Predicting instabilities in liquid rocket engines requires the ability to simulate unsteady reacting flows al high pressures. Intake manifolds, injector design and placement, addition of baffles and acoustic cavities add to the complexity and size of the computational problem at hand. The current effort is focused on the improvement of the basic building blocks which make up the simulation tool. The ability of the toll to track acoustic waves in a low Mach number, unsteady flow with chemical...

Topics: DTIC Archive, METACOMP TECHNOLOGIES INC AGOURA HILLS CA, *COMBUSTION STABILITY, COMPUTATIONAL FLUID...

This paper details the development of a thermoacoustic model and associated dynamic analysis. The model describes the results obtained in a gas fueled experimental combustion program carried out at UTRC. The contents of the paper are (a) the development of a thermoacoustic model composed of acoustic and heat release components, (b) the dynamic analysis of the resulting non-linear model using harmonic balance methods to compute linear stability boundaries and the amplitudes of oscillations and...

Topics: DTIC Archive, Jacobson, C. A., Khibnik, A. J., Banaszuk, A., Cohen, J., Proscia, W., UNITED...

Final report summarizes shortly main results of the quarterly reports and presents experimental results on self-ignition and combustion stabilization in supersonic flow using free recirculation zone. Tests are conducted at hypersonic facility TsAGI T-131B. Measurements are performed in a nearly matched supersonic jet at the exit of two-dimensional channel over Mach number range M=2.O-2.8 at stagnation temperature range Tt=1200-1400K. initial thickness of jet was equal 67 mm. Self-ignition and...

Topics: DTIC Archive, CENTRAL AERODYNAMIC INST MOSCOW (RUSSIA), *COMBUSTION STABILITY, *SUPERSONIC FLOW,...

Emissions at 450 nm and 4.27 micrometers have been measured when a variety of mixtures containing H2, CO, either O2 or N2O, and Ar were heated behind reflected shock waves to temperatures of 2000-2850 K and total concentrations near 5 x 10 to the 18th power molecule/cc. These emissions were used to obtain absolute concentration - time data for both oxygen atoms and carbon dioxide. The data were then compared to the results of numerical integrations of the likely mechanisms. It was observed that...

Topics: DTIC Archive, Dean,Anthony M, PURDUE UNIV LAFAYETTE IND PROJECT SQUID HEADQUARTERS, *REACTION...

The results of an investigation to select a satisfactory numerical method for calculating the propagation of steep fronted shock like waveforms in a solid rocket motor combusion chamber are presented. A number of different numerical schemes were evaluated by comparing the results obtained for three problems: the shock tube problem, the linear wave equation, and nonlinear wave propagation in a closed tube. The most promising method--a combination of the Lax-Wendroff, Hybrid and Artificial...

Topics: DTIC Archive, Baum,Joseph D, DAYTON UNIV OH RESEARCH INST, *FINITE DIFFERENCE THEORY, *WAVE...

A technique for predicting the stability characteristics of a gaseous-propellant rocket combustion system is developed based on a model that assumes coupling between the flow through the injector and the oscillating chamber pressure. The theoretical model uses a lumped parameter approach for the flow elements in the injection system plus wave dynamics in the combustion chamber. The injector flow oscillations are coupled to the chamber pressure oscillations with a delay time. Frequency and decay...

Topics: NASA Technical Reports Server (NTRS), COMBUSTION CHAMBERS, COMBUSTION STABILITY, GASEOUS ROCKET...

A stainless steel, two-dimensional (rectangular), center-dump, premixed-prevaporized combustor with quartz window sidewalls for visual access was designed, built, and used to study flashback. A parametric study revealed that the flashback equivalence ratio decreased slightly as the inlet air temperature increased. It also indicated that the average premixer velocity and premixer wall temperature were not governing parameters of flashback. The steady-state velocity balance concept as the...

Topics: NASA Technical Reports Server (NTRS), COMBUSTION STABILITY, DUMP COMBUSTORS, FLASHBACK, FUEL...

A feedback free fluidic oscillator was designed and integrated into a single element rocket combustor with

Topics: NASA Technical Reports Server (NTRS), COMBUSTION CONTROL, DUMP COMBUSTORS, FEEDBACK, FLUIDICS,...

