| A Theory for Optical Flow-based Transport on Image Manifolds |
21 Nov 2011 |
38 pages |
| Authors:
Sriram Nagaraj; Aswin C Sankaranarayanan; Richard G Baraniuk; RICE UNIV HOUSTON TX DEPT OF ELECTRICAL AND COMPUTER ENGINEERING
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 | An image articulation manifold (IAM) is the collection of images formed when an object is articulated in front of a camera. IAMs arise in a variety of image processing and computer vision applications, where they provide a natural lowdimensional embedding of the collection of high-dimensional images. To date IAMs have been studied as embedded submanifolds of Euclidean spaces. Unfortunately their promise has not been realized in practice, because real world ... |
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| The Impact of Manifold-to-Orifice Turning Angle on Sharp-Edge Orifice Flow Characteristics in both Cavitation and Non-Cavitation Turbulent Flow Regimes (Preprint) |
JUN 2007 |
21 pages |
| Authors:
W. H. Nurick; T. Ohanian; D. G. Talley; P. A. Strakey; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE
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| The approach taken was to analyze the results in a manner consistent with application by design engineers to new and existing applications, while providing some insight into the processes that are occurring. This paper deals with predicting the initiation of cavitation, cavitation impacts on Cc, and non-cavitation impacts on Cd from L/D of 5 sharp-edge orifices with both single angle and compound angle directional flow. The results show that in ... |
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| Investigation of Possible Decomposition of Alternative Fire- Extinguishing Agents Discharged Through a Vehicle Personnel Heater |
OCT 96 |
49 pages |
| Authors:
Kevin L. McNesby; Steven H. Modiano; Paul Marsh; William Bolt; Craig Herud; ARMY RESEARCH LAB ABERDEEN PROVING GROUND MD
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| Fourier transform infrared (FT-IR) spectroscopy was used to monitor the possible thermal decomposition of alternative fire-extinguishing agents discharged through a vehicle personnel heater. The agent was introduced into the heater air induction pen and flowed across the heat exchanger manifold. Gas samples were removed from the hot air output duct extension of the heater via stainless steel tubing and flowed through a 1Om path-length multipass optical gas cell placed in ... |
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| Aerosol Dispensing Apparatus for Dispensing a Medicated Vapor into the Lungs of a Patient. |
JAN 1996 |
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| Authors:
Guy F. Cooper; DEPARTMENT OF THE NAVY WASHINGTON DC
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 | A dispensing apparatus comprising a reservoir for providing a medication under pressure and a housing which has a centrally located chamber and a wave shaping chamber located in a front portion of the housing. Positioned between the wave shaping chamber and the centrally located chamber is a blast valve. The plunger of a reciprocating piston has a vertical extending support member attached to its front end. A power supply provides ... |
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| Velocity Characteristics of Dividing Flow in a T-Junction, |
23 JUL 1992 |
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| Authors:
H. Fu; A. P. Watkins; M. J. Tindal; M. Yianneskis; KING'S COLL LONDON (UNITED KINGDOM)
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| This paper presents in experimental investigation of the flows in a T-junction from a model of an internal combustion engine manifold. The flow patterns though the main duct and one branch of the manifold were measured using laser-Doppler anemometry. Detailed measurements of the mean velocity components and corresponding turbulence levels were obtained in order to characterize the flow and provide benchmark data appropriate for the development and assessment of the ... |
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| Incremental Maneuver Estimation Model for Target Tracking. |
APR 1992 |
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| Authors:
W. T. Chang; S. A. Lin; NATIONAL CHIAO TUNG UNIV HSINCHU (TAIWAN)
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| Solid-Propellant-Powered Maneuvering System for Spacecraft. |
05 NOV 1991 |
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| Authors:
Charles W. Goddard; John T. Lucas; Paul A. Galvan; DEPARTMENT OF THE NAVY WASHINGTON DC
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| 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 ... |
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| Intake Structure Operation Study Elk Creek Dam, Oregon |
SEP 90 |
50 pages |
| Authors:
Stacy E. Howington; ARMY ENGINEER WATERWAYS EXPERIMENT STATION VICKSBURG MS HYDRAULICS LAB
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| Elk Creek Dam, presently under construction in the Rouge River Basin , Oregon, will be operated for multiple purposes including flood control and fish and wildlife enhancement. Flood control will dictate the quantity of water released; and fish and wildlife enhancement, the water quality. Selective withdrawal will be used to control the dam's release water temperature, which is important to the anadromous fishery in the Rogue River. When selective withdrawal ... |
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| NAHBE (Naval Academy Heat Balanced Engine) M151 Retrofit Evaluation |
15 AUG 1983 |
75 pages |
| Authors:
A. A. Pouring; C. C. Failla; SONEX RESEARCH INC ANNAPOLIS MD
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| NAHBE (Naval Academy Heat Balanced Engine) state of the art technology was applied to a standard military four cylinder M-151-1/4 Ton Utility Truck (Jeep) to demonstrate retrofitted versus standard engine performance in waterbrake and chassis dynamometers as well as on the road. Chassis dyno results showed a maximum possible retrofit improvement in miles per gallon of 21.3% at 55 mph and 35.4% at 30 mph. Waterbrake dyno results show higher ... |
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| Fuel Valve. |
01 FEB 1983 |
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| Authors:
Raymond L. Williams; DEPARTMENT OF THE AIR FORCE WASHINGTON DC
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| This invention is a spring-biased valve assembly that will not corrode, gall, or otherwise wear, and that is for use in selectively controlling a flow of liquid fuel. The valve assembly, in its preferred embodiment, is eminently suitable for use in a gas turbine engine to keep the fuel manifold of the afterburner full when not operating, and to effectuate equal distribution of the fuel flow to a plurality of ... |
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| Injector/Chamber Scaling Evaluation. |
AUG 1972 |
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| Authors:
Roy A. Silver; AIR FORCE ROCKET PROPULSION LAB EDWARDS AFB CA
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| This report describes the results of the testing performed at the Air Force Rocket Propulsion Laboratory. The purpose of this program was to demonstrate the performance, stability, injector/chamber compatibility and long-duration operation of low-cost scalable pressure-fed engines which use storable propellants. Tests were conducted at the 250,000-pound-thrust level with thrust chamber assemblies using two different design approaches: a pintle injector designed by TRW Systems and a modular injector designed by ... |
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| UpSTAGE Technology Report: Special Manufacturing and Fabrication Processes, |
JUL 1972 |
429 pages |
| Authors:
D. E. Schwab; MCDONNELL DOUGLAS ASTRONAUTICS CO-HB HUNTINGTON BEACH CA
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| In the conduct of the UpSTAGE Experiment, a number of special manufacturing processes were developed to meet the advanced state-of-the-art performance requirements of the interceptor design. Significant technological advances in materials processing were made to enable the successful manufacture of fuel tanks, fuel manifold frames, thick-film electronic assemblies, heat shield insulation, internal hot gas duct insulation, and solid propellant booster motors. A description of these process developments emphasizes the methods ... |
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| Advanced Maneuvering Propulsion Technology Program Interim Materials and Processes Report. |
OCT 1970 |
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| Authors:
ROCKETDYNE CANOGA PARK CALIF
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| Materials and processes developed and used to fabricate segments of a LF2/LH2 aerospike thrust chamber assembly, nozzle extension, injectors and bearings and seals for LF2 turbopumps are presented. A brief design description of each item is provided. The materials used included OFHC copper, Nickel 200, electrodeposited nickel, CRES 347 and 304L, and Inconel 718. The processes include electrodeposition (electroforming), stretch forming, explosive forming, electro-discharge machining, brazing, and welding. (Author) |
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| Altitude Developmental Testing of the J-2S Rocket Engine in Rocket Development Test Cell (J-4) (Tests J4-1001-06, -07, -11, and -15). |
SEP 1970 |
118 pages |
| Authors:
C. E. Pillow; ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFS TN
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| Eleven firings of the Rocketdyne J-2S rocket engine were conducted. These firings were accomplished at pressure altitudes ranging from 80,000 to 108,000 ft at engine start signal. The major objectives for these tests were to verify stable idle-mode operation, confirm that oxidizer injection temperatures were not excessive during transition from main-stage to post-main-stage idle-mode operation, evaluate main-stage performance, and determine the rate at which thrust chamber temperature increased during pre-main-stage ... |
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| High Temperature Hydrocarbon Fuels Research in an Advanced Aircraft Fuel System Simulator on Fuel AFFB-12-68 |
FEB 1970 |
109 pages |
| Authors:
Harold Goodman; Royce P. Bradley; NORTH AMERICAN ROCKWELL CORP LOS ANGELES CA LOS ANGELES DIV
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| Hydrocarbon jet fuels tend to form deposits at elevated temperatures that decrease heat exchanger efficiency and plug screens and filter elements. The Advanced Aircraft Fuel System Simulator provides generalized performance data, with respect to thermal stability, on various advanced fuels that will be used to correlate to small-scale test results and provide information on design criteria for future supersonic aircraft. In this report, the thermal stability of the fifth fuel ... |
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| Injector/Chamber Scaling Evaluation-TRW Injector Development. |
OCT 1969 |
78 pages |
| Authors:
Bernard R. Bornhorst; Michael F. Powell; Donald A. Grimes; Mitchell J. Fleiszar Jr.; Patrick W. Powell; AIR FORCE ROCKET PROPULSION LAB EDWARDS AFB CALIF
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| This report describes the results of TRW injector development tests. This project, a task under the overall Minimum Cost Design Space Launch Vehicle (MCD/SLV) Program, has as a goal the development of low-cost injectors capable of performing at 90% theoretical Isp (shifting), 250,000-lb thrust using N2O4/UDMH propellants, and will evaluate their scalability up to the multimillion-lb-thrust class. A total of seven injector and three chamber configurations were tested. Maximum performance ... |
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| Advancement of Injector and Thrust Chamber Technology. |
DEC 1967 |
|
| Authors:
G. A. Voorhees Jr; TRW SYSTEMS REDONDO BEACH CALIF
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| This report covers an experimental test program to determine the scalability of the LMDE centrally located, coaxial injector to much higher thrust levels than previously tested. A 250,000 lbf thrust, 300 psia chamber pressure Thrust Chamber Assembly (TCA) was fabricated and tested at a reduced thrust level of approximately 50,000 lbf thrust. The TCA design consisted of a centrally located coaxial injector, based upon the LMDE design, and heat sink ... |
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| ADVANCED CRYOGENIC ROCKET ENGINE PROGRAM AEROSPIKE NOZZLE CONCEPT -- MATERIALS AND PROCESSES |
NOV 1967 |
188 pages |
| Authors:
F. B. Lary; ROCKETDYNE CANOGA PARK CA
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| Reported herein are the results of Materials and Processes effort related to development and fabrication of experimental Aerospike thrust chamber hardware. This report includes information relative to the selection of materials and information concerning the fabrication of the 250K combustor bodies and injectors, the development of the small tapered thrust chamber tubes, and the development of tooling and successful brazing of the small tubes to backup structure, and the injectors. ... |
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| HIGH TEMPERATURE HYDROCARBON FUELS RESEARCH IN AN ADVANCED AIRCRAFT FUEL SYSTEM SIMULATOR ON FUEL AFFB-8-67 |
SEP 1967 |
108 pages |
| Authors:
Harold Goodman; Royce P. Bradley; Theodore G. Sickles; NORTH AMERICAN AVIATION INC LOS ANGELES CA LOS ANGELES DIV
|
| At elevated temperatures hydrocarbon jet fuels tend to form deposits which decrease heat exchanger efficiency and plug screens and filter elements. A small-scale device is required which has been demonstrated to be applicable to all qualities of hydrocarbon jet fuels and will quantify this tendency in terms meaningful to fuel system designers. In this report, the thermal stability of a fuel (AFFB-8-67) is quantified in terms of amount of deposit ... |
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| ADVANCED CRYOGENIC ROCKET ENGINE PROGRAM, AEROSPIKE NOZZLE CONCEPT. |
JUN 1967 |
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| Authors:
F. B. Lary; ROCKETDYNE CANOGA PARK CALIF
|
| This program includes analysis and preliminary design of an advanced rocket engine using an Aerospike nozzle and experimental evaluation of critical technology related to the Aerospike concept. Component and system features, physical arrangements, and design parameters and details have been established for an optimum demonstrator engine. Studies of application of a flight engine to certain vehicles are completed. Experimental injector performance investigations on segment chambers and material studies are completed. ... |
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| CELLULAR COMBUSTION CHAMBER PROGRAM (PROJECT SCORPIO). A SIMPLIFIED CLUSTERING TECHNIQUE FOR ROCKET ENGINE MODULES |
MAR 1966 |
120 pages |
| Authors:
Daweel George; Lester E. Tepe; Vernon L. Mahugh; Howard V. Main; AIR FORCE ROCKET PROPULSION LAB EDWARDS AFB CA
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| Results of the tests and evaluations performed on (1) a simplified clustering technique for rocket engine modules, (2) single modules utilizing simplified large thrust per element injectors and film-cooled thrust chambers, and (3) a unique thrust vectoring mechanism known as the CAM Ring Gimbal are presented. The high-energy, cryogenic propellant combination of liquid oxygen and liquid hydrogen was used throughout. |
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| DEVELOPMENT OF A SUPERSONIC TRANSPORT AIRCRAFT ENGINE. PHASE II-C. |
10 FEB 1966 |
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| Authors:
PRATT AND WHITNEY AIRCRAFT WEST PALM BEACH FLA FLORIDA RESEARCH AND DEVELOPMENT CENTER
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| DEVELOPMENT OF A SUPERSONIC TRANSPORT AIRCRAFT ENGINE. PHASE II-C. |
10 JAN 1966 |
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| Authors:
PRATT AND WHITNEY AIRCRAFT WEST PALM BEACH FLA FLORIDA RESEARCH AND DEVELOPMENT CENTER
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| ULTIMATE LOAD TEST OF THE 7-31-21 PROTOTYPE LIGHT WEIGHT THRUST STRUCTURE, |
22 APR 1959 |
|
| Authors:
P. F. Niesen Jr; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
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| Ultimate loading conditions are the same as the corresponding limit loading conditions, except the ultimate loads are twenty-five percent higher. This test is required to: Verify the structural integrity of the thrust structure when it is subjected to ultimate load conditions; Obtain ultimate strain and deflection data; Obtain data for determining the effects on the thrust structure caused by the low pressure fuel and liquid oxygen manifolds when they are ... |
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| Cylinder-Head Temperatures and Coolant Heat Rejections of a Multicylinder, Liquid-Cooled Engine of 1710-Cubic-Inch Displacement |
Jun 1948 |
63 pages |
| Authors:
John H Povolny; Louis J Chelko; FLIGHT PROPULSION RESEARCH LAB CLEVELAND OH
|
| An extensive investigation of the cooling characteristics of a multicylinder, liquid-cooled aircraft engine of 1710-cubic-inch displacement was conducted at the NACA Cleveland laboratory. The results of this investigation are presented showing the variation of the cylinder-head temperature and the coolant heat rejection with the pertinent engine and coolant variables. The data, which were obtained on five engines, are presented for power outputs up to 1860 brake horsepower, coolant flows from ... |
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| A Study of Piston-Ring Friction |
AUG 1947 |
50 pages |
| Authors:
James C. Livengood; Chapin Wallour; MASSACHUSETTS INST OF TECH CAMBRIDGE SLOAN LABS FOR AUTOMOTIVE AND AIRCRAFT ENGINES
|
| A series of tests was made with a special engine equipped with a crosshead and an elastically mounted combustion cylinder. The apparatus permitted the isolation and measurement of the friction forces existing between the piston rings and the cylinder wall during operation of the engine. Various combinations of piston-ring and cyilnder-sleeve materials were investigated in addition to the effects of several engine operating conditions. It was found that under the ... |
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| Investigation of Three Design Modifications of the NACA Injection Impeller in an R-3350 Engine |
09 Sep 1946 |
25 pages |
| Authors:
Robert O Hickel; Donald J Michel; AIRCRAFT ENGINE RESEARCH LAB CLEVELAND OH
|
| An investigation was conducted to determine the effects of three design modifications of the original NACA injection impeller on the performance of an R-3350 engine. Different methods of injecting the fuel into the impeller air stream were studied and evaluated from the individual cylinder fuel-air ratios and the resulting cylinder temperatures. Each impeller was tested for a range of engine powers normally used in flight operation. The relatively simple design ... |
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| A Study of the Effect of Aftercooling on the Power and the Weight of a 2000-Horsepower Air-Cooled Engine Installation |
SEP 1944 |
29 pages |
| Authors:
George P. Wood; D. E. Brimley; NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS LANGLEY FIELD VA LANGLEY AERONAUTICAL LABORATORY
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| Investigations were made to determine effects of aftercooling on brake horsepower and weight power ratio. An increase in bhp of 42% was obtained with superchargers operating at constant manifold temperature and aftercooling to a manifold temperature of 40 deg F. Supercharging to a detonation limited manifold pressure and aftercooling to a temperature of 40 deg F resulted in an increase of 65% in bhp. A 10% reduction in weight-power ratio ... |
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