| Solid State Digital Propulsion Cluster Thrusters for Small Satellites Using High Performance Electrically Controlled Extinguishable Solid Propellants |
JUN 2005 |
7 pages |
| Authors:
Wayne N. Sawka; Arthur Katzakian Jr.; CHarles Grix; AIR FORCE RESEARCH LAB EDWARDS AFB CA
|
 | Electrically controlled extinguishable solid propellants (ESCSP) are capable of multiple ignitions, extinguishments and throttle control by the application of electrical power. Both core and end burning no moving parts ECESP grains/motors to three inches in diameter have now been tested. Ongoing research has led to a newer family of even higher performance ECESP providing up to 10% higher Isp, manufacturing ease, and significantly higher electrical conduction. The high conductivity was ... |
|
| Design of Injectors for Self-Sustaining of Combustion Chambers Acoustic Stability |
22 JUN 2004 |
25 pages |
| Authors:
Vladimir Bazarov; MOSCOW INST OF AVIATION TECHNOLOGY (USSR)
|
| Comparative analysis of the injector development history in order to eliminate acoustic instability in combustion chambers of LOX/kerosene big thrust engines both of gas generator and staged combustion cycle such as F-1, RD-170 and some experimental engines is presented in the Paper. It was studied what stationary and dynamic parameters of injector elements and the injector assembly as a whole were changed during such a development and what kind of ... |
|
| Modelling of Axial Magnetic Field Effect on Electric Arc in Ablation Capillaries |
07 APR 2004 |
2 pages |
| Authors:
A. Wolny J. Piotrowski; GDANSK TECHNICAL UNIV (POLAND)
|
| Modelling of the axial magnetic field effect on the arc voltage of an arc burning in a gas-evolving chamber using Niemeyer's model of ablation arcs is discussed. The results support the assumption that the arc voltage rise is due to the increasing gas generation. |
|
| Analytic Modeling and Experimental Validation of Intumescent Behavior of Charring Heatshield Materials |
JAN 2004 |
142 pages |
| Authors:
Gerald W. Russell; ARMY AVIATION AND MISSILE COMMAND REDSTONE ARSENAL AL
|
| Intumescing heatshield materials have been shown to provide significant thermal protection for missile system environments. The design and use of these materials requires the analytic understanding of a considerable level of thermodynamic phenomena occurring on the surface, as well as in-depth. These phenomena can include in-depth thermochemical decomposition, pyrolysis gas generation and mass transfer, thermophysical property change, thermochemical and mechanical ablation, intumescence or conduction path growth, and boundary layer modification ... |
|
| Simplified Liquid Rocket Engine Performance and Weight Model |
25 APR 2003 |
|
| Authors:
Wendel M. Burkhardt; Eric Paulson; Steve Mysko; Tim Jenkins; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE
|
 | The Air Force Research Laboratory is developing a tool to analyze liquid propellant launch systems. This tool, called Integrated Propulsion Analysis Tool (IPAT), requires the capability to predict the weight of the vehicle components as well as the performance of the rocket engines. For IPAT, a simplified model was developed to predict liquid rocket engine (LRE) performance and weight. The LRE model was developed to be very flexible and model ... |
|
| Pressure Effects on Hydrogen Peroxide Decomposition Temperature |
AUG 2002 |
15 pages |
| Authors:
Raymond F. Walsh; Alan M. Sutton; SCHAFER CORP CALABASAS CA
|
| The use of very high concentration hydrogen peroxide (e.g., 98%) in rocket engines yields substantial specific impulse (Isp) gains when compared with traditional 90% peroxide engine systems. However, when used in pump-fed engines, 98% peroxide places a significant design burden on the turbine from a material strength and oxygen compatibility standpoint. The decomposition temperature for 98% peroxide is ^1240 K (^2230 R), a temperature regime in which most alloys show ... |
|
| Dynamic Rupture Strength of Lacquer Seal in Flash Tube of 30-mm Ammunition for the M230 Cannon |
MAY 2002 |
22 pages |
| Authors:
Stephen L. Howard; ARMY RESEARCH LAB ABERDEEN PROVING GROUND MD
|
| The M788, M789, and M799 30 mm ammunition use a flash tube to augment the ignition stimulus of the primer and to provide an ignition source for the propellant bed in each round. The flash tube must be fast acting, provide abundant hot gases/particles, and increase the pressure in the propellant bed sufficiently that the initial burn rate of the propellant in the bed is high enough to propel the ... |
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| Telescoping Pressure Balanced Gas Generators Launchers for Underwater Use |
20 AUG 2001 |
24 pages |
| Authors:
Brenda B. Macleod; Jeffrey L. Cipolla; DEPARTMENT OF THE NAVY WASHINGTON DC
|
| A launching apparatus including a launch tube having a fore end and an aft end, each end having an opening formed therein. A muzzle cap is fit to the fore end of the launch tube and a breech mounting is formed at the aft end of the launch tube. A primary plenum housing is seated in the aft end of the launch tube, the primary housing having a fore end ... |
|
| Transient Application, Recirculating Pool Fire, Agent Effectiveness Screen: Final Report, NGP Project 3A/890 |
APR 2001 |
89 pages |
| Authors:
William Grosshandler; Anthony Hamins; Kevin McGrattan; Cary Presser; NATIONAL INST OF STANDARDS AND TECHNOLOGY GAITHERSBURG MD BUILDING AND FIRE RESEARCH LAB
|
| In this study, a laboratory-scale facility has been developed to screen the suppression effectiveness of agents that are delivered in a transient fashion such as solid propellant gas generators. The transient application, recirculating pool fire (TARPF) agent effectiveness screen features a propane fire stabilized behind an obstruction, which is known to be a highly challenging suppression configuration. The character of the flame and the impact of the air flow, fuel ... |
|
| A System Dynamics Approach to Modeling Temperature Effects in Solid Waste Landfills |
20 MAR 2001 |
203 pages |
| Authors:
David A. Jokinen; AIR FORCE INST OF TECH WRIGHT-PATTERSONAFB OH
|
| The amount of municipal solid waste discarded to landfills is continually increasing even with extensive recycling efforts. The need to understand the behavior of waste in landfills is increased due to the decreasing number of active landfills, communities' concern to the potential hazards associated with landfills, and companies or installations with landfills on-site need to understand landfill behavior comply with new legislation concerning design and detecting hazardous material movement of-site. ... |
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| Machinery Monitoring Technology Design Methodology for Determining the Information and Sensors Required for Reduced Manning of Ships |
JUN 2000 |
|
| Authors:
Brian P. Murphy; MASSACHUSETTS INST OF TECH CAMBRIDGE
|
| A method is developed for determining how to implement sensors and data fusion systems for shipboard use in new or backfit warship designs. The underlying goal of proper implementation of new automation systems is to improve the operational readiness of the ship while simultaneously reducing crew size and operating costs. The thesis entails defining the method and then using it to determine the information requirements for the ... |
|
| Chemical Mechanisms at the Burning Surface |
31 MAY 2000 |
7 pages |
| Authors:
Thomas B. Brill; DELAWARE UNIV NEWARK DEPT OF CHEMISTRY
|
| This research program was devoted to the study of high-nitrogen compounds that have been of worldwide interest as gas generators, explosives, and propellants. The focus was specifically on substituted tetrazole and furazan ring compounds. The Russian FLAME database reveals that many of these compounds have high burning rates. In the United States these compounds are of interest to AFRL, Los Alamos National Laboratory, and the Thiokol Corporation ... |
|
| Aging Systems in Aeronautics and Space Damage Tolerance in Helicopters |
APR 2000 |
9 pages |
| Authors:
Paolo Santini; NORTH ATLANTIC TREATY ORGANIZATION CORFU (GREECE) APPLIED VEHICLE TECHNOLOGY PANEL
|
| The aim of this keynote lecture should be that of introducing the main (or, at least,the common) features of the papers that will be presented during the Workshops that will take place in Corfou this week: Aging Aeronautical Systems, Life Extension for Helicopters, Propulsion and Gas Generators for aerospace vehicles. A keynote lecture may be given in several ways. The most obvious form is probably an overview of the subjects ... |
|
| Effects of Moisture Content in Solid Waste Landfills |
MAR 2000 |
116 pages |
| Authors:
Craig P. Eck; AIR FORCE INST OF TECH WRIGHT-PATTERSONAFB OH SCHOOL OF ENGINEERING
|
| Solid waste landfills are an extremely complex and heterogeneous environment. Modeling the biodegradation processes within a landfill must involve an understanding of how environmental factors affect these processes. Arguably, the most important environmental factor influencing biodegradation processes is solid waste moisture content. This research effort, which is an extension of a system dynamics model previously presented by Colborn (1997) and amended by Benter (1999), ... |
|
| Vortex Ring Generator: Mechanical Engineering Design for 100-kpsi Operating Pressures |
JAN 2000 |
52 pages |
| Authors:
George K. Lucey Jr; ARMY RESEARCH LAB ADELPHI MD
|
| This report documents engineering design guidelines used to construct an explosive gas generator (100 kpsi maximum) and an adjustable area ratio (2844 maximum) nozzle. The equipment enables ring vortices to be generated using jet streams with significantly higher Mach numbers than previously reported in the literature. Studies are planned of the risks, limits, and capabilities of ring vortices for nonlethal crowd control applications. The focus is limited ... |
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| Method and Apparatus for Retaining Wires in a Cylindrical Tube |
24 AUG 1999 |
|
| Authors:
Craig S. Mello; DEPARTMENT OF THE NAVY WASHINGTON DC
|
| A submarine signal launcher is disclosed for preventing pinched control wires therein. The submarine signal launcher includes a gas generator, an acoustic device countermeasure, a launch tube for housing the gas generator and the countermeasure, and a ram plate positioned between the gas generator and the countermeasure. A status cable is connected to the countermeasure and intermediately threaded through the ram plate and joined to the gas generator. A collapsible ... |
|
| Underwater Projectile Launcher |
29 JUN 1999 |
|
| Authors:
Jeffrey L. Cipolla; DEPARTMENT OF THE NAVY WASHINGTON DC
|
| Disclosed is an underwater gas generator projectile launcher which includes a tubular barrel having a forward muzzle end and an opposed rearward end. A projectile is positioned in this tubular barrel adjacent the forward end An expellable closure for the forward muzzle end of the barrel means is provided. A projectile propelling piston assembly is positioned in the tubular barrel and includes a shell axially movable in the tubular barrel. ... |
|
| Structural Assessment of Solid Propellant Grains (l'Evaluation structurale des blocs de poudre a' propergol solide) |
DEC 1997 |
|
| Authors:
ADVISORY GROUP FOR AEROSPACE RESEARCH AND DEVELOPMENT NEUILLY-SUR-SEINE (FRANCE)
|
| Solid propellant rocket motors and gas generators are used in military and civil devices. Missiles, boosters, space propulsion, pyrotechnic actuators are examples. The structural capability of the grain over time and under varying temperature, humidity, and mechanical loads, is of prime concern for the reliability, safety and service life of the device. From 1994 to 1996 an AGARD working group has collected, reviewed and evaluated the methods used for structural ... |
|
| FY98 Aero Propulsion & Power Technology Area Plan |
NOV 1997 |
38 pages |
| Authors:
AIR FORCE RESEARCH LAB WRIGHT-PATTERSON AFB OH PROPULSION DIRECTORATE
|
| The Aero Propulsion and Power Technology Area is responsible for developing air breathing propulsion and power technology for Air Force use. Besides developing new technologies, product centers are supported by helping acquire systems and providing expertise to help solve developmental problems. current research and development includes aircraft gas turbine engines components, gas generators, technology demonstrator engines, fuels and lubricants), missile propulsion, solid fuel ramjets, ducted rockets, and small turbine engines) ... |
|
| Method and Apparatus for Retaining Wires in a Cylindrical Tube |
09 OCT 1997 |
14 pages |
| Authors:
Craig S. Mello; DEPARTMENT OF THE NAVY WASHINGTON DC
|
| A submarine signal launcher is disclosed for preventing pinched control wires therein. The submarine signal launcher includes a gas generator, an acoustic device countermeasure, a launch tube for housing the gas generator and the countermeasure, and a ram plate positioned between the gas generator and the countermeasure. A status cable is connected to the countermeasure and intermediately threaded through the ram plate and joined to the gas generator. A collapsible ... |
|
| Design and Construction of a Thermophotovoltaic Energy Conversion System Using Combustion Gases from a T-58 Gas Turbine |
07 MAY 1997 |
92 pages |
| Authors:
Timothy A. Erickson; NAVAL ACADEMY ANNAPOLIS MD
|
| An ongoing project at the U.S. Naval Academy involves the development of a prototype ThermoPhotovoltaic (TPV) generator that uses a General Electric T-58 gas turbine as the heat source. The combustion gas was tapped from the T- 58's combustor through an ignitor port and then extracted through a silicon carbide composite tube into a ceramic emitter. The emitter was also made from the same silicon carbide composite. The TPV generator ... |
|
| Advanced Fire Suppression Technology (AFST) Research and Development Program |
APR 97 |
33 pages |
| Authors:
M. A. Wilson; J. D. Moran; OLIN AEROSPACE CO REDMOND WA
|
| Halon 1301 has been widely used in aircraft fire suppression systems because of its ability to efficiently extinguish fires. Unfortunately, halon production was banned in 1994 because it is an ozone depleting substance. The ban on halon production has created a need for alternative fire suppression technologies in both the military and civilian aircraft industries. Solid Propellant Gas Generators (SPGG) is a viable alternative to halon for in-flight fire suppression. ... |
|
| Nuclear Weapons: Capabilities of DOE's Limited Life Component Program to Meet Operational Needs |
MAR 97 |
9 pages |
| Authors:
GENERAL ACCOUNTING OFFICE WASHINGTON DC RESOURCES COMMUNITY AND ECONOMIC DEVE LOPMENT DIV
|
| The Department of Energy (DOE) is responsible for managing the nation's nuclear weapons stockpile, including a limited life components program. That program involves the periodic replacement of four components that have useful operating lives shorter than the expected life of a nuclear weapon. If these components are not replaced within a specified time, the weapon would eventually become inoperative. The number and type of nuclear weapons to be managed by ... |
|
| Ballistic Analysis of Electrothermal-Chemical (ETC) Propellant |
DEC 96 |
42 pages |
| Authors:
Gloria P. Wren; William F. Oberle; Sharon L. Richardson; ARMY RESEARCH LAB ABERDEEN PROVING GROUND MD
|
| Firings performed under the alternate electrothermal-chemical (ETC) propellant materials contract with the Olin Corporation investigated a number of propellants using both conventional and plasma driven combustion. The objectives of this paper are to utilize the test series to examine: (1) ignition characteristics of plasma driven propellants; (2) pressurization rates of propellants under the influence of a plasma; (3) control of the gas generation rate in the gun with a plasma; ... |
|
| FY97 Aero Propulsion and Power Technology Area Plan |
AUG 96 |
40 pages |
| Authors:
WRIGHT LAB WRIGHT-PATTERSON AFB OH
|
| The Aero Propulsion and Power Technology Area is responsible for developing air breathing propulsion and power technology for Air Force use. Besides developing new technologies, product centers are supported by helping acquire systems and providing expertise to help solve developmental problems. current research and development includes aircraft gas turbine engines (components, gas generators, technology demonstrator engines, fuels and lubricants), missile propulsion, (solid fuel ramjets, ducted rockets, and small turbine engines) ... |
|
| External Combustion Engine Having An Asymmetrical Cam and Method of Operation. |
12 MAR 1996 |
|
| Authors:
Anthony W. Duva; DEPARTMENT OF THE NAVY WASHINGTON DC
|
| An external combustion engine having an asymmetrical cam. The engine includes a combustion chamber for generating a high-pressure, energized gas from a monopropellant fuel and an even number of cylinders for sequentially receiving the energized gas through a rotary valve, the gas performing work on a piston disposed within each cylinder The pistons transfer energy to a drive shaft through a connection to the asymmetrically shaped cam. The cam is ... |
|
| Computed In-Flight Temperature Response of a 120-mm XM797 Gas Generator Training Round Nose Cap |
OCT 95 |
45 pages |
| Authors:
Bernard J. Guidos; ARMY RESEARCH LAB ABERDEEN PROVING GROUND MD
|
| A computational study is presented of the aerothermal response of an XM797 gas generator nosecap. The XM797 nosecap is a critical component in the design of a 1 2O-mm finned kinetic energy (KE) training round projectile. A propellant-filled chamber within the nosecap is designed so that aerodynamic heating ignites the propellant down range, initiating projectile breakup. The objective of this study is to provide the nosecap temperature response, which is ... |
|
| FY96 Aero Propulsion and Power Technology Area Plan (TAP) |
JUL 95 |
36 pages |
| Authors:
WRIGHT LAB WRIGHT-PATTERSON AFB OH
|
| The Aero Propulsion and Power Technology Area is responsible for developing air breathing propulsion and power technology for Air Force use. Besides developing new technologies, product centers are supported by helping acquire systems and providing expertise to help solve developmental problems. Current research and development includes aircraft gas turbine engines (components, gas generators, technology demonstrator engines, fuels and lubricants) , missile propulsion, (solid fuel ramjets, ducted rockets, and small turbine ... |
|
| International Annual Conference of ICT (26th), (Pyrotechnics - Basic Principles, Technology, Application) Held at Karlsruhe, Federal Republic of Germany on July 4 - July 7, 1995 |
95 |
1104 pages |
| Authors:
FRAUNHOFER-INST FUER CHEMISCHE TECHNOLOGIE BERGHAUSEN (GERMANY F R)
|
| Partial contents: Development of an extrudable composite cordlike gas-generating propellant; Influence of the binder content on the reaction behaviour of pyrotechnic mixtures; New concepts in development of explosives devices; An experimental investigation of the acceleration induced burning rate increase of composite solid propellants for gas generator; Pyrotechnic smokes for screening - a summary; A hybrid gas generator using low concentration hydrogen peroxide of inflating airbags; An influence off the chemical ... |
|
| Energy Supply Alternatives for the Year 2002 at the U.S. Military Academy (USMA) |
OCT 94 |
112 pages |
| Authors:
Mike C. Lin; Mike Binder; Richard G. Andersen; CONSTRUCTION ENGINEERING RESEARCH LAB (ARMY) CHAMPAIGN IL ENERGY AND UTILITI ES SYSTEMS DIV
|
| The U.S. Military Academy (USMA) is concerned about how to meet present and future energy demands as the existing generating equipment and distribution facilities age. To help the installation develop an energy supply plan, the USMA asked the U.S. Army Construction Engineering Research Laboratories to determine options for future energy supply, taking into consideration both the projected increases in energy demands and the Army's energy conservation goals. Researchers considered 68 ... |
|
| Advanced Fire Suppression Technology (AFST) Research and Development |
SEP 94 |
52 pages |
| Authors:
Robert M. Mitchell; OLIN AEROSPACE CO REDMOND WA
|
| The advanced fire supression technology (AFST) research and development program is being conducted by Olin Aerospace Research and Development program is being conducted by Olin Aerospace Company for WPAFB. The three phase program goal is to evaluate the effectiveness of gas generator technology in suppressing aircraft drybay and engine nacelle fires. This report presents the activities of phase 1, including an initital evaluation of non- filtered solid propellant gas generators, ... |
|
| Performance Oriented Packaging Testing of Container, Shipping and Storage, MK 723 MOD 0 for Packing Group II Solid Hazardous Materials |
JAN 94 |
7 pages |
| Authors:
Karen McDonnell; NAVAL WEAPONS STATION EARLE COLTS NECK NJ
|
| This Performance Oriented Packaging (POP) test was conducted to ascertain whether the Mk 723 Mod 0 Shipping and Storage Container (Drawing JCM- 14219) meets the Packing Group 11 requirements specified by the Code of Federal Regulations, Title 49 CFR, Parts 106 through 178, dated 1 October 1992. The packaged commodity used for the test was an inert gas generator weighing 91 kg (200 pounds). This represents the current maximum commodity ... |
|
| Area Handbook Series: Persian Gulf States Country Studies |
JAN 93 |
480 pages |
| Authors:
Helen C. Metz; LIBRARY OF CONGRESS WASHINGTON DC FEDERAL RESEARCH DIV
|
| THE COUNTRIES OF THE PERSIAN GULF covered in this volume-Bahrain, Kuwait, Oman, Qatar, and the United Arab Emirates-have assumed added prominence as a result of Operation Desert Shield in 1990 and the Persian Gulf War in 1991. These states share certain characteristics while simultaneously differing from one another in various respects. Islam has played a major role in each of the Persian Gulf states, although Kuwait and Bahrain reflect a ... |
|
| Propellant Grain Assembly for a Gas Generator. |
07 APR 1992 |
|
| Authors:
Kenneth E. Adams; DEPARTMENT OF THE NAVY WASHINGTON DC
|
| A gas generator for a long range missile is driven by a solid propellant grain assembly which includes a cylindrical inhibitor, a forward closure assembly that is attached to one end of the inhibitor and a propellant grain that is cast into the cylindrical cavity formed by the interior surface of the cylindrical inhibitor. Between the grain and inhibitor and between the grain and forward closure assembly is an adhesive ... |
|
| Burst Diaphragm Sequence Valve. |
12 NOV 1991 |
|
| Authors:
Bradley D. Wisneskie; Sheldon Hyman; Charles E. Hallum; DEPARTMENT OF THE NAVY WASHINGTON DC
|
| A burst diaphragm sequence valve which effectively combines the structure of a burst diaphragm with that of an ordinary swing check valve, the pivot of the ordinary swing check valve being replaced by an integral flexural hinge. The sequence valve provides a way to sequentially burn solid propellant hot gas generators which exit into a common gas manifold, thereby enabling gas-powered devices to operate for a longer time than the ... |
|
| Solid-Propellant-Powered Maneuvering System for Spacecraft. |
05 NOV 1991 |
|
| Authors:
Charles W. Goddard; John T. Lucas; Paul A. Galvan; DEPARTMENT OF THE NAVY WASHINGTON DC
|
| An improvement to a variable-pressure solid-propellant-powered maneuvering system for spacecraft, enabling the system to operate for longer than one propellant burn time. At least two solid propellant gas generators are connected via a manifold to a plurality of nozzle valve clusters; at least one of the gas generators is connected to the manifold via a sequence valve which isolates that generator from the manifold until such time as it is ... |
|
| Experimental Investigation of a 16 Inch Diameter Water Piston Propulsor at Speeds up to 23 Feet Per Second and Gas Temperatures up to 3600 F |
MAY 91 |
|
| Authors:
V. E. Johnson Jr.; R. A. Barr; D. Kowalyshyn; R. Bateman; TRACOR HYDRONAUTICS INC LAUREL MD
|
| The Water Piston Propulsor (WPP) combines prime mover, transmission, and propulsor into a single unit. High pressure heated gas is expanded directly on columns of water so as to add momentum to ingested fluid and thereby produces thrust. The WPP theoretically has a very high power per unit volume and power per unit weight if the gas can be transmitted to the rotor with minor pressure loss and if the ... |
|
| Performance Oriented Packaging Testing of MS-27684-2 Metal Drum for MK 64 Mod 0 Gas Generator |
APR 91 |
9 pages |
| Authors:
Billie Landstrom; NAVAL WEAPONS SUPPORT CENTER CRANE IN
|
| Qualification tests were performed to determine whether the MS-27684- 2 Metal Drum used for MK 64 MOD 0 Gas Generator meets the Performance Oriented Packaging (POP) requirements specified by the United Nations Recommendations on the Transportation of Dangerous Goods. The container loaded to a gross weight of 50.7 pounds successfully met the requirements and retained its contents throughout the tests. |
|
| A Computer Program for Prediction of Internal Performance of a Ramrocket |
APR 91 |
|
| Authors:
Lincoln P. Erm; AERONAUTICAL RESEARCH LABS MELBOURNE (AUSTRALIA)
|
| The operation of a computer program to predict idealised ramrocket performance is described. The program predicts performance for chosen aerodynamic and thermodynamic variables and contains provision for varying the gas generator propellant formulation. |
|
| Thermal Energy Storage and Heat Transfer Support Program. Task-5. Heat Pipe Life Test Study. Facilities Upgrading and Maintenance |
01 MAR 91 |
|
| Authors:
R. Ponnappan; UNIVERSAL ENERGY SYSTEMS INC DAYTON OH
|
| This report describes the recommissioning, upgrading, and maintaining of thirty low and five high temperature heat pipe life test rigs. This is an ongoing research effort, originally put together by NASA LeRC, continued by the Air Force. The 92 cm long 1.27 cm dia. spacecraft-type heat pipes have completed nearly 74,000 hours of life tests. They exhibit varying Delta Ts across the length and symptoms of gas accumulation. Life test ... |
|
| Self-Sealing Separation Fastener for Small Confines. |
22 JAN 1991 |
|
| Authors:
Martin E. Moore; Robert R. Bennett; DEPARTMENT OF THE NAVY WASHINGTON DC
|
| A separable fastener includes a fastener body having a head end and a shank end. The head end defines a generally cylindrical open ended cavity in which a cylindrical punch is disposed. The cavity is sealed and closed by a gas generator that develops an increasing fluid pressure against the punch. The punch is restrained within the cavity by a retaining ring which yields once a preselected gas pressure is ... |
|
| Potential Application of Magnetohydrodynamic Acceleration to Hypersonic Environmental Testing |
AUG 90 |
99 pages |
| Authors:
R. A. Crawford; J. N. Chapman; R. P. Rhodes; ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFS TN
|
| This investigation reviews the technical results from previous MHD accelerator research and conducts a theoretical analysis of the simulation capabilities of an MHD-augmented hypersonic flow facility. This investigation identified the performance potential of MHD accelerator and hot gas generator combinations subject to reasonable constraints from available technology. The performance goal was to extend the hypersonic flight simulation limits from Mach 10 to Mach 25. The results of this investigation identified ... |
|
| Analysis of the Flight Performance of the 155 mm M864 Base Burn Projectile |
APR 90 |
55 pages |
| Authors:
James E. Danberg; ARMY BALLISTIC RESEARCH LAB ABERDEEN PROVING GROUND MD
|
| An engineering model has been developed to compute the flight performance of the M864 base burn projectile. This model includes the coupled performance of the gas generator, effects of injected mass flow on the aerodynamics, and a modified point mass trajectory simulation. The gas generator model is based on measured burn rates and basic fluid dynamics. The discharge rate of the generator is calibrated against laboratory experiments. Effects of spin ... |
|
| An Experimental Investigation into NO sub X Control of a Gas Turbine Combustor and Augmentor Tube Incorporating a Catalytic Reduction System |
MAR 90 |
|
| Authors:
Christopher K. Behrens; NAVAL POSTGRADUATE SCHOOL MONTEREY CA
|
| An initial experimental investigation was conducted to examine the feasibility of NOx emission control using catalytic reduction techniques in the jet engine test cell environment., A modified T-63 gas turbine combustor and an augmentor tube, 21 feet in length and containing a perlite catalyst, were used as a gas generator and catalytic reduction system. Four data runs were made. Three runs were completed without the catalyst installed. Temperature and velocity ... |
|
| Cycle Analysis for Helicopter Gas Turbine Engines |
APR 89 |
|
| Authors:
A. D. Bewley; ROYAL AEROSPACE ESTABLISHMENT FARNBOROUGH (ENGLAND)
|
| The performance potential of a 1000 kW gas turbine engine is determined in terms of specific fuel consumption and specific power. Compressor and turbine efficiencies are assumed size dependent and the cycle temperature is determined from the material capability and cooling technology available. Simple cycle and heat exchanger cycles engines for helicopters are considered. In the near term, engines with a two-stage gas generator turbine and uncooled power turbine offer ... |
|
| W-Bank Varactor-Tuned Oscillators with 10 GHz Bandwidth. |
OCT 1988 |
|
| Authors:
|
|
| DC to 20 GHz Monolithic GaAs FET Switches Based on Quarter-Micron Gates. |
AUG 1988 |
|
| Authors:
G. Dawe; D. Bartle; F. Spooner; ALPHA INDUSTRIES INC WOBURN MA
|
|
| Advanced Air Separation Module Performance Evaluation |
JUL 88 |
215 pages |
| Authors:
Charles L. Anderson; BOEING ADVANCED SYSTEMS CO SEATTLE WA
|
| Results of an experimental performance evaluation of two advanced lightweight permeable membrane(PM) air apace modules(ASM) are presented. ASMs produce nitrogen enriched air which is used for airplane fuel tank inerting. The airplane inerting system is termed On-Board Inert Gas Generator System (OBIGGS). ASMs were obtained from two sources: A/G Technology Corp. and Permea Inc Steady state performance envelope, long term endurance, hot/cold start-up on/off cycling, moisture, vibration, contaminant, and high ... |
|
| Speed Control of a Missile with Throttleable Ducted Rocket Propulsion, |
DEC 1987 |
|
| Authors:
Dieter Thomaier; MESSERSCHMITT-BOELKOW-BLOHM G M B H MUNICH (GERMANY F R)
|
| The wide range of altitudes, in which many missiles must be operational, makes the variation of thrust mandatory and leads ultimately to the control of propellant mass flow. With the choice of a solid propellant ducted rocket as propulsion system, the gasgenerator must produce a variable mass flow rates. The widely applied method uses a propellant with a pressure sensitive burning rate. A valve with variable throat area controls the ... |
|
| Proceedings of the Conference on Toxicology Held in Dayton, Ohio on 28- 30 October 1986 |
DEC 87 |
374 pages |
| Authors:
Donald E. Gardner; William E. Houston; Raymond S. Kutzman; NORTHROP SERVICES INC-ENVIRONMENTAL SCIENCES DAYTON OH
|
| This series of manuscripts from the 16th Conference on Toxicology addresses critical research and development issues for improving the scientific capability to predict potential health risks associated with various occupational and environmental exposures. To meet the needs of the Department of Defense, these contributions focus on the current knowledge of the health effects of a variety of chemical substances which are either used in military systems or generated during military ... |
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Reports by Keyword(s)
GAS GENERATING SYSTEMS
