramjet (X-25LR) using Optimal Trajectories by Implicit Simulation (OTIS). OTIS has been used to produce an optimized trajectory simulation of a laser ramjet's flight to Low Earth Orbit (LEO). The baseline case that has been simulated is a flight vehicle powered ... |
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| Carbon Materials Research |
14 JUL 2005 |
7 pages |
| Authors:
Wesley P. Hoffman; AIR FORCE RESEARCH LAB EDWARDS AFB CA SPACE AND MISSILE PROPULSION DIV
|
| Carbon-carbon composites have been used by the Air Force and others for over 25 years in a variety of thermostructural applications including rocket propulsion, re-entry, hypersonics and aircraft brakes. Although the technology is mature, these materials are still very expensive, have long lead-times, are limited in thickness, are not uniform in density, and cannot be used in an oxidizing environment for extended periods without some type of protection. There is ... |
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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
|
| 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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| Holloman High Speed Test Track Design Manual |
01 MAR 2005 |
83 pages |
| Authors:
TEST GROUP ( 46TH) HOLLOMAN AFB NM
|
| 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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| Program Research and Announcement PRDA 04-01-PKT Integrated High Payoff Rocket Propulsion Technology XI (IHPRPT) |
03 FEB 2004 |
34 pages |
| Authors:
Frank Gulczinaki; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE
|
| The Air Force Research Laboratory, Propulsion Directorate, AFRL/PR- West, Edwards AFB, CA is soliciting unclassified technical and price proposals for the effort described in Section A below. This announcement provides a complete description of the topic, the government projected funding profile and the technology areas to which the topic belongs. Proposals should be addressed to the Contracting POCs and Technical POC stated in the Preface with the appropriate markings. This ... |
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| Combustion Instabilities In Solid Propellant Rocket Motors |
JAN 2004 |
179 pages |
| Authors:
F. E. Culick; CALIFORNIA INST OF TECH PASADENA
|
| These notes for two lectures are intended to provide the basic ideas for understanding and interpreting coherent oscillations is solid propellant rocket motors. The discussion is concerned mainly with the dynamics of a system consisting of two coupled sub-systems: the chamber containing combustion products; and the combustion processes con ned almost entirely to a thin region adjacent to the surface of burning propellant. Coupling between the sub-systems is always present ... |
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| Internal Aerodynamics in Solid Rocket Propulsion (L'aerodynamique interne de la propulsion par moteurs-fusees a propergols solides) (CD-ROM) |
JAN 2004 |
|
| Authors:
NATO RESEARCH AND TECHNOLOGY ORGANIZATION NEUILLY-SUR-SEINE (FRANCE)
|
 | ELECTRONIC FILE CHARACTERISTICS: 318 files; HyperText Markup Language (.HTML), MS PowerPoint SlideShow (.PPS), and Adobe Acrobat (.PDF). PHYSICAL DESCRIPTION: 1 computer laser optical disc (CD-ROM); 4 3/4 in.; 323 MB. SYSTEMS DETAIL NOTE: ABSTRACT: These RTO-AVT/VKI Special Course notes provide the state of the art in internal aerodyanamics in solid rocket propulsion, in a way accessible to attendees coming from both academic and industrial areas. Two families of solid motors ... |
|
| Economics of Test Stand Renovation/Rebuilding |
29 AUG 2003 |
15 pages |
| Authors:
David Harder; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE
|
| This paper provides some background information related to space infrastructure, rocket propulsion and rocket engine testing and discusses some economic considerations in the renovation/rebuilding of rocket engine Test Stands 1D and 2A at Edwards AFB CA. Various means used to minimize renovation/ re-building costs and schedule are discussed as is the current state of the commercial rocket launch business. |
|
| Thermodynamic Limitations on Energy Conversion in Laser Propulsion |
21 AUG 2003 |
24 pages |
| Authors:
C. W. Larson; F. B. Mead Jr.; S. D. Knecht; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE
|
| Outline: Comparison of Constant Momentum Mission and Constant Specific Impulse Mission; Efficiency of conversion of laser energy to propellant kinetic energy; Upper limit to conversion of laser energy to jet kinetic energy from energy conservation and definitions; Comparing momentum quantities to energy quantities. The "Phi Factor" and velocity distributions in propellant jet. Phi values for delta function, Maxwellian, Gaussian, Chunks and gas, supersonic expansion, etc.; Upper limits to performance based ... |
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| Thermodynamic Limitations on Energy Conversion in Laser Propulsion |
21 AUG 2003 |
12 pages |
| Authors:
C. W. Larson; F. B. Mead Jr.; S. D. Knecht; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE
|
| We show that perfect propulsion requires a constant momentum mission, as a consequence of Newton's second law. Perfect propulsion occurs when the velocity of the propelled mass in the inertial frame of reference matches the velocity of the propellant jet in the rocket frame of reference. We compare constant momentum to constant specific impulse propulsion, which, for a given specification of the mission delta V, has an optimum specific impulse ... |
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| New Materials Design |
28 MAY 2003 |
12 pages |
| Authors:
Jerry Boatz; Mark S. Gordon; Gregory Voth; Sharon Hammes-Schiffer; Ruth Pachter; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE
|
| In this paper we report our recent results on the design of materials with controlled properties by the application of computational chemistry methods, new algorithms and scalable software. |
|
| Micro-Thruster Technology for Military Applications |
25 APR 2003 |
48 pages |
| Authors:
J. M. Fife; Andrew Ketsdever; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE
|
| Evolving military doctrine continues to impose ever-more-stressing requirements for greater range and enhanced maneuverability of miniature satellites (picosats, 1-10 kg)-, micro-unmanned air vehicles (UAVs), sensor systems, projectiles, and missiles. To meet these requirements, continuing advances in micro-thruster technology are needed to increase thrust, fuel efficiency, thruster/system controllability, system deployability, and to reduce system weight. Flexible/adaptable micro-thruster technologies that enable on- mission trade-offs between features (e.g., fuel efficiency and thrust) are ... |
|
| 5Klbf Unielement TCA for Film Cooling Model Validation |
24 APR 2003 |
38 pages |
| Authors:
Jeffrey Muss; SIERRA ENGINEERING INC CARSON CITY NV
|
| This document is a report of the 5Klbf Unielement TCA for Film Cooling Model Validation. |
|
| Review of Poss Effects on Polymers and the Future 6.1 Research Direction of the Poss PWG |
10 MAR 2003 |
105 pages |
| Authors:
Rene I. Gonzalex; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE
|
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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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| Near Net-Shape Ultra-High Melting Recession-Resistant Rocket Nozzles II: Low Cost Carbon-Carbon Technology for Use in Ultra-High Temperature Oxidative Environments |
2003 |
20 pages |
| Authors:
W. P. Hoffman; P. G. Wapner; P. J. Wurm; J. R. Schorr; K. H. Sandage; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE
|
| Carbon-carbon composites are ideal materials for high temperature structural uses, such as in rocket propulsion components, hypersonic vehicles, and aircraft brakes. In spite of their excellent properties, the use of carbon- carbon composites has been limited because of their high cost and rapid oxidation at elevated temperatures. Two novel approaches to solving these problems are described and these approaches are employed along with a ZrC/W- based nozzle insert to fabricate ... |
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| Air Force Research Laboratory's Rocket Engine Program Enters Fast-Paced Test Phase |
18 OCT 2002 |
6 pages |
| Authors:
Jeff Thornburg; AIR FORCE RESEARCH LAB EDWARDS AFB CA SPACE AND MISSILE PROPULSION DIV
|
| EDWARDS AFB, Calif. Testing is underway of critical components for integration into the world's first full flow cycle hydrogen/oxygen boost engine. Recent tests of the Integrated Powerhead Demonstration project here established a technical first for the United States and mark the first advancements in boost engine technology since the space shuttle main engine was initially developed in the 1970's. The Department of Defense's Integrated Powerhead Demonstration project developed by the ... |
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| Density Functional Theory Characterization of the Structure and Gas- Phase, Mid-Infrared Absorption Spectrum of 2-Azido-N,N-Dimethylethanamine (DMAZ) |
JUL 2002 |
46 pages |
| Authors:
Michael J. McQuaid; Kevin L. McNesby; Betsy M. Rice; Cary F. Chabalowski; ARMY RESEARCH LAB ABERDEEN PROVING GROUND MD
|
| Non-local density functional theory utilizing the B3LYP exchange- correlation functionals with a 6-311++G(d, p) basis set was employed to characterize the geometric parameters and normal modes of 12 equilibrium conformations of 2-azido-N,N-dimethylethanamine. Also known as DMAZ, an experimentally acquired mid-infrared absorption spectrum of this fuel's vapor is analyzed based on the computational results. The analysis indicates that the relative populations of DMAZ conformers in a room-temperature sample do not deviate ... |
