Near-field plume-surface interaction and regolith erosion and dispersal during the lunar landing

Rahimi, Amin; Ejtehadi, Omid; Lee, K.H.; Myong, R.S.

doi:10.1016/j.actaastro.2020.05.042

Cited by 46 publications

(11 citation statements)

References 35 publications

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“…The simulation models of both stages are shown in Figure 2. Fluent software was used to simulate the two flow stages, which are verified as useful and effective in describing this type of flow when vacuum flow is near-field [28,29]. Figure 2a shows the nozzle geometry of the Chang'E-5 mission.…”

Section: Compressible Plume Flow Simulation Model and Methodsmentioning

confidence: 99%

“…The dominant erosion mechanism adopted here is viscous erosion in the lunar environment. In this investigation, the Roberts erosion model, based on the viscous erosion model, is adopted to describe the lunar surface erosion characteristics of the Chang'E-5 mission [28]. In this model, if the lunar surface shear stress exceeds the critical stress, surface erosion will take place, and the mass erosion rate in this moment will be…”

Section: Lunar Surface Erosion Modelmentioning

confidence: 99%

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The Investigation of Plume-Regolith Interaction and Dust Dispersal during Chang’E-5 Descent Stage

Zhang

You

et al. 2022

Aerospace

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The plume-surface interaction that occurs as a result of a variable-thrust engine exhaust plume impinging on soil during landings is critical for future lunar mission design. Unique lunar environmental properties, such as low gravity, high vacuum, and the regolith layer, make this study complex and challenging. In this paper, we build a reliable simulation model, with constraints based on landing photos, to characterize the erosion properties induced by a low-thrust engine plume. We focus on the low-thrust plume-surface erosion process and erosion properties during the Chang’E-5 mission, aiming to determine the erosion difference between high- and low-thrust conditions; this is a major concern, as the erosion process for a low-thrust lunar mission is rarely studied. First, to identify the entire erosion process and its relative effect on the flat lunar surface, a one-to-one rocket nozzle simulation model is built; ground experimental results are utilized to verify the simulated inlet parameters of the vacuum plume flow field. Following that, plume flow is considered using the finite volume method, and the Roberts erosion model, based on excess shear stress, is adopted to describe plume-surface interaction properties. Finally, a Lagrangian framework using the discrete phase model is selected to investigate the dynamic properties of lunar dust particles. Results show that erosion depth, total ejected mass, and the maximum particle incline angle during the Chang’E-5 landing period are approximately 0.2 cm, 335.95 kg, and 4.16°, respectively. These results are not only useful for the Chang’E-5 lunar sample analysis, but also for future lunar mission design.

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Section: Compressible Plume Flow Simulation Model and Methodsmentioning

confidence: 99%

Section: Lunar Surface Erosion Modelmentioning

confidence: 99%

The Investigation of Plume-Regolith Interaction and Dust Dispersal during Chang’E-5 Descent Stage

Zhang

You

et al. 2022

Aerospace

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“…Inter-particle forces arising from collisions and sliding/rolling friction vary based on the physical properties of the regolith. In recent years, Eulerian-based two-fluid models (Gale et al, 2017;Balakrishnan and Bellan, 2018;Gale et al, 2020;Balakrishnan and Bellan, 2019;Chinnappan et al, 2021;Balakrishnan and Bellan, 2021) and particle-based methods (He et al, 2012;Morris et al, 2015;Rahimi et al, 2020;Shallcross, 2021) of PSI have been conducted that explicitly account for these interactions. Yet, the underlying models these simulations are built upon (e.g., drag, subgrid scale turbulence, etc.)…”

Section: Multiphase Flow Dynamics During Psimentioning

confidence: 99%

Modeling high-speed gas-particle flows relevant to spacecraft landings: A review and perspectives

Capecelatro

2021

Preprint

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The interactions between rocket exhaust plumes and the surface of extraterrestrial bodies during spacecraft landings involve complex multiphase flow dynamics that pose significant risk to space exploration missions. The two-phase flow is characterized by high Reynolds and Mach number conditions with particle concentrations ranging from dilute to close-packing. Low atmospheric pressure and gravity typically encountered in landing environments combined with reduced optical access by the granular material pose significant challenges for experimental investigations. Consequently, numerical modeling is expected to play an increasingly important role for future missions. This article presents a review and perspectives on modeling high-speed disperse two-phase flows relevant to plume-surface interactions (PSI). We present an overview of existing drag laws, with origins from 18th-century cannon fire experiments and new insights from particle-resolved numerical simulations. While the focus here is on multiphase flows relevant to PSI, much of the same physics are shared by other compressible gas-particle flows, such as coal-dust explosions, volcanic eruptions, and detonation of solid material.

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“…The temperature of the ambient gas and cylinder walls was assumed to be constant (273 K). Figure 3 compares the shear stress and heat flux measured along the surface of the cylinder for argon at M = 5.0 and Kn = 0.005 [33,49]. It is seen that the numerical errors consistently decrease with larger grid refinements.…”

Section: Grid Independent Studymentioning

confidence: 99%

Computational simulations of near-continuum gas flow using Navier-Stokes-Fourier equations with slip and jump conditions based on the modal discontinuous Galerkin method

et al. 2020

Self Cite

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Blunt-body configurations are the most common geometries adopted for non-lifting re-entry vehicles. Hypersonic re-entry vehicles experience different flow regimes during flight due to drastic changes in atmospheric density. The conventional Navier-Stokes-Fourier equations with no-slip and no-jump boundary conditions may not provide accurate information regarding the aerothermodynamic properties of blunt-bodies in flow regimes away from the continuum. In addition, direct simulation Monte Carlo method requires significant computational resources to analyze the near-continuum flow regime. To overcome these shortcomings, the Navier-Stokes-Fourier equations with slip and jump conditions were numerically solved. A mixed-type modal discontinuous Galerkin method was employed to achieve the appropriate numerical accuracy. The computational simulations were conducted for different blunt-body configurations with varying freestream Mach and Knudsen numbers. The results show that the drag coefficient decreases with an increased Mach number, while the heat flux coefficient increases. On the other hand, both the drag and heat flux coefficients increase with a larger Knudsen number. Moreover, for an Apollo-like blunt-body configuration, as the flow enters into non-continuum regimes, there are considerable losses in the lift-to-drag ratio and stability.

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Near-field plume-surface interaction and regolith erosion and dispersal during the lunar landing

Cited by 46 publications

References 35 publications

The Investigation of Plume-Regolith Interaction and Dust Dispersal during Chang’E-5 Descent Stage

The Investigation of Plume-Regolith Interaction and Dust Dispersal during Chang’E-5 Descent Stage

Modeling high-speed gas-particle flows relevant to spacecraft landings: A review and perspectives

Computational simulations of near-continuum gas flow using Navier-Stokes-Fourier equations with slip and jump conditions based on the modal discontinuous Galerkin method

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