Lagrangian Trajectory Modeling of Lunar Dust Particles

Lane, John E.; Metzger, Philip T.; Immer, Christopher

doi:10.1061/40988(323)3

Cited by 30 publications

(36 citation statements)

References 3 publications

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“…Plots of the lunar surface pressure and shear can be seen in Figures 3(a) and 3(b), respectively. The flow field and surface properties obtained from this analysis were used in a separate study investigating lunar soil erosion and debris tracking [18] which was similar to the studies done before and after the Apollo landings [5]. Example plots from the ascent stage plume impingement analysis are shown in Figure 4.…”

Section: Summary Of Resultsmentioning

confidence: 99%

Study of Plume Impingement Effects in the Lunar Lander Environment

Marichalar

Prisbell

Lumpkin

et al. 2011

AIP Conference Proceedings

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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.

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Section: Summary Of Resultsmentioning

confidence: 99%

Study of Plume Impingement Effects in the Lunar Lander Environment

Marichalar

Prisbell

Lumpkin

et al. 2011

AIP Conference Proceedings

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“…For more on the detailed physics and effects of plume effects during descent, we refer the reader to Lane et al (), Metzger et al (, ), Immer et al (), Immer et al (), Lane and Metzger (), Kaydash et al (), Clegg et al (), and Clegg‐Watkins et al ().…”

Section: Enhancing Technologiesmentioning

confidence: 99%

Lunar Science for Landed Missions Workshop Findings Report

Jawin

Valencia

Clegg-Watkins

et al. 2019

Earth and Space Science

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The Lunar Science for Landed Missions workshop was convened at the National Aeronautics and Space Administration Ames Research Center on 10–12 January, 2018. Interest in the workshop was broad, with 110 people participating in person and 70 people joining online. In addition, the workshop website (https://lunar-landing.arc.nasa.gov) includes video recordings of many of the presentations. This workshop defined a set of targets that near‐term landed missions could visit for scientific exploration. The scope of such missions was aimed primarily, but not exclusively, at commercial exploration companies with interests in pursuing ventures on the surface of the Moon. Contributed and invited talks were presented that detailed many high priority landing site options across the surface of the Moon that would meet scientific goals in a wide variety of areas, including impact cratering processes and dating, volatiles, volcanism, magnetism, geophysics, and astrophysics. Representatives from the Japan Aerospace Exploration Agency and the European Space Agency also presented about international plans for lunar exploration and science. This report summarizes the set of landing sites and/or investigations that were presented at the workshop that would address high priority science and exploration questions. In addition to landing site discussions, technology developments were also specified that were considered as enhancing to the types of investigations presented. It is evident that the Moon is rich in scientific exploration targets that will inform us on the origin and evolution of the Earth‐Moon system and the history of the inner Solar System, and also has enormous potential for enabling human exploration and for the development of a vibrant lunar commercial sector.

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“…The area ratio of the expander was 47.5 and the diameter at the nozzle exit plane was 1.32m. The flow is sonic at the nozzle throat and the corresponding density and temperature are computed from isentropic flow relations and are 0.1275kg»m 3 and 2491K respectively. The recovered thrust of the modeled engine is 2960lbs and the mean exit plane density, velocity, and temperature are 1.18 ×10…”

Section: Methodsmentioning

confidence: 99%

“…The apparent density can be related to particle density via the volume coefficient, Į v , which is defined as the volume displaced by the grain divided by the cubed aerodynamic diameter, d a . The recommended value for the volume coefficient is 0.34 [15] and the resulting apparent density is 1900kg»m 3 . The aerodynamic cross section is then simply ʌd a 2 »4.…”

Section: Dust Entrainment and Granular Collisionsmentioning

confidence: 99%

Far field deposition of scoured regolith resulting from lunar landings

Morris

Goldstein²,

Varghese³

et al. 2012

AIP Conference Proceedings

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Abstract. As a lunar lander approaches a dusty surface, the plume from the descent engine impinges on the ground, entraining loose regolith into a high velocity dust spray. Without the inhibition of a background atmosphere, the entrained regolith can travel many kilometers from the landing site. In this work, we simulate the flow field from the throat of the descent engine nozzle to where the dust grains impact the surface many kilometers away. The near field is either continuum or marginally rarefied and is simulated via a loosely coupled hybrid DSMC -Navier Stokes (DPLR) solver. Regions of two-phase and polydisperse granular flows are solved via DSMC. The far field deposition is obtained by using a staged calculation, where the first stages are in the near field where the flow is quasi-steady and the outer stages are unsteady. A realistic landing trajectory is approximated by a set of discrete hovering altitudes which range from 20m to 3m. The dust and gas motions are fully coupled using an interaction model that conserves mass, momentum, and energy statistically and inelastic collisions between dust particles are also accounted for. Simulations of a 4 engine configuration are also examined, and the erosion rates as well as near field particle fluxes are discussed.

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Lagrangian Trajectory Modeling of Lunar Dust Particles

Cited by 30 publications

References 3 publications

Study of Plume Impingement Effects in the Lunar Lander Environment

Study of Plume Impingement Effects in the Lunar Lander Environment

Lunar Science for Landed Missions Workshop Findings Report

Far field deposition of scoured regolith resulting from lunar landings

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