| Contamination and Micropropulsion Technology |
Jul 2012 |
135 pages |
| Authors:
Andrew Ketsdever; Sergey Gimelshein; Natalia Gimelshein; Taylor Lilly; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIR
|
 | The growing interest in the use of microspacecraft within government and industry is driving a critical need for new propulsion systems capable of fulfilling a wide range of mission requirements. The applicability of each propulsion system is highly mission dependent and subject to system constraints. The purpose of this research was to investigate the design, fabrication, and microspacecraft systems limitations associated with the scaling of micropropulsion devices. |
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| Investigation of Innovative Lightcraft Designs for Hypersonic Air Breathing and Rocket Flight by Beamed Energy Propulsion |
Jun 2012 |
251 pages |
| Authors:
Con Doolan; Vince Wheatley; David Froning; ADELAIDE UNIV (AUSTRALIA)
|
| The report has three parts: 1) Lightcraft inlet design: The work outlines the innovative streamtraced design methodology and a number of suitable lightcraft inlet designs. It also contains an analysis of laser detonation, a system level analysis of lightcraft flight and analysis of a ground test model. 2) Experimental ground testing. The lightcraft design documented in Part 1 was tested at the University of Southern Queensland's hypersonic test facility. This ... |
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| Methane Dual Expander Aerospike Nozzle Rocket Engine |
22 Mar 2012 |
131 pages |
| Authors:
Michael D Moen; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH GRADUATE SCHOOL OF ENGINEERING AND MANAGEMENT
|
| The Air Force Institute of Technology (AFIT), working to meet requirements set by the Air Force Research Laboratory's Next Generation Engine (NGE) initiative, is developing upper stage rocket models. The current path of investigation focuses on combining a dual expander cycle with an aerospike nozzle, or the Dual Expander Aerospike Nozzle (DEAN) using methane fuel. The design process will rely heavily on AFIT's previous work, which focused on the development ... |
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| An Overview of Advanced Concepts for Launch |
09 Feb 2012 |
36 pages |
| Authors:
Marcus Young; Jason Mossman; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIR/SPACE AND MISSILE PROPULSION DIV/AEROPHYSICS BRANCH
|
| This briefing presented an overview of advanced concepts for launch at AFRL. It explored the launch problem and the nanoLaunch problem, then discussed advanced concepts for cost effective launch/nanoLaunch. |
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| Accuracy and Best Practices for Small-Scale Rocket Engine Testing |
10 Nov 2011 |
31 pages |
| Authors:
Malissa Lightfoot; Stephen A Danczyk; Jon Watts; S A Schumaker; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIR/SPACE AND MISSILE PROPULSION DIV
|
| An in-depth analysis of the uncertainties associated with small-scale rocket engine testing has been conducted. The analysis uses terminology and approaches detailed in the ISO 'Guide to the Expression of Uncertainty in Measurement' (GUM) and a recent NASA handbook on the subject (NASA HBK-8739.19-3). Along with this analysis, best practices for minimizing uncertainties are provided. AFRL's Experimental Cell-1 facility is used as the example engine, and the data values provided ... |
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| Injector-Wall Interactions in Gas-Centered Swirl Coaxial Injectors |
08 Nov 2011 |
23 pages |
| Authors:
Malissa D Lightfoot; Larry A Villasmil; S A Schumaker; Stephen A Danczyk; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE
|
| Rocket engines often rely on tailoring wall elements to provide a fuel-rich wall environment or to cool the wall or both. Due to their importance in protecting the wall, it is imperative that the behavior of these elements is understood. The nearby wall may alter the performance from that of a single, isolated element. Most experiments are not designed to elucidate these effects; either single, isolated elements are examined, or ... |
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| High Energy Advanced Thermal Storage for Spacecraft Solar Thermal Power and Propulsion Systems |
28 Oct 2011 |
45 pages |
| Authors:
David B Scharfe; M P Young; M R Gilpin; R Webb; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIR/SPACE AND MISSILE PROPULSION DIV/AEROPHYSICS BRANCH
|
| Previous reviews have identified solar thermal propulsion (STP) as a promising candidate for high performance microsatellite missions, due to its high delta-v capability with a quick response time, relatively high thrust and efficiency, and low mass fraction for high capability. However, there are drawbacks to solar thermal propulsion, outlined in this presentation. Augmented STP is proposed and described. |
