| Molecular Dynamics Simulations of Supercritical Sprays |
12 MAR 2004 |
9 pages |
| Authors:
Michael M. Micci; PENNSYLVANIA STATE UNIV UNIVERSITY PARK DEPT OF AEROSPACE ENGINEERING
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 | The objective of this program was to develop an accurate and fast simulation methodology for supercritical injection and mixing using molecular dynamics (MD). The use of MD allows the supercritical mixing to occur naturally' without the need for tracking phase boundaries and intrinsically includes all physical processes, material properties and equations of state in both subcritical and supercritical environments. MD also allows the tracking of injected liquid molecules into the ... |
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| Molecular Dynamics Investigation of Supercritical Fuels |
29 FEB 2000 |
15 pages |
| Authors:
Michael M. Micci; Lyle N. Long; PENNSYLVANIA STATE UNIV UNIVERSITY PARK
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| Equilibrium and nonequilibrium molecular dynamics (MD) implemented on parallel processing computers was used to simulate supercritical fuel phenomena occurring in high pressure combustion devices. The coefficients of diffusion, viscosity and thermal conductivity and the equation of state of argon, oxygen, nitrogen and various alkanes at high pressures and temperatures were obtained via molecular dynamics with the obtained values agreeing with and extending NIST SUPERTRAPP code values. ... |
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| Plasma Stabilization in Low-Power C Band Microwave Arcjets |
31 OCT 1999 |
34 pages |
| Authors:
Michael M. Micci; D. Nordling; F. Souliez; PENNSYLVANIA STATE UNIV UNIVERSITY PARK DEPT OF AEROSPACE ENGINEERING
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| Performance evaluation of a 100 Watt 7.5 GHz resonant cavity microwave thruster was conducted using helium, nitrogen and ammonia propellants exhausting to both atmospheric and vacuum conditions. Emission spectroscopy of the plasma was made in order to measure the plasma electron temperature at different specific power levels, and the assumption of Local Thermodynamic Equilibrium (LTE) was examined. Electron temperature values of approximately 4000 Kelvin ... |
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| Application of Parallel Processing to the Investigation of Supercritical Droplet Evaporation and Combustion Using Molecular Dynamics |
24 OCT 97 |
12 pages |
| Authors:
Michael M. Micci; Lyle N. Long; PENNSYLVANIA STATE UNIV UNIVERSITY PARK DEPT OF AEROSPACE ENGINEERING
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| Molecular dynamics (MD) implemented on parallel processors was used to model supercritical droplet phenomena occurring in combustion devices. The use of molecular dynamics allows the modeling of supercritical phenomena without an a priori knowledge of the equation of state or transport properties of the individual components or the mixture. Three-dimensional supercritical oxygen vaporization into gaseous oxygen and helium using two-site Lennard-Jones potentials for the oxygen has been modeled and both ... |
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| Contributions of Shear Coaxial Injectors to Liquid Rocket Motor Combustion Instabilities |
24 OCT 97 |
12 pages |
| Authors:
Michael M. Micci; PENNSYLVANIA STATE UNIV UNIVERSITY PARK DEPT OF AEROSPACE ENGINEERING
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| Acoustic oscillations were induced in a subscale 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 were 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 ... |
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| Contributions of Atomization, Vaporization and Combustion to Liquid Rocket Acoustic Energy |
15 SEP 97 |
7 pages |
| Authors:
Michael M. Micci; PENNSYLVANIA STATE UNIV UNIVERSITY PARK DEPT OF AEROSPACE ENGINEERING
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| 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 ... |
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| Liquid Rocket Motor Combustion Stability Using Coaxial Injectors and Supercritical Droplet Combustion and Dynamics |
MAY 95 |
222 pages |
| Authors:
Michael M. Micci; Vigor Yang; PENNSYLVANIA STATE UNIV UNIVERSITY PARK
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| Cold flow experiments with a full-size SSME preburner shear coaxial injector element using liquid and gaseous nitrogen at pressures up to 4 MPa showed that the intact liquid core decreased in length with increasing chamber pressure up to the critical pressure, after which it increased in length. Increasing the liquid to gas mass flow rate ratio resulted in an increase in the length of the liquid core. LDV measurements showed ... |
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| Liquid Motor Combustion Stability Using Coaxial Injectors |
12 APR 93 |
12 pages |
| Authors:
Michael M. Micci; PENNSYLVANIA STATE UNIV UNIVERSITY PARK DEPT OF AEROSPACE ENGINEERING
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| The Final Report documents the first fifteen months of work on an experimental investigation of the sources of combustion instability in liquid propellant rocket motors using coaxial injectors. Three possible contributions to combustion instability are being investigated: atomization characteristics, flameholding by means of a recirculation region at the base of the LOX post and gas side injector coupling. The atomization is characterized by means of a Phase Doppler Particle Analyzer ... |
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| Coupling between Radiation and Gas Dynamics |
31 MAY 91 |
75 pages |
| Authors:
Charles L. Merkle; Michael M. Micci; PENNSYLVANIA STATE UNIV UNIVERSITY PARK DEPT OF MECHANICAL ENGINEERING
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| Detailed experimental and analytic studies of microwave thermal propulsion are presented. Results are obtained for four geometric configurations: bluff-body stabilized resonant cavity plasmas; swirl-stabilized resonant cavity plasmas; free-floating plasmas in resonant cavities; and propagating, bluff-body stabilized plasmas in waveguides. Swirl stabilization proved to be less effective than bluff-body stabilization and was not modeled analytically. The experimental studies included both helium and nitrogen plasmas, while the analytic results are for helium ... |
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| Coupling between Radiation and Gas Dynamics |
24 MAY 89 |
39 pages |
| Authors:
Charles L. Merkle; Michael M. Micci; PENNSYLVANIA STATE UNIV UNIVERSITY PARK DEPT OF MECHANICAL ENGINEERING
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| Heat addition in flowing gases by electromagnetic wave absorption is being considered for propulsive purposes. The research includes both microwave and solar radiation. In the microwave studies, an experimental investigation of helium and nitrogen discharges has shown that free-floating plasmas can be established in either medium for a range of input powers and gas flow rates, although helium gives the broader range of stable limits. The discharges are being set ... |
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| Coupling between Radiation and Gas Dynamics |
01 MAR 88 |
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| Authors:
Charles L. Merkle; Michael M. Micci; PENNSYLVANIA STATE UNIV UNIVERSITY PARK DEPT OF MECHANICAL ENGINEERING
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 | Direct heat addition of flowing gases by radiation absorption is considered. In the visible wavelength regime, the interaction between concentrated solar energy and a flowing gas is being modeled numerically. Additional analyses of laser-gasdynamic interactions are also being considered. Implicit time-iterative procedures originally developed for transonic flows are being adapted to the low Mach number, low Reynolds number regimes of interest. Two-dimensional solutions show that absorption plasmas can exist over ... |
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| Analysis and Measurement of High Frequency Solid Propellant Responses |
JUL 86 |
46 pages |
| Authors:
Michael M. Micci; PENNSYLVANIA STATE UNIV UNIVERSITY PARK DEPT OF AEROSPACE ENGINEERING
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| This report describes a program to study high frequency solid propellant responsed. The experimental techniques are based on the application of the magnetic flowmeter. A magnetic flowmeter burner was designed and constructed to evaluate the direct method of pressure-coupled response measurement. Response measurements were obtained for two formulations of AP/HTPB composite propellant at pressure oscillation frequencies from 4000 to 20,000 Hz. The measured data displayed consistent trends in both the ... |
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