Thermal and microstructural properties of fine-grained material at the Viking Lander 1 site

Paton, Mark; Harri, A. M.; Savijärvi, Hannu; Mäkinen, T.; Kemppinen, Osku; Johnston, A. K.

doi:10.1016/j.icarus.2016.02.012

Cited by 10 publications

(6 citation statements)

References 58 publications

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“…Some of the ripples have a slightly cohesive near surface layer (few kPa) a few centimeters thick (Sullivan et al 2011). (2) Drift deposits appear to be very fine grained dust (< 10 µm) that has settled out of the atmosphere (Christensen and Moore 1992;Moore et al 1999;Paton et al 2016). This material is also effectively cohesionless (and not load bearing).…”

Section: Cohesionmentioning

confidence: 99%

“…Because of the strong dependence of its value on grain size and degree of cementation, Putzig (2006) distinguished between dust (28-135 J/(m 2 K s 1/2 )), sand (135-630 J/(m 2 K s 1/2 )) and duricrust (252-513 J/(m 2 K s 1/2 )). Paton et al (2016) gave a value for I of 81 to 125 J/(m 2 K s 1/2 ) for dust around the Viking 1 footpads from direct measurements. The highest resolution TES nighttime thermal inertia determination of the InSight landing site (Putzig and Mellon 2007) at 20 pixels per degree range from 138 to 284 J/(m 2 K s 1/2 ) and average 218 J/(m 2 K s 1/2 ) (n = 314).…”

Section: Surface Thermal Inertiamentioning

confidence: 99%

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A Pre-Landing Assessment of Regolith Properties at the InSight Landing Site

et al. 2018

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This article discusses relevant physical properties of the regolith at the Mars InSight landing site as understood prior to landing of the spacecraft. InSight will land in the northern lowland plains of Mars, close to the equator, where the regolith is estimated to be ≥ 3-5 m thick. These investigations of physical properties have relied on data collected from Mars orbital measurements, previously collected lander and rover data, results of studies of data and samples from Apollo lunar missions, laboratory measurements on regolith simu-The InSight Mission to Mars II Edited by William B.

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Section: Cohesionmentioning

confidence: 99%

Section: Surface Thermal Inertiamentioning

confidence: 99%

A Pre-Landing Assessment of Regolith Properties at the InSight Landing Site

et al. 2018

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“…Within each layer, the thermal conductivity is fixed at a single value, and the density and specific heat for both the regolith and breccia are set to ρ = 1750 kg m −3 and c = 600 J kg −1 K −1 , respectively, as in Grott et al (2007). Following Paton et al (2016), the bedrock is set to ρ = 2600 kg m −3 and c = 800 J kg −1 K −1 . In reality, thermal conductivity should be a function of time and depth, k = k(z, t), dependent not just on the layering, but variations within the layers.…”

Section: Methodsmentioning

confidence: 99%

Potential effects of atmospheric collapse on Martian heat flow and application to the InSight measurements

Attree

Patel

Grott

et al. 2020

Planetary and Space Science

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Heat flow is an important constraint on planetary formation and evolution. It has been suggested that Martian obliquity cycles might cause periodic collapses in atmospheric pressure, leading to corresponding decreases in regolith thermal conductivity (which is controlled by gas in the pore spaces). Geothermal heat would then build up in the subsurface, potentially affecting present-day heat flow -and thus the measurements made by a heat-flow probe such as the InSight HP 3 instrument. To gauge the order of magnitude of this effect, we model the diffusion of a putative heat pulse caused by thermal conductivity changes with a simple numerical scheme and compare it to the heat-flow perturbations caused by other effects. We find that an atmospheric collapse to 300 Pa in the last 40 kyr would lead to a present-day heat flow that is up to 2 − 8% larger than the average geothermal background. Considering the InSight mission with expected 5−15% error bars on the HP 3 measurement, this perturbation would only be significant in the best-case scenario of full instrument deployment, completed measurement campaign, and a well-modelled surface configuration. The prospects for detecting long-term climate perturbations via spacecraft heat-flow experiments remain challenging.

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“…9). This results in smaller thermal variations for those payload components and lander subsystems housed in the front part of the lander (Paton et al, 2016). The MNL battery can operate down to temperatures of 220 K and will have its own additional thermal insulation and heaters to increase the battery temperature during charging to at least 250 K if needed.…”

Section: Electric Power and Thermal Management Subsystemsmentioning

confidence: 99%

The MetNet vehicle: a lander to deploy environmental stations for local and global investigations of Mars

Harri

Pichkadze

Zeleny³

et al. 2017

Geosci. Instrum. Method. Data Syst.

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Abstract. Investigations of global and related local phenomena on Mars such as atmospheric circulation patterns, boundary layer phenomena, water, dust and climatological cycles and investigations of the planetary interior would benefit from simultaneous, distributed in situ measurements. Practically, such an observation network would require low-mass landers, with a high packing density, so a large number of landers could be delivered to Mars with the minimum number of launchers.The Mars Network Lander (MetNet Lander; MNL), a small semi-hard lander/penetrator design with a payload mass fraction of approximately 17 %, has been developed, tested and prototyped. The MNL features an innovative Entry, Descent and Landing System (EDLS) that is based on inflatable structures. The EDLS is capable of decelerating the lander from interplanetary transfer trajectories down to a surface impact speed of 50-70 m s −1 with a deceleration of < 500 g for < 20 ms. The total mass of the prototype design is ≈ 24 kg, with ≈ 4 kg of mass available for the payload.The EDLS is designed to orient the penetrator for a vertical impact. As the payload bay will be embedded in the surface materials, the bay's temperature excursions will be much less than if it were fully exposed on the Martian surface, allowing a reduction in the amount of thermal insulation and savings on mass.The MNL is well suited for delivering meteorological and atmospheric instruments to the Martian surface. The payload concept also enables the use of other environmental instruments. The small size and low mass of a MNL makes it ideally suited for piggy-backing on larger spacecraft. MNLs are designed primarily for use as surface networks but could also be used as pathfinders for high-value landed missions.

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Thermal and microstructural properties of fine-grained material at the Viking Lander 1 site

Cited by 10 publications

References 58 publications

A Pre-Landing Assessment of Regolith Properties at the InSight Landing Site

A Pre-Landing Assessment of Regolith Properties at the InSight Landing Site

Potential effects of atmospheric collapse on Martian heat flow and application to the InSight measurements

The MetNet vehicle: a lander to deploy environmental stations for local and global investigations of Mars

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