A major objective in the achievement of propulsion capability for future space missions is to provide capability for heavier payloads, higher mission velocities, and greater operational flexibility. Considering these requirements for improved propulsion, the propellants to be used should provide high specific impulse and high density, they should have smooth ignition characteristics and permit reliable multiple starting capability perhaps by virtue of being hypergolic, and they should offer...

Topics: DTIC Archive, Schmidt, Harold W., NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON DC...

This paper outlines a theoretical approach for predicting the onset of detonation in unconfined turbulent flames. Two basic assumptions are made (1) the gradient mechanism is the inherent mechanism that leads to DDT in unconfined conditions, and (2) the sole mechanism for preparing the gradient in induction time is by turbulent mixing and local flame quenching. The criterion for DDT is derived in terms of the one-dimensional detonation wave thickness, the laminar flame speed, and the laminar...

Topics: DTIC Archive, Khokhlov, Alexei M., NAVAL RESEARCH LAB WASHINGTON DC SENIOR SCIENTIST FOR REACTIVE...

The development is discussed of analytical techniques and numerical methods for the prediction of the stability behavior of liquid propellant rocket combustors with partial length acoustic liners, injector face baffles, and nonlinear combustion responses. Three primary objectives included: (1) extension of the Green's Function integral-iteration technique previously developed so that nonlinear three dimensional wave propagation effects could be included in stability predictions; (2) development...

Topics: NASA Technical Reports Server (NTRS), COMBUSTION STABILITY, LIQUID PROPELLANT ROCKET ENGINES,...

Extensive research is being done toward the development of ultra-low-emissions combustors for aircraft gas turbine engines. However, these combustors have an increased susceptibility to thermoacoustic instabilities. This type of instability was recently observed in an advanced, low emissions combustor prototype installed in a NASA Glenn Research Center test stand. The instability produces pressure oscillations that grow with increasing fuel/air ratio, preventing full power operation. The...

Topics: NASA Technical Reports Server (NTRS), GAS TURBINE ENGINES, PRESSURE OSCILLATIONS, AIR FLOW,...

Since the early 1960's, it has been known that realistic combustion models for liquid fuel rocket engines should contain at least a rudimentary treatment of atomization and spray physics. This is of particular importance in transient operations. It has long been recognized that spray characteristics and droplet vaporization physics play a fundamental role in determining the stability behavior of liquid fuel rocket motors. This paper gives an overview of work in progress on design of a numerical...

Topics: NASA Technical Reports Server (NTRS), ATOMIZING, COMBUSTION PHYSICS, COMBUSTION STABILITY, DROPS...

The liquid rocket engine stability prediction software (LCI) predicts combustion stability of systems using LOX-LH2 propellants. Both longitudinal and transverse mode stability characteristics are calculated. This software has the unique feature of being able to predict system limit amplitude.

Topics: NASA Technical Reports Server (NTRS), COMBUSTION STABILITY, LIQUID PROPELLANT ROCKET ENGINES,...

Extensive research is being done toward the development of ultra-low-emissions combustors for aircraft gas turbine engines. However, these combustors have an increased susceptibility to thermoacoustic instabilities. This type of instability was recently observed in an advanced, low emissions combustor prototype installed in a NASA Glenn Research Center test stand. The instability produces pressure oscillations that grow with increasing fuel/air ratio, preventing full power operation. The...

Topics: NASA Technical Reports Server (NTRS), COMBUSTION CHAMBERS, COMBUSTION STABILITY, PROTOTYPES,...

The combustion characteristics of hydrazine strands were studied under both steady state and oscillatory conditions. A steady strand burner was used to measure steady strand burning rates, liquid temperature distributions and surface temperatures as a function of pressure in the pressure range of 0.32 to 42 atm. It was found that for subatmospheric pressures the burning rate varied as the square root of pressure; for pressures greater than atmospheric the burning rate varied linearly with...

Topics: NASA Technical Reports Server (NTRS), BURNING RATE, MONOPROPELLANTS, PRESSURE OSCILLATIONS,...

An object of this invention is to provide a composition of beryllium hydride and carboxy-terminated polybutadiene which is stable. Another object of this invention is to provide a method for inhibiting the reactivity of beryllium hydride toward carboxy-terminated polybutadiene. It was found that a small amount of lecithin inhibits the reaction of beryllium hydride with the acid groups in carboxy terminated polybutadiene.

Topics: NASA Technical Reports Server (NTRS), BERYLLIUM HYDRIDES, INHIBITORS, POLYBUTADIENE, PROPELLANT...

To provide combustion stability in burners over a wide range of flow conditions, a coaxial injector is provided which includes an outer annular sleeve for introduction of one reactant and a hollow pintle with spaced slots for introduction of another reactant to impinge on the first reactant. The slots are staggered in location and size to permit initial interlocking of the reactants and, therefore, increased mixing and improved combustion performance.

Topics: NASA Technical Reports Server (NTRS), BURNERS, COMBUSTION, COMBUSTION STABILITY, INJECTORS,...

The influence of stretch and preferential diffusion on premixed flame extinction and stability was investigated via two model flame configurations, namely the stagnation flame and the bunsen flame. Using a counterflow burner and a stagnation flow burner with a water-cooled wall, the effect of downstream heat loss on the extinction of a stretched premixed flame investigated for lean and rich propane/air and methane/air mixtures. It was demonstrated that extinction by stretch alone is possible...

Topics: NASA Technical Reports Server (NTRS), COMBUSTION, EXTINCTION, FLAME STABILITY, MIXTURES, PREMIXED...

The performance and stability of liquid rocket engines is determined to a large degree by atomization, mixing, and combustion processes. Control over these processes is exerted through the design of the injector. Injectors in liquid rocket engines are called upon to perform many functions. They must first of all mix the propellants to provide suitable performance in the shortest possible length. For main injectors, this is driven by the tradeoff between the combustion chamber performance,...

Topics: NASA Technical Reports Server (NTRS), ATOMIZING, COMBUSTION PHYSICS, COMBUSTION STABILITY, DROPS...

The goal of this research is to experimentally characterize the behavior of droplets in vaporizing liquid sprays under conditions typical of those encountered in high pressure combustion systems such as liquid fueled rocket engines. Of particular interest are measurements of droplet drag, droplet heating, droplet vaporization, droplet distortion, and secondary droplet breakup, under both subcritical and supercritical conditions. The paper presents a brief description of the specific...

Topics: NASA Technical Reports Server (NTRS), DROPS (LIQUIDS), LIQUID PROPELLANT ROCKET ENGINES, PARTICLE...

A method involving approximate modal analysis using the Galerkin method followed by an approximate solution of the resulting modal-amplitude equations by the two-variable perturbation method (method of multiple scales) is applied to two problems of pressure-sensitive nonlinear combustion instability in liquid-fuel rocket motors. One problem exhibits self-coupled instability while the other exhibits mode-coupled instability. In both cases it is possible to carry out the entire linear stability...

Topics: NASA Technical Reports Server (NTRS), COMBUSTION STABILITY, COUPLED MODES, GALERKIN METHOD, LIQUID...

An analytical model is formulated for a three-dimensional nonlinear stability problem in a rocket motor combustion chamber. The chamber is modeled as a right circular cylinder with a short (multi-orifice) nozzle, and an acoustic linear covering an arbitrary portion of the cylindrical periphery. The combustion is concentrated at the injector and the gas flow field is characterized by a mean Mach number. The unsteady combustion processes are formulated using the Crocco time lag model. The...

Topics: NASA Technical Reports Server (NTRS), COMBUSTION CHAMBERS, COMBUSTION STABILITY, ROCKET ENGINES,...

Results obtained in studying the origin and suppression of large-amplitude pressure oscillations in a 24 in. diameter hybrid motor using a liquid oxygen/hydroxylterminated polybutadiene/polycyclopentadiene propellant system are discussed. Tests conducted with liquid oxygen flow rates varying from 10 to 40 lbm/sec were designed to gauge the effectiveness of various vaporization chamber flow fields, injector designs, and levels of heat addition in suppressing high-frequency longitudinal mode...

Topics: NASA Technical Reports Server (NTRS), BOOSTER ROCKET ENGINES, COMBUSTION CHAMBERS, COMBUSTION...

The program utilizes a wide variety of experimental methods as well as theoretical studies in specific areas such as burn rate modeling. These methods have been well documented in numerous presentations, publications, and patents. They allow the study of catalyzed and uncatalyzed decomposition of propellant oxidizers, binders, and metal fuels, and the evaluation of combustion characteristics, combustion performance, and combustion stability of experimental and production lot propellants. Where...

Topics: DTIC Archive, Kraeutle, K. J., NAVAL WEAPONS CENTER CHINA LAKE CA, *TEST AND EVALUATION,...

