Lunar dust deposition effects on the solar absorptance of thermal control materials

1971 ◽  
Author(s):  
R. DURKEE ◽  
R. HARRIS, JR.
Keyword(s):  
Thermal Control ◽  
Dust Deposition ◽  
Solar Absorptance ◽  
Lunar Dust

Multilayer Tuneable Emittance Coatings with Low Solar Absorptance for Improved Smart Thermal Control in Space Applications

2009 ◽  
Author(s):  
Emile Haddad ◽  
Roman V. Kruzelecky ◽  
Brian Wong ◽  
Wes Jamroz ◽  
Mohamed Soltani ◽  
...  
Keyword(s):  
Thermal Control ◽  
Space Applications ◽  
Solar Absorptance

Solar Effects on Tensile and Optical Properties of Hubble Space Telescope Silver-Teflon Insulation

2006 ◽  
Vol 929 ◽  
Author(s):  
Kim K. de Groh ◽  
Joyce A. Dever ◽  
Aaron Snyder ◽  
Sharon Kaminski ◽  
Catherine E. McCarthy ◽  
...  
Keyword(s):  
Radiation Effects ◽  
Hubble Space Telescope ◽  
Strong Dependence ◽  
Thermal Control ◽  
Space Environment ◽  
Solar Array ◽  
Solar Absorptance ◽  
Space Telescope ◽  
Solar Arrays ◽  
Solar Exposure

ABSTRACTDuring the fourth servicing mission of the Hubble Space Telescope (HST), the second set of solar arrays (SA-II) was replaced with a third set and the SA-II was brought back to Earth. A section of the retrieved SA-II solar array drive arm (SADA) multilayer insulation (MLI), which experienced 8.25 years of space exposure, was provided to NASA Glenn Research Center for environmental durability analyses of the top layer of silver-Teflon fluorinated ethylene propylene (Ag-FEP). Because the SADA MLI had solar and anti-solar facing surfaces and was exposed to the space environment for a long duration, it provided a unique opportunity to study solar effects on environmental degradation of Ag-FEP, a commonly used spacecraft thermal control material. Therefore, the objective of this research was to characterize the degradation of retrieved HST SADA Ag-FEP with particular emphasis on solar radiation effects. Data obtained included tensile properties, solar absorptance, surface morphology and chemistry. The solar facing surface of the SADA was found to be extremely embrittled and contained numerous through-thickness cracks. Tensile testing indicated that the solar facing surface lost 60% of its mechanical strength and 90% of its elasticity while the anti-solar facing surface had ductility similar to pristine FEP. The solar absorptance of both the solar facing surface (0.155 ± 0.032) and the anti-solar facing surface (0.208 ± 0.012) were found to be greater than pristine Ag-FEP (0.074). Solar facing and anti-solar facing surfaces were microscopically textured, and locations of isolated contamination were present on the anti-solar surface resulting in increased localized texturing. Yet, the overall texture was significantly more pronounced on the solar facing surface indicating a synergistic effect of combined solar exposure and increased heating with atomic oxygen erosion. The results indicate a very strong dependence of degradation, particularly embrittlement, upon solar exposure with orbital thermal cycling having a significant effect.

Evaluation of Lunar Dust Mitigation Strategies for Thermal Control Surfaces

2011 ◽  
Author(s):  
James Gaier ◽  
Deborah Waters ◽  
Bruce Banks ◽  
Khrissaundra Journey ◽  
Steven Christopher
Keyword(s):  
Thermal Control ◽  
Mitigation Strategies ◽  
Lunar Dust ◽  
Control Surfaces

Simulations of Lunar Dust interaction with exploration systems and instruments

2021 ◽  
Author(s):  
Fabrice Cipriani ◽  
François Piette
Keyword(s):  
Lunar Surface ◽  
Imaging System ◽  
Compositional Analysis ◽  
Thermal Control ◽  
The Moon ◽  
Lunar Dust ◽  
Dust Transport ◽  
Predictive Algorithms ◽  
Performance Variations

<p>Lunar Dust is representing both an engineering challenge for future exploration missions due to systems potential contamination (due to regolith mobilization during e.g. traverse phases, landings, scooping, astronauts EVAs..) and a scientific target for e.g. mineralogical and compositional analysis of the Lunar surface. Therefore predicting not only interactions with systems but also payloads landed at the lunar surface is an important part of future missions design. Strong partnerships and synergies between agencies and space industries are now allowing the preparation of new missions with challenging timescales, for a return to the Moon in the next couple of years. In this context, the analysis of re-analysis of some of the Apollo era data and other landed assets is of high interest to perform the calibration of predictive algorithms and simulations tools of regolith transport and interactions with systems.</p> <p>The present work is organized in two parts: in the first part, we present a modelling study of two experiments included in the Apollo Lunar Surface Experiment Package (ALSEP): the Lunar Ejecta and Meteoroids Experiment (LEAM), which experienced failures linked to thermal control and the Dust Detector Experiment (DDE) which could measure solar cells performance variations due to dust coverage.</p> <p>In the second part, we present simulation results for the contamination of the Imaging System accommodated on the PROSPECT experiment that will be embarked on the Luna 27 lander, due to land on the Moon in the next couple of years.</p> <p>We will discuss the quality of our predictions, the uncertainties inherent to the measurements, and the way forward in terms of better representation of lunar dust transport and interactions processes through models.</p>

Effect of Simulated Lunar Dust on the Properties of Thermal Control Surfaces

2010 ◽  
Vol 47 (1) ◽  
pp. 147-152 ◽  
Author(s):  
James R. Gaier ◽  
John Siamidis ◽  
Elizabeth M. G. Larkin
Keyword(s):  
Thermal Control ◽  
Lunar Dust ◽  
Control Surfaces

Optical Absorption Properties of Nanotitanium Dioxide Doped ZnO/Silicone Thermal Control Coating

2007 ◽  
Vol 546-549 ◽  
pp. 1725-1728
Author(s):  
Wei Qin ◽  
Xiao Hong Wu ◽  
Gui Mei Zhao ◽  
Xiao Ming Lai ◽  
Li Gong Zhang
Keyword(s):  
Optical Properties ◽  
Visible Region ◽  
Wavelength Region ◽  
Thermal Control ◽  
Infrared Region ◽  
Absorption Properties ◽  
Solar Absorptance ◽  
Doped Zno ◽  
Thermal Control Coatings ◽  
Control Principle

As a kind of white paint, ZnO/silicone thermal control coatings are used commonly in space. In order to implement more effective thermal control in space, nanotitanium dioxide was doped to the coatings. In this paper, different percent of nanotitanium dioxide was appended to the coatings, and thermal control principle was discussed. Optical properties of these coatings were discussed by spectrophotometry and infