Thermal radiation properties of Apollo 14 fines

Birkebak, R. C.; Dawson, J. P.

doi:10.1007/bf02630654

Cited by 5 publications

(2 citation statements)

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“…Surface features, mainly boulders and craters of varying sizes, further alter the local heat fluxes. Depending on the local mineralogy and topology, only 5 to 25% of the incoming energy from the sun is reflected from the lunar surface (see Table 1, [29,30,[34][35][36][37][38][39][40]). The absorbed portion heats up the surface, including boulders or illuminated sections of crater slopes, which in turn each emit heat in the far infrared wavelength range.…”

Section: Simulated Lunar-surface Environmentmentioning

confidence: 99%

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Characterizing a Transient Heat Flux Envelope for Lunar-Surface Spacesuit Thermal Control Applications

Hager¹,

Walter²,

Massina³

et al. 2015

Journal of Spacecraft and Rockets

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In this paper, a transient thermal simulation approach is used to characterize the heat flux and heat flux rates between the lunar surface and a moving spacesuit model. Five different lunar-surface settings are simulated with craters and boulders at three solar elevation angles (θ 2, 10, 90 deg). Heat fluxes and rates are evaluated for different parts of the suit and different characteristic tasks along a given path. The simulated paths are based on Apollo mobility studies. The results indicate that, at lower solar elevation angles, which imply lower lunar-surface temperatures, the thermal impact of surface features becomes more pronounced. In all simulated cases, and for more than 85% of the time, the infrared heat fluxes vary at rates below 20 W · m −2 · s −1 . The incidence versus magnitude of infrared heat flux rates follows a power law with a negative exponent. Smaller heat flux rates have a higher occurrence at lower surface temperatures, and vice versa. The created lookup tables with task, solar elevation angle, and incident heat fluxes can be used as a baseline in the design and sizing of thermal control hardware for moving objects on the surface of the Moon. Nomenclature

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Section: Simulated Lunar-surface Environmentmentioning

confidence: 99%

“…Regolith material properties and overview of used model parameter ranges[29,30,[34][35][36][37][38][39][40] Thermal conductivity 0.009 and 0.035 W · m −1 · K −1 0.009 and 0.035 W · m −1 · K −1 identical for the cases described in Sec. II.D.…”

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confidence: 99%