A nonlinear stability analysis of solid rocket propellant burning was carried out, within the framework of a thermal theory for thin (quasi-steady gas phase) heterogeneous flames. This required an integral method in reducing the partial differential equation for the condensed phase heat conduction to an approximate ordinary differential equation. A nonlinear algebraic function, called static restoring function, was found that contains all basic properties of equilibrium and stability of burning...

Topics: DTIC Archive, De Luca,Luigi, POLITECNICO DI MILANO (ITALY) IST DI MACCHINE, *DYNAMICS, *COMBUSTION,...

The steady-state combustion model developed in FY 1979 was further improved by the incorporation of models of aluminum agglomeration and energetic binder combustion. Application of the model to a large variety of composite propellants was successful for the most part. Remaining deficiencies in the model are discussed. Experiments with a porous burner apparatus designed to simulate the diffusion flames of bimodal propellants revealed that fine oxidizer ports tend to operate more fuel-rich than...

Topics: DTIC Archive, Cohen,N S, JET PROPULSION LAB PASADENA CA, *MATHEMATICAL MODELS, *COMBUSTION,...

Turbularization of an acoustic boundary-layer (Strokes layer) on impermeable and permeable surfaces is analytically considered. The theoretical approach utilizes a second-order closure model of turbulence. An approximate, closed form solution and a more comprehensive finite difference solution of the time dependent, parabolic, one dimensional governing equations are obtained. For simple acoustic boundary layers on impermeable surfaces, the approximate solution and the numerical results for the...

Topics: DTIC Archive, Beddini, Robert A, ILLINOIS UNIV AT URBANA DEPT OF AERONAUTICAL AND ASTRONAUTICAL...

No abstract available

Topics: NASA Technical Reports Server (NTRS), COMBUSTION CONTROL, COMBUSTION CHAMBERS, PROTOTYPES,...

Combustion instability, where unsteady heat release couples with acoustic modes, has long been an area of concern in liquid rocket engines. Accurate modeling of the acoustic normal modes of the combustion chamber is important to understanding and preventing combustion instability. This study evaluates the effect of injector resistance on the mode shapes and complex eigen-frequencies of an injector/combustion chamber system by defining a high Mach-flow form of the convective wave equation (see...

Topics: NASA Technical Reports Server (NTRS), INJECTORS, COMBUSTION CHAMBERS, COMBUSTION STABILITY,...

This paper describes ongoing testing of an adaptive control method to suppress high frequency thermo-acoustic instabilities like those found in lean-burning, low emission combustors that are being developed for future aircraft gas turbine engines. The method called Adaptive Sliding Phasor Averaged Control, was previously tested in an experimental rig designed to simulate a combustor with an instability of about 530 Hz. Results published earlier, and briefly presented here, demonstrated that...

Topics: NASA Technical Reports Server (NTRS), COMBUSTION STABILITY, GAS TURBINE ENGINES, ADAPTIVE CONTROL,...

A procedure which can accurately characterize injector designs for large thrust (0.5 to 1.5 million pounds), high pressure (500 to 3000 psia) LOX/hydrocarbon engines is currently under development. In this procedure, a rectangular cross-sectional combustion chamber is to be used to simulate the lower traverse frequency modes of the large scale chamber. The chamber will be sized so that the first width mode of the rectangular chamber corresponds to the first tangential mode of the full-scale...

Topics: NASA Technical Reports Server (NTRS), COMPUTER PROGRAMS, FUEL INJECTION, INLET NOZZLES,...

The response of solid rocket motor materials to high-temperature corrosive gases is usually accomplished by testing the materials in a subscale solid rocket motor. While this imposes the proper thermal and chemical environment, a solid rocket motor does not provide practical features that would enhance systematic evaluations such as: the ability to throttle for margin testing, on/off capability, low test cost, and a low-hazards test article. Solid Rocket Combustion Simulators (SRCS) are being...

Topics: NASA Technical Reports Server (NTRS), BURNING RATE, CORROSION TESTS, ENGINE TESTS, PROPELLANT...

An experimental program has been conducted to study interactions between acoustics waves and two types of non-uniform average flow occurring in solid propellant rockets. Measurements in a resonance tube confirmed the existence of an energy loss associated with interactions between a longitudinal acoustic field and an average flow entering through a lateral boundary. The measured loss was approximately five times as large as that predicted by a simple one-dimensional analysis. However, due to...

