Application highlights of the DSMC Analysis Code (DAC) software for simulating rarefied flows

LeBeau, Gerald J.; Lumpkin, Forrest E.

doi:10.1016/s0045-7825(01)00304-8

Cited by 110 publications

(49 citation statements)

References 22 publications

Supporting

Mentioning

Contrasting

Unclassified

Order By: Relevance

“…Here the movement and collisions of a large number of test particles are decoupled over a time step which is a fraction of the mean collision time. The technique is well established and has been used to simulate flow applications as diverse as high altitude aerodynamics [13], micro-thrusters for space applications [14] and steady flow CVD applications [15].…”

Section: Introductionmentioning

confidence: 99%

Development of a model for high precursor conversion efficiency pulsed-pressure chemical vapor deposition (PP-CVD) processing

Cave

Krumdieck

Jermy

2008

Chemical Engineering Journal

View full text Add to dashboard Cite

A model of the movement of precursor particles in the unsteady Pulsed-Pressure Chemical Vapour Deposition (PP-CVD) process is developed to study the high conversion efficiencies observed experimentally in this process. Verification of the modelling procedures was conducted through a study of velocity persistence in an equilibrium gas and through Direct Simulation Monte Carlo (DSMC) simulations of unsteady self-diffusion processes.The model results demonstrate that in the PP-CVD process the arrival time for precursor particles at the deposition surface is much less than the reactor pump-down time, resulting in high precursor conversion efficiencies. Higher conversion efficiency was found to correlate with smaller size solvent molecules and moderate reactor peak pressure.

show abstract

Section: Introductionmentioning

confidence: 99%

Development of a model for high precursor conversion efficiency pulsed-pressure chemical vapor deposition (PP-CVD) processing

Cave

Krumdieck

Jermy

2008

Chemical Engineering Journal

View full text Add to dashboard Cite

show abstract

“…All DSMC simulations were performed with the NASA Johnson Space Center DSMC Analysis Code (DAC) [13]. The DAC option for nearest neighbor collisions was used for all simulations as described in Reference [14], which allows for relaxation of the standard 1.0 ratio of mean-free-path-to-cell-size resolution.…”

Section: Methodology and Assumptionsmentioning

confidence: 99%

Study of Plume Impingement Effects in the Lunar Lander Environment

Marichalar

Prisbell

Lumpkin

et al. 2011

AIP Conference Proceedings

View full text Add to dashboard Cite

Abstract. Plume impingement effects from the descent and ascent engine firings of the Lunar Lander were analyzed in support of the Lunar Architecture Team under the Constellation Program. The descent stage analysis was performed to obtain shear and pressure forces on the lunar surface as well as velocity and density profiles in the flow field in an effort to understand lunar soil erosion and ejected soil impact damage which was analyzed as part of a separate study. A Computational Fluid Dynamics (CFD)/Direct Simulation Monte Carlo (DSMC) decoupled methodology was used with the Bird continuum breakdown parameter to distinguish the continuum flow from the rarefied flow. The ascent stage analysis was performed to ascertain the forces and moments acting on the Lunar Lander Ascent Module due to the firing of the main engine on take-off. The Reacting and Multiphase Program (RAMP) method of characteristics (MOC) code was used to model the continuum region of the nozzle plume, and the DSMC Analysis Code (DAC) was used to model the impingement results in the rarefied region. The ascent module (AM) was analyzed for various pitch and yaw rotations and for various heights in relation to the descent module (DM). For the ascent stage analysis, the plume inflow boundary was located near the nozzle exit plane in a region where the flow number density was large enough to make the DSMC solution computationally expensive. Therefore, a scaling coefficient was used to make the DSMC solution more computationally manageable. An analysis of the effects of this scaling technique was performed. Because the inflow boundary was near the nozzle exit plane, another analysis was performed investigating three different inflow contours to determine the effects of the flow expansion around the nozzle lip on the final plume impingement results.

show abstract

“…This inflow contour did not compromise the validity of the results but merely resulted in a more complex DSMC simulation. The DSMC simulations were made using the DSMC Analysis Code (DAC) [4]. DAC is the primary program used by NASA Johnson Space Center (JSC) for simulating rarefied flow environments.…”

Section: Methodsmentioning

confidence: 99%

Analysis of Plume Impingement Effects from Orion Crew Service Module Dual Reaction Control System Engine Firings

Prisbell

Marichalar

Lumpkin

et al. 2011

AIP Conference Proceedings

View full text Add to dashboard Cite

Plume impingement effects on the Orion Crew Service Module (CSM) were analyzed for various dual Reaction Control System (RCS) engine firings and various configurations of the solar arrays. The study was performed using a decoupled computational fluid dynamics (CFD) and Direct Simulation Monte Carlo (DSMC) approach. This approach included a single jet plume solution for the R1E RCS engine computed with the General Aerodynamic Simulation Program (GASP) CFD code. The CFD solution was used to create an inflow surface for the DSMC solution based on the Bird continuum breakdown parameter. The DSMC solution was then used to model the dual RCS plume impingement effects on the entire CSM geometry with deployed solar arrays. However, because the continuum breakdown parameter of 0.5 could not be achieved due to geometrical constraints and because high resolution in the plume shock interaction region is desired, a focused DSMC simulation modeling only the plumes and the shock interaction region was performed. This high resolution intermediate solution was then used as the inflow to the larger DSMC solution to obtain plume impingement heating, forces, and moments on the CSM and the solar arrays for a total of 21 cases that were analyzed. The results of these simulations were used to populate the Orion CSM Aerothermal Database. Abstract. Plume impingement effects on the Orion Crew Service Module (CSM) were analyzed for various dual Reaction Control System (RCS) engine firings and various configurations of the solar arrays. The study was performed using a decoupled computational fluid dynamics (CFD) and Direct Simulation Monte Carlo (DSMC) approach. This approach included a single jet plume solution for the R1E RCS engine computed with the General Aerodynamic Simulation Program (GASP) CFD code. The CFD solution was used to create an inflow surface for the DSMC solution based on the Bird continuum breakdown parameter. The DSMC solution was then used to model the dual RCS plume impingement effects on the entire CSM geometry with deployed solar arrays. However, because the continuum breakdown parameter of 0.05 could not be achieved due to geometrical constraints and because high resolution in the plume shock interaction region is desired, a focused DSMC simulation modeling only the plumes and the shock interaction region was performed. This high resolution intermediate solution was then used as the inflow to the larger DSMC solution to obtain plume impingement heating, forces, and moments on the CSM and the solar arrays for a total of 21 cases that were analyzed. The results of these simulations were used to populate the Orion CSM Aerothermal Database.

show abstract

Application highlights of the DSMC Analysis Code (DAC) software for simulating rarefied flows

Cited by 110 publications

References 22 publications

Development of a model for high precursor conversion efficiency pulsed-pressure chemical vapor deposition (PP-CVD) processing

Development of a model for high precursor conversion efficiency pulsed-pressure chemical vapor deposition (PP-CVD) processing

Study of Plume Impingement Effects in the Lunar Lander Environment

Analysis of Plume Impingement Effects from Orion Crew Service Module Dual Reaction Control System Engine Firings

Contact Info

Product

Resources

About