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| Accuracy and Best Practices for Small-Scale Rocket Engine Testing |
19 Oct 2011 |
48 pages |
| Authors:
M D Lightfoot; S A Danczyk; J M Watts; S A Schumaker; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE
|
| An in-depth analysis of the uncertainties associated with small-scale rocket engine testing has been conducted. The analysis uses terminology and approaches detailed in the ISO ?Guide to the Expression of Uncertainty in Measurement? (GUM) and a recent NASA handbook on the subject (NASA HBK-8739.19-3). Along with this analysis, best practices for minimizing uncertainties are provided. AFRL?s Experimental Cell-1 facility is used as the example engine, and the data values provided ... |
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| The Effect of Swirl on Gas-Centered Swirl Coaxial Injector Sprays |
13 Oct 2011 |
12 pages |
| Authors:
Malissa D Lightfoot; S A Schumaker; Larry A Villasmil; Stephen A Danczyk; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE
|
| Gas-centered swirl coaxial injector design criteria and scaling laws have been developed by AFRL over the last several years. These studies have predominately focused on the measurement and behavior of the liquid film and its relation to atomization efficiency. The spread and quality of the spray as well as its stability have received less attention. These parameters are the focus here and are shown to support the conclusions drawn from ... |
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| Technical Review Board Chairperson Guidelines for Conducting Technical Review Boards for Rocket Testing |
17 Aug 2011 |
64 pages |
| Authors:
Daniel C Harbour; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE
|
| The purpose of this study is to create a guide for technical review board chairperson conducting technical review boards for rocket testing performed by the Air Force Research Laboratory's Space & Missile Propulsion Division located at Edwards Air Force Base in California. Technical review boards are independent reviews of the test programs, providing a crucial check and balance in the program's overall systems engineering and quality process. As will be ... |
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| Molten Boron Phase-Change Thermal Energy Storage to Augment Solar Thermal Propulsion Systems |
13 Jul 2011 |
|
| Authors:
Matthew R Gilpin; David B Scharfe; Anthony P Pancotti; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE
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| Solar thermal propulsion offers a unique combination of high thrust and high specific impulse levels that can provide competitive advantages relative to traditional satellite propulsion systems. In order to enhance the functionality of this technology, thermal storage combined with a means of thermal-to-electric conversion is suggested, with the idea of providing a dual-mode power and propulsion system based on thermal energy. A system including boron phase change material for storing ... |
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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
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| 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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| Advancing Reusable Booster System (RBS) Technologies and Capabilities with a Space Tourist Suborbital Vehicle |
Apr 2011 |
14 pages |
| Authors:
Barry Hellman; Craig Remillard; Khaki McKee; Mark Street; AIR FORCE RESEARCH LAB WRIGHT-PATTERSON AFB OH AIR VEHICLES DIRECTORATE
|
| The Air Force is pursuing a Reusable Booster System (RBS) to meet future responsive launch needs. These needs include 'within days' reconstitution, flexibility, adaptability, and assuredness. This report discusses how the aeromechanic technologies from a suborbital space tourist vehicle are being studied to further develop the aeromechanic technologies of the RBS concept. |
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| Propulsion Systems |
31 MAR 2011 |
71 pages |
| Authors:
Ivett A. Leyva; Marcus Young; Jr. Hargus William A.; Richard Van Allen; Charles M. Zakrzwski; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIR/SPACE AND MISSILE PROPULSION DIV/AEROPHYSICS BRANCH
|
| This chapter starts with a review of the basic rocket performance parameters, the rocket equation and staging. Different classes of chemical rockets used for space propulsion are then examined. The System Design Elements section guides the reader on how to size common components for a conventional chemical propulsion system. Electric propulsion and other potential new systems are presented next. This chapter concludes with two examples of preliminary designs for a ... |