Topics: DTIC Archive, Culick,F E C, CALIFORNIA INST OF TECH PASADENA GUGGENHEIM JET PROPULSION CENTER, *GAS...

An investigation was conducted to determine the cause of starting problems in the hypergolic rocket engines of the Apollo reaction control (RCS) engines. The scope of the investigation was as follows: (1) to establish that chemical reactions occurred during the preignition and post combustion periods, (2) to identify the chemical species of the products of preignition and post combustion reaction, and (3) to determine the explosive nature of the identified species. The methods used in...

Topics: NASA Technical Reports Server (NTRS), COMBUSTION PRODUCTS, HYPERGOLIC ROCKET PROPELLANTS,...

The results of an investigation to select a satisfactory numerical method for calculating the propagation of steep fronted shock like waveforms in a solid rocket motor combusion chamber are presented. A number of different numerical schemes were evaluated by comparing the results obtained for three problems: the shock tube problem, the linear wave equation, and nonlinear wave propagation in a closed tube. The most promising method--a combination of the Lax-Wendroff, Hybrid and Artificial...

Topics: DTIC Archive, Baum,Joseph D, DAYTON UNIV OH RESEARCH INST, *FINITE DIFFERENCE THEORY, *WAVE...

An experimental program has been conducted to study interactions between acoustics waves and two types of non-uniform average flow occurring in solid propellant rockets. Measurements in a resonance tube confirmed the existence of an energy loss associated with interactions between a longitudinal acoustic field and an average flow entering through a lateral boundary. The measured loss was approximately five times as large as that predicted by a simple one-dimensional analysis. However, due to...

Topics: DTIC Archive, Culick,F E C, CALIFORNIA INST OF TECH PASADENA GUGGENHEIM JET PROPULSION CENTER, *GAS...

This report covers: (1) the application of a modular combustor model for the liquid fueled sudden expansion combustor configuration to the analysis of flame stability and the interpretation of combustor test data; (2) the extension of the modular model to the analysis of boron slurry fueled ramjet combustors; and (3) the development of analytical models of the ducted rocket combustor. The modular approach is demonstrated to be a useful tool for the analysis and interpretation of...

Topics: DTIC Archive, Bragg,W N, SCIENCE APPLICATIONS INC CANOGA PARK CA COMBUSTION DYNAMICS AND PROPULSION...

The report consists of a collection of abstracts of the numerous research progress reports given by AFOSR contractors and of invited papers from other governmental agencies and contractors. These papers presented over a five-day period composed the 1977 annual contractors meeting on air-breathing combustion dynamics. The principal investigators and their organizational association are also identified. (Author)

Topics: DTIC Archive, PURDUE UNIV LAFAYETTE IND SCHOOL OF MECHANICAL ENGINEERING, *AIR BREATHING ENGINES,...

The use of liquid propellants in guns is reviewed both historically and in terms of the characteristics and properties required of such materials. The physical and chemical characteristics required of propellant formulations is strongly predicated on application in a particular weapons system and, based on such system requirements, the aqueous monopropellants consisting of the nitrate salts of hydroxylamine and an aliphatic, tertiary amine are shown to currently hold the greatest promise for...

Topics: DTIC Archive, Klein, Nathan, ARMY BALLISTIC RESEARCH LAB ABERDEEN PROVING GROUND MD, *OXIDIZERS,...

Turbularization of an acoustic boundary layer (Stokes Layer) on impermeable and permeable surfaces is analytically considered. The theoretical approach uses a second-order closure model of turbulence. Both an approximate, closed-form solution and a more comprehensive finite difference solution of the time dependent, parabolic, one-dimensional governing equations are obtained. For simple acoustic boundary-layers on impermeable surfaces, both the approximate solution and the numerical results for...

Topics: DTIC Archive, Roberts, Ted A, ILLINOIS UNIV AT URBANA DEPT OF AERONAUTICAL AND ASTRONAUTICAL...

Combustion instability in conventional guns is often manifested by the presence of longitudinal pressure waves traveling between the breech face and base of the projectile. Such waves are of concern because of their causal connection with high chamber pressures and pressurization rates which may in turn lead to breechblows, projectile or fuze malfunctions, and ballistic variability. While design approaches which minimize pressure waves are routinely employed today, the problem remains of...

Topics: DTIC Archive, Horst, A W, ARMY BALLISTIC RESEARCH LAB ABERDEEN PROVING GROUND MD, *PRESSURE...

Acoustic oscillations were induced in a sub-scale liquid rocket engine that burned liquid oxygen and gaseous hydrogen as propellants. The oscillations in the chamber were forced by a rotating gear just downstream of the nozzle throat. High frequency data was acquired for pressure and velocity via a pressure transducer and a magnetic flowmeter. The magnetic flowmeter obtains the acoustic gas velocity by measuring the voltage induced by the ionized combustion products moving through an externally...

Topics: DTIC Archive, Micci, Michael M., PENNSYLVANIA STATE UNIV UNIVERSITY PARK DEPT OF AEROSPACE...

Flame-balls are stationary spherical premixed flames observed in certain near-limit mixtures. Sufficiently large flame-balls are subject to a three-dimensional instability which defines a maximum mixture strength for which steady flame-balls can exist. The researchers studied the dynamics of flame- balls in the neighborhood of the neutral stability point and show that there is a transcritical bifurcation and the dynamics is governed by a fifth-order system of nonlinear ordinary differential...

Topics: DTIC Archive, Buckmaster, John, ILLINOIS UNIV AT URBANA DEPT OF AERONAUTICAL AND ASTRONAUTICAL...

A nonlinear stability analysis of solid rocket propellant burning was carried out, within the framework of a thermal theory for thin (quasi-steady gas phase) heterogeneous flames. This required an integral method in reducing the partial differential equation for the condensed phase heat conduction to an approximate ordinary differential equation. A nonlinear algebraic function, called static restoring function, was found that contains all basic properties of equilibrium and stability of burning...

Topics: DTIC Archive, De Luca,Luigi, POLITECNICO DI MILANO (ITALY) IST DI MACCHINE, *DYNAMICS, *COMBUSTION,...

Topics: DTIC Archive, NATIONAL AERONAUTICS AND SPACE ADMINISTRATION CLEVELAND OH GLENN RESEARCH CENTER,...

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Jun 1, 2010
06/10

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Kerslake, W. R.; Male, T

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Prevention of high frequency combustion pressure oscillations by longitudinal fins in combustion chamber of rocket engine

Topics: BURNOUT, ROCKET ENGINES, COMBUSTION CHAMBER, COMBUSTION INSTABILITY, FIN, PRESSURE OSCILLATION,...

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Jul 6, 2010
07/10

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HELLER, T

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A PRINCIPLE FOR THE MODIFICATION OF A SYNCHRONOUS AMPLIFIER IS PRESENTED. THE CONVENTIONAL SYNCHRONOUS AMPLIFIER IS DESCRIBED, AND THE EQUATION FOR MODIFIED SYNCHRONOUS AMPLIFICATION IS DERIVED ALONG WITH THE EXPRESSION FOR THE IMPROVEMENT FACTOR, I.E., THE RATIO OF THE PERTURBING NOISE AMPLITUDE FOR THE CONVENTIONAL AND MODIFIED SYNCHRONOUS AMPLIFICATION.

Topics: CHEMICAL PROPULSION, THRUST CHAMBERS, TURBOMACHINERY, COMBUSTION STABILITY, ENGINE DESIGN,...

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May 23, 2011
05/11

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Jain, Rames

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Many complex systems deal with information from multiple sources. A system guiding a pilot should be able to dynamically assimilate information from on board sensors and communication. An autonomous robot, like its human counterpart, needs to interact with its environment using multiple sensors and actuators. A system collecting multi-modal information from information servers for presentation to the user should assimilate multiple sources of information. One common feature in all these...

Topics: SPACE SHUTTLE MAIN ENGINE, LOADS (FORCES), HIGH PRESSURE, CRITICAL VELOCITY, BOUNDARY LAYER...

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Jun 2, 2011
06/11

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Franklin, James A

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As a member of the Joint Strike Fighter program team, Ames Research Center is participating in technology development for short takeoff and vertical landing (STOVL) fighter aircraft. NASA's role in the program is to develop design guidelines for integrated flight/propulsion controls, to support technology development for a demonstrator aircraft, and to provide consultation on integrated control design to industry participants. The choices of control response types and of pilot/vehicle interface...

Topics: ACOUSTIC PROPERTIES, COMBUSTION CHAMBERS, COMPUTATIONAL FLUID DYNAMICS, SIMULATION, COMBUSTION...