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| New Materials Design |
17 MAY 2002 |
11 pages |
| Authors:
Jerry Boatz; Mark S. Gordon; Gregory Voth; Sharon Hammes-Schiffer; Ruth Pachter; AIR FORCE RESEARCH LAB EDWARDS AFB CA SPACE AND MISSILE PROPULSION DIV
|
| The identification, development, and formulation of new energetic materials for advanced rocket propulsion applications is an area of long standing interest to the Air Force. The performance limits of currently used propellants have been reached, so new energetic compounds are required to significantly improve the ability of the warfighter to access and control space. |
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| Pulse Combustion Rockets for Space Propulsion Applications |
10 MAY 2002 |
|
| Authors:
Edward B. Coy; Douglas G. Talley; Jonathan M. Watts; AIR FORCE RESEARCH LAB EDWARDS AFB CA SPACE AND MISSILE PROPULSION DIV
|
| Pulse combustion propulsion devices are currently being considered as alternatives to conventional constant-pressure engines. Potential advantages include reduction or elimination of pumps and/or compressors, and improved Isp for a given feed system supply pressure. In this paper the authors compare pulse combustors, or constant-volume engines, with pulse detonation engines and discuss why in some applications the former may be the preferred cycle. A model is presented for a monopropellant-fueled, constant-volume, ... |
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| Simulations of Energetic Materials for Rocket Propulsion: Obtaining More "Bang for the Buck" |
29 APR 2002 |
5 pages |
| Authors:
Dan C. Sorescu; Donald L. Thompson; Jerry Boatz; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE WEST
|
| Powderized aluminum has long been used as an energetic ingredient in rocket propellant formulations, comprising approximately 15-20% of some conventional ammonium perchlorate solid propellant formulations. However, the performance of aluminum is reduced by the rapid formation of an aluminum oxide overcoat on aluminum particles prior to combustion, which also inhibits efficient burning. Furthermore, formation of the oxide overcoat severely reduces the potential advantages of using high surface-to-volume-ratio ultrafine aluminum particles, ... |
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| Comparative Lightcraft Impulse Measurements |
13 MAR 2002 |
13 pages |
| Authors:
F. B. Mead Jr.; C. W. Larson; W. M. Kalliomaa; W. O. Schall; H. A. Eckel; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE WEST
|
| The impulse coupling coefficients of two radically different laser propulsion thruster concepts (lightcrafts), each 10 cm in diameter, have been measured under equal conditions using two different pendulum test stands. One test stand and one lightcraft of toroidal shape were provided by the U.S. Air Force Research Laboratory. The other test stand and a bell shaped (i.e. a paraboloid) lightcraft were those of the German Aerospace Center (DLR). All experiments ... |
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| Solar Thermal Propulsion IHPRPT Phase I Demonstration Program |
02 JAN 2002 |
3 pages |
| Authors:
Dean M. Lester; Gregory D. Farmer; Michael R. Holmes; Wayne Wong; THIOKOL PROPULSION BRIGHAM CITY UT
|
| Solar thermal propulsion is an innovative concept that will double the efficiency of currently used LH2 - L02 chemical upper stages. Solar thermal propulsion uses the sun's energy to heat a low molecular weight working fluid such as hydrogen to very high temperatures (3,000 K). The stored thermal energy is then converted to kinetic energy as the working fluid exits a diverging nozzle. This document will report on the completed ... |
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| Investigation of an Alternative Geometry Hybrid Rocket for Small Spacecraft Orbit Transfer |
27 JUL 2001 |
|
| Authors:
Dave M. Gibbon; Gary S. Haag; SURREY SATELLITE TECHNOLOGY LTD GUILDFORD (UNITED KINGDOM)
|
| The following testing was carried out in support of the Surrey Space Centre (SSC) Alternative Geometry Hybrid Rocket research and development program. Although VFP testing was conducted in a low cost environment, the research program collected a wealth of valuable data with regard to this all-new hybrid rocket engine. The combustion efficiency is outstanding within the VFP. The scalability test has demonstrated that the VFP indeed scales well, providing high ... |
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| AFOSR Sponsored Research in Combustion and Diagnostics |
19 JUN 2001 |
2 pages |
| Authors:
Julian M. Tishkoff; AIR FORCE OFFICE OF SCIENTIFIC RESEARCH ARLINGTON VA
|
| The Air Force Office of Scientific Research (AFOSR) program in combustion and diagnostics currently is focused on five areas of study: high-speed propulsion, turbulent combustion, atomization and sprays, diagnostics, and supercritical fuel behavior. An assessment of major research needs in each of these areas is presented. |
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| Characterization of Reduced Toxicity, High Performance Monopropellants at the U.S. Air Force Research Laboratory |
11 JUN 2001 |
10 pages |
| Authors:
T. W. Hawkins; A. J. Brand; M. B. McKay; I. M. K. Ismail; AIR FORCE RESEARCH LAB EDWARDS AFB CA SPACE AND MISSILE PROPULSION DIV
|
| Current U.S. Air Force programs are working to develop reduced toxicity monopropellant formulations to replace spacecraft hydrazine monopropellant and exceed the monopropellant performance objective (greater than 50% increase in density impulse) specified by the Integrated High Payoff Rocket Propulsion Technology (IHPRPT) Program. The creation of such monopropellants can offer considerable cost savings associated with handling and loading, longer spacecraft service life, smaller vehicle design, and heavier payloads. The Air Force ... |
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| Yes--This is Rocket Science: MMCs for Liquid Rocket Engines |
05 JUN 2001 |
49 pages |
| Authors:
J. S. Shelley; R. LeClaire; D. Miracle; J. Nichols; AIR FORCE RESEARCH LAB EDWARDS AFB CA SPACE AND MISSILE PROPULSION DIV
|
| The Air Force's Integrated High-Payoff Rocket Propulsion Technologies (IHPRPT) Program has established aggressive goals for both improved performance and reduced cost of rocket engines and components. Achieving these goals relies on developing affordable Metal Matrix Composite (MMC) technologies for application to Liquid Rocket Engines (LREs). Efforts are being conducted on three types of MMCs: Aluminum, Copper, and Nickel matrix material systems. Potential applications include turbopump housings, rotating machinery, and high ... |
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| IHPRPT Phase I Solid Boost Demonstrator, A Success Story |
JUN 2001 |
8 pages |
| Authors:
Steven R. Glaittli; ATK THIOKOL PROPULSION CORP BRIGHAM CITY UT
|
| The integrated High-Payoff Rocket Propulsion Technology or IHPRPT program seeks to double the launch capability of the United States by the year 2010. The program is organized into three phases, with a technology demonstrator at the end of each phase. The IHPRPT Phase I Solid Boost Demonstrator Program is presented. Materials and processing technologies developed under the IHPRPT program and on other contracted technology and privately funded programs were combined ... |
|
| ARO and AFOSR 2001 Contractors' Meeting in Chemical Propulsion |
JUN 2001 |
185 pages |
| Authors:
David M. Mann; Julian M. Tishkoff; ARMY RESEARCH OFFICE RESEARCH TRIANGLEPARK NC
|
| Abstracts are given for 6.1 basic research in chemical propulsion sponsored by the Army Research Office and the Air Force Office of Scientific Research. |
|
| Bond Dissociation Energies of Energetic Compounds: A Comparison of Theoretical Methods |
23 MAY 2001 |
36 pages |
| Authors:
Jerry Boatz; Donald Thompson; Dan Sorescu; AIR FORCE RESEARCH LAB EDWARDS AFB CA SPACE AND MISSILE PROPULSION DIV
|
|
| Rocket Propulsion Technology Impact on TSTO Launch System Cost |
08 MAY 2001 |
37 pages |
| Authors:
Jason B. Mossman; David R. Perkins; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE WEST
|
| The benefits of advanced liquid rocket propulsion technology are evaluated for two-stage-to-orbit (TSTO) reusable launch systems. Life cycle cost (LCC) is used as a figure-of-merit and is driven by high launch rate requirements. This paper reports the methods and results of that study. The reported analysis focused on chemical rocket propulsion using either hydrogen or hydrocarbon fuels, and oxygen or high purity hydrogen peroxide as oxidizers. Results indicate that advanced ... |
|
| The Launch of Gorizont 45 on the First Proton K/Breeze M |
03 APR 2001 |
|
| Authors:
Fred D. Rosenberg; MASSACHUSETTS INST OF TECH LEXINGTON LINCOLN LAB
|
| On 6 June 2000 Russia launched Gorizont 45 using the newly developed Breeze M upper stage. It was the first non-historic deep space Russian launch in many years. However, International Launch Services published detailed description of the booster capabilities and launch scenarios. Pre-mission planning led to successful coverage of the rocket body and payload up to synchronous injection. |
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| Solar Rocket Propulsion. Ground and Space Technology Demonstration |
29 MAR 2001 |
14 pages |
| Authors:
Michael Holmes; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE WEST
|
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Reports by Keyword(s)
ROCKET PROPULSION