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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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| Optimized Dual Expander Aerospike Rocket |
Mar 2011 |
303 pages |
| Authors:
Joshua N Hall; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH DEPT OF AERONAUTICS AND ASTRONAUTICS
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| Research at the Air Force Institute of Technology (AFIT) focused on designing a cryogenic dual-expander aerospike nozzle (DEAN) upper stage rocket engine to produce 50,000 pounds-force (222.4 kilo-Newtons) vacuum thrust, 464 seconds of vacuum specific impulse and a thrust-to-weight ratio of 106.5. The use of dual expander cycles improves engine reliability, maximizes efficiency, and eliminates some catastrophic failure modes. An upper stage engine with an aerospike nozzle is shorter and ... |
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| Using a Gatling-Gun Configured Micro Pulsed Plasma Thruster as a Means to Control Micro Satellites with Extreme Precision |
Mar 2011 |
119 pages |
| Authors:
Lee I Watson; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH GRADUATE SCHOOL OF ENGINEERING AND MANAGEMENT
|
| Micro-Pulsed Plasma Thrusters (muPPT) are becoming increasingly attractive for their low power consumption and moderately high specific impulse from 800-1000s. The Gatling Gun micro-Pulsed Plasma Thruster (GG-muPPT) is a new device offering reduced mass and higher thrust than single muPPTs in precise pointing and orbit maintenance applications. The performance of muPPTs depends on frequency and applied voltage/power levels. A variation of these input parameters and effects on operation and performance ... |
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| Mixing Under Transcritical Flow Conditions |
MAR 2011 |
105 pages |
| Authors:
Sebastien Candel; J. Rodriguez; T. Schmitt; ECOLE CENTRALE PARIS CHATENAY-MALABRY (FRANCE) LAB DES MATERIAUX
|
| The project focused on the mixing behavior of fluids under transcritical flow conditions. This topic is relevant to rocket propulsion applications and it is also applicable to other high pressure systems such as gas turbine combustors. Extensive work in this general area of propulsion has been performed at the EM2C (Energetique, Moleculaire, Macroscopique et Combustion) laboratory at Ecole Centrale Paris (ECP) which has suitable complemented the experimental work that has ... |
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| Initial Assessment of the Operational Reusable Booster System (RBS) Rocketback |
Mar 2011 |
30 pages |
| Authors:
Barry Hellman; Jon Wallace; Brad St Germain; AIR FORCE RESEARCH LAB WRIGHT-PATTERSON AFB OH AIR VEHICLES DIRECTORATE/STRUCTURES DIVISION
|
| The U.S. Air Force is pursuing a reusable booster system (RBS) to meet future responsive launch needs. An RBS consists of a reusable booster with and expendable upper stage. To meet operability and life cycle cost (LCC) goals, the current approach is for the RBS to return to the launch site (RTLS) after releasing the upper stage to avoid the need of operating a downrange base and avoiding the cost ... |
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| Simulation of Electric Propulsion Thrusters (Preprint) |
07 FEB 2011 |
30 pages |
| Authors:
Iain D. Boyd; MICHIGAN UNIV ANN ARBOR DEPT OF AEROSPACE ENGINEERING
|
| Electric propulsion thrusters are replacing small chemical thrusters used for spacecraft control and orbital maneuvers. These thrusters use a variety of mechanisms to convert electrical power into thrust and in general provide superior specific impulse in comparison to chemical systems. Electric propulsion has been under development for the last fifty years, and almost all thrusters are designed based largely on experience and experimentation. The present article considers the progress made ... |
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| Measurement of the Effectiveness of Concave Spherical Dimples for the Enhancement of Hot-gas Side Heat Transfer |
31 JAN 2011 |
13 pages |
| Authors:
Edward B. Coy; Stephen A. Danczyk; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE
|
| In an expander cycle rocket engine, the turbo-pump is driven by a gaseous propellant that has been heated in channels incorporated into the thrust chamber wall. The power output of the turbine islimited by the hot gas wall heat transfer coefficient and surface area. To increase the chamber pressure, additional pump power and heat are required. Part of the increase can come from an increased heat transfer coefficient at elevated ... |
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| Flow Structure and Acoustics of Supersonic Jets from Conical Convergent-Divergent Nozzles |
Jan 2011 |
14 pages |
| Authors:
D Munday; E Gutmark; J Liu; K Kailasanath; CINCINNATI UNIV OH APPLIED SCIENCE RESEARCH LAB
|
| Conical convergent-divergent (CCD) nozzles represent an important category of supersonic jet-engine nozzles which require variable throat areas and variable exit areas to adapt to a range of operating conditions. CCD nozzles with design Mach numbers of 1.3, 1.5, and 1.65 are examined experimentally over a range of fully expanded Mach numbers from 1.22 to 1.71. The characteristics of the flow and acoustic fields from these nozzles are explored. Shadowgraph, Particle ... |
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| Mission Capability Gains from Multi-Mode Propulsion Thrust Profile Variations for a Plane Change Maneuver |
29 DEC 2010 |
14 pages |
| Authors:
Tiffany Rexius; Michael R. Holmes; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIR/SPACE AND MISSILE PROPULSION DIV
|
| Plane change maneuvers are very costly in terms of propellant required. Performing a plane change can quickly drain a spacecraft's propellant required. The utilization of a multi-mode propulsion (MMP) system could greatly reduce the amount of propellant required for the maneuver. MMP refers to a propulsion system that couples an electric and chemical propulsion system which utilizes the same propellant and piping. A fully coupled system provides many advantages over ... |
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| Development of Terahertz Rayleigh Scattering Diagnostics for a Solid Rocket Exhaust Plume |
28 Oct 2010 |
83 pages |
| Authors:
Anthony T O'Shea; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE
|
| This research proposes a new technique using terahertz radiation and Rayleigh scattering off of particulates in the plume. This technique is limited to firing the beam straight across the plume. Terahertz radiation wavelengths in relation to alumina particle sizes align with the Rayleigh criterion, which requires that the wavelength of light be at least ten times greater than the radius of the particle. Rayleigh scattering would allow for changing the ... |
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| Stage Separation Failure: Model Based Diagnostics and Prognostics |
Oct 2010 |
10 pages |
| Authors:
Dmitry Luchinsky; Vasyl Hafiychuk; Igor Kulikov; Vadim Smelyanskiy; Ann Patterson-Hine; John Hanson; Ashley Hill; NATIONAL AERONAUTICS AND SPACE ADMINISTRATION MOFFETT FIELD CA AMES RESEARCH CENTER
|
| Safety of the next-generation space flight vehicles requires development of an in-flight Failure Detection and Prognostic (FD&P) system. Development of such system is challenging task that involves analysis of many hard hitting engineering problems across the board. In this paper we report progress in the development of FD&P for the re-contact fault between upper stage nozzle and the inter-stage caused by the first stage and upper stage separation failure. A ... |
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| Magnetohydrodynamic Augmentation of Pulse Detonation Rocket Engines (Preprint) |
28 Sep 2010 |
36 pages |
| Authors:
Jean-Luc Cambier; Christopher F Zeineh; Lord K Cole; Timothy Roth; Ann R Karagozian; CALIFORNIA UNIV LOS ANGELES DEPT OF MECHANICAL AND AEROSPACE ENGINEERING
|
| Pulse detonation engines (PDEs) are the focus of increasing attention due to their potentially superior performance over constant pressure cycle engines. Yet due to its unsteady chamber pressure, the PDE system will either be over- or under-expanded for the majority of the cycle, with energy being used without maximum gain. Magnetohydrodynamic (MHD) augmentation offers the opportunity to extract energy and apply it to a separate stream where the net thrust ... |
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| Mitigation of Fuel Fire Threat to Large Rocket Motors by Venting |
01 Sep 2010 |
33 pages |
| Authors:
Kenneth J Graham; AIR FORCE RESEARCH LAB EDWARDS AFB CA MOTOR BRANCH
|
| Venting of a container such as a rocket motor or a warhead case is a well-recognized method to potentially reduce the violent response of the system to a fuel fire threat. There have been many proposed rocket motor or warhead venting systems. The thermally-initiated venting system (TIVS) on the AMRAAM rocket motor has been shown to reduce violent response, by cutting the case with a linear shaped-charge. Graham has demonstrated ... |
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| Design and Analysis of an Electron Gun/Booster and Free Electron Laser Optical Theory |
Sep 2010 |
263 pages |
| Authors:
Sean P Niles; NAVAL POSTGRADUATE SCHOOL MONTEREY CA
|
| As interest in high power free electron lasers (FELs) has increased, the FEL and accelerator communities have been faced with the need to develop high bunch charge, high repetition rate, low emittance electron sources for use as the driving accelerators for FELs. A novel superconducting, radio-frequency (SRF) gun/booster has been designed by and built for the Naval Postgraduate School (NPS) FEL Beam Physics Lab in collaboration with Niowave, Inc., for ... |
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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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| Optimal Vehicle Design Using the Integrated System and Cost Modeling Tool Suite |
Aug 2010 |
46 pages |
| Authors:
Michael O'Such; ADVATECH PACIFIC INC PALMDALE CA
|
| The Review of the U.S. Human Spaceflight Plans Committee found that the space exploration plans set forth in 2009 were unsustainable and is forcing NASA to rethink its plans and focus on realistic estimates for its programs. The Air Force is facing similar problems due to continuing delays in completing programs and cost overruns. The Constellation program, which was to develop the Ares I, the heavy-lift vehicle Ares V, the ... |
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| Cookoff Results of Sub-Scale Hazard Division 1.3 Propellant Samples |
Jul 2010 |
46 pages |
| Authors:
Eric Wilson; Matthew Gross; Ephraim Washburn; Eric Sievert; Daniel Wooldridge; John Daly; Scott Barry; J Covino; NAVAL AIR WARFARE CENTER WEAPONS DIV CHINA LAKE CA
|
| A hazardous materials siting effort by the National Aeronautics and Space Administration (NASA), the Naval Air Warfare Center Weapons Division (NAWCWD), Hughes & Associates, Inc., and Alliant Techsystems Inc. (ATK), indicated that inadvertent ignition of a rocket in the Vehicle Assembly Building (VAB) at Kennedy Space Center (KSC) might cause other rockets in the facility to burn. Currently, the Space Shuttle Program (SSP) builds and stores rockets in the VAB. ... |
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| Development of an Alternative for the External Means of Initiation for Hazard Classification of Rocket Motors |
Jul 2010 |
23 pages |
| Authors:
K P Ford; C E Lovern; T J Schilling; D B Crutcher; A I Atwood; N L Purcell; T R Taylor; J H France; R S Henry; J Covino; NAVAL AIR WARFARE CENTER WEAPONS DIV CHINA LAKE CA
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| The purpose of this report is the rewrite of TB 700-2 requires single package test, sympathetic reaction test if expected outside reaction, Large diameter rocket motors, not transported or stored in stack configuration, alternate test used, and super large scale gap test. |
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| Terahertz Rayleigh Scattering of Particles in Rocket Exhaust Plumes |
17 Jun 2010 |
13 pages |
| Authors:
A O'Shea; T Mulcahy; H Song; A Ketsdever; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE
|
| Characterization of particles in solid rocket plumes has been difficult due to the lack of real-time measurement techniques. This research proposes a new technique using terahertz radiation and Rayleigh scattering on alumina particulates in the plume. Previous techniques have involved collecting particles on a probe or mesh. Others have used Mie scattering using lasers, but this technique is limited to firing the beam straight across the plume. Terahertz radiation wavelengths ... |
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| Assessment of the Compositional Variability of RP-1 and RP-2 with the Advanced Distillation Curve Approach |
21 Apr 2010 |
30 pages |
| Authors:
Bret C Windom; Tara M Lovestead; Jennifer R Riggs; Christopher Nickell; Thomas J Bruno; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE
|
| RP-1 is a long-established hydrocarbon fuel that continues to be widely used as the kerosene component in rocket propulsion systems. The desire in recent years to use rocket motors many times, rather than a single time, has led to reformulations of RP-1. In terms of processing, increased hydro-treating of the component feedstock fluids used in the manufacture of RP-1 can lower the sulfur, olefin and aromatic content significantly. The resulting ... |
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| Atomization Uniformity in Gas-Centered Swirl-Coaxial Injectors |
17 Mar 2010 |
11 pages |
| Authors:
Malissa D Lightfoot; S A Schumaker; Stephen A Danczyk; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE
|
| There are two important aspects to good injector performance in rocket engines-the atomization performance (droplet size and distribution, for example) and uniformity of operation (even distribution of droplets in time and space). In general, both of these aspects are affected by the geometry and operating conditions of the injector. In studying atomization performance, prior work has largely focused on the atomization performance, partially because uniformity, especially temporal uniformity, can be ... |
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| Design of a Film Cooling Experiment for Rocket Engines |
Mar 2010 |
155 pages |
| Authors:
Andrew L Sincock; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH GRADUATE SCHOOL OF ENGINEERING AND MANAGEMENT
|
| The Film Cooling Rig (FCR) is a new test rig at the Air Force Institute of Technology (AFIT) to study film cooling for rocket engine applications. The original researcher designed, built, and then utilized the FCR to study radial curvature effects on film cooling for a non-combustion environment. This effort modified the FCR by adding propane-air combustion. Modular stainless steel test sections were produced to allow study of various curvatures ... |
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| A Model of High-Pressure Ablative Capillary Discharge for Plasma Thrusters with Capillary Wall Thermal Conduction and Radiation Absorption (Preprint) |
03 Feb 2010 |
17 pages |
| Authors:
L Pekker; O Pekker; ENGINEERING RESEARCH AND CONSULTING INC (ERC INC) EDWARDS AFB CA
|
| A zero-dimensional time-dependent high-pressure slab capillary discharge model with capillary wall thermal conduction and radiation absorption is presented. The model includes a resistor-inductor-capacitor circuit and a heat-transfer radiation model based on a radiation database constructed using PrismSPEC, a commercially available radiation software, to calculate the radiation heat flux output from a uniform plasma slab. The model also includes a model of the thin transition boundary layer between the uniform plasma ... |
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| Spacelift Development Plan |
02 Feb 2010 |
12 pages |
| Authors:
SPACE AND MISSILE SYSTEMS CENTER LOS ANGELES AFB CA
|
| This briefing discusses the Air Force Space Command's (AFSPC's) Spacelift Development Plan. The AFSPC seeks to have affordable responsive lift for a full range of payloads. Thus it is studying a range of vehicle options -- expendable boosters, partially reusable vehicles with reusable main booster and expendable upper stages, and fully reusable vehicles. Gen. Kehler's perspective is given. |
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| HIFiRE Flight 2 Flowpath Design Update (PREPRINT) |
Dec 2009 |
17 pages |
| Authors:
Mark R Gruber; Paul Ferlemann; Keith McDaniel; AIR FORCE RESEARCH LAB WRIGHT-PATTERSON AFB OH PROPULSION DIRECTORATE
|
| This paper describes the evolution of various aspects of the flowpath design as the payload system design has matured. Forebody design changes were required in order to reduce the overall payload system weight and to meet shroud design requirements. In response to the forebody design changes, modifications were made to the fuel injectors within the combustor as the captured air mass flow rate reduced. No additional changes were made to ... |
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| International Symposium on Special Topics in Chemical Propulsion (8th): Advancements in Energetic Materials and Chemical Propulsion Held in Cape Town, South Africa on 2-6 November 2009 |
06 Nov 2009 |
196 pages |
| Authors:
Kenneth K Kuo; Hansie van Knoetze; Deon Zyl; PENNSYLVANIA STATE UNIV UNIVERSITY PARK DEPT OF MECHANICAL AND NUCLEAR ENGINEERING
|
| In order to promote technical communication and to encourage further advancements of new energetic materials and chemical propulsion, the International Advisory Committee for the Foundation of International Symposium on Special Topics in Chemical Propulsion conducted the International Symposium on Special Topics in Chemical Propulsion (8-ISICP) in Cape Town, South Africa from November 2-6, 2009. During the 4-day technical program, 79 papers were presented (including 9 Invited Papers) on 18 different ... |
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| High Frequency Combustion Instability Studies of LOX/Methane Fueled Rocket Engines |
25-Sep-2009 |
28 pages |
| Authors:
Robert J Santoro; PENNSYLVANIA STATE UNIV UNIVERSITY PARK
|
| A series of studies were conducted using a rectangular rocket chamber burning LOX methane propellanrs to investigate the effect of the temperature of the methane on the lunation of combustion instability The rectangular rocket used in these studies employed LOX centered coaxial swirl injectors The rectangular injector used in these studied provided 16 possible injector element locations in a linear array. Variation of injector element location showed that injector elements ... |
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| Integrated Analysis of Scramjet Flowpath and Innovative Inlets (Preprint) |
Sep 2009 |
10 pages |
| Authors:
Datta V Gaitonde; F J Malo-Molina; Daniel Risha; H Ebrahimi; AIR FORCE RESEARCH LAB WRIGHT-PATTERSON AFB OH AIR VEHICLES DIRECTORATE
|
| An overview is presented of fundamental and practical insights obtained on scramjet flowpaths during a three year Challenge Project utilizing high fidelity methodologies and advanced postprocessing techniques. Simulations are employed to analyze the principal phenomena, including inlet distortion, fuel-air mixing, ignition and thrust generation at freestream Mach numbers between 6 and 8. In addition to guiding the evolution and execution of high-speed ground and flight experiments, the discovery objective of ... |
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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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| Performance and Analysis of Vortex Oxidizer Injection in a Hybrid Rocket |
05 May 2009 |
170 pages |
| Authors:
Charles C Jones; NAVAL ACADEMY ANNAPOLIS MD
|
| A hybrid rocket motor is a type of rocket motor where fuel is placed in a combustion chamber as a solid, and then gaseous or liquid oxidizer is injected. When the two mix and are ignited, the surface of the fuel burns and the gases produced in the combustion develop thrust. Hybrid rocket motor performance is dictated by the rate at which the fuel burns. Fuel burn rate (or regression ... |
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| Micro-Propulsion Devices in Low Temperature Co-Fired Ceramics |
27-Feb-2009 |
8 pages |
| Authors:
Amy J Moll; Judi Steciak; Donald G Plumlee; BOISE STATE UNIV ID
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| Three supersonic nozzle configurations were developed and tested using the LTCC materials system. An isentropic model was generated to determine the overall size of each nozzle and the nozzle curvature was defined using a Method of Characteristics approach. Each nozzle was tested using a cold gas test stand at several pressures. The experimental thrust measurement was compared to the isentropic model and several 3D CFD models. A schlieren visualization system ... |
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| High-Density Renewable Fuels Based on the Selective Dimerization of Pinenes |
Jan-2009 |
8 pages |
| Authors:
Benjamin G Harvey; Michael E Wright; Roxanne L Quintana; NAVAL AIR WARFARE CENTER WEAPONS DIV CHINA LAKE CA
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| High-density fuel candidates have been synthesized in up to 90% yield from beta-pinene, a renewable strained bicyclic compound derived from wood and plant sources. The process is based on the heterogeneous acidic catalysts Montmorillonite-K10 and Nafion, which promote selective isomerization and dimerization of pinenes under moderate conditions (100-deg C and atmospheric pressure). Montmorillonite-K10 was shown to be a highly active catalyst for dimerization but was also active in the ring ... |
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| An Update of the Nation's Long-Term Strategic Needs for NASA's Aeronautics Test Facilities |
Jan 2009 |
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| Authors:
Philip S Anton; Raj Raman; Jan Osburg; James G Kallimani; RAND CORP SANTA MONICA CA
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 | The National Aeronautics and Space Administration's (NASA's) major wind tunnel (WT), propulsion test (PT), and simulation facilities exist to serve NASA's and the nation's aeronautics needs. RAND Corporation researchers conducted a prior study of these facilities from 2002 to 2003, identifying (1) NASA's continuing ability to serve national needs, (2) which facilities appear strategically important from an engineering perspective given the vehicle classes the nation investigates and produces, and (3) ... |
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| Enhanced Passive Thermal Propulsion System |
Jan 2009 |
21 pages |
| Authors:
Dwight Warner; Ellis Warner; TUSAIRE INC ELK RIVER MN
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| The long term goal is to advance our understanding of thermal energy extraction from the ocean thermocline using an enhanced passive thermal propulsion system. Integration of this new propulsion technology in a low drag hydrodynamic shape is expected to yield undersea glider speeds in excess of 3 Knots (5 Knots may be achievable), and persistence measured in years. Higher speeds will allow: Enhanced glider operations in currents, Increased measurement rate ... |
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Rocket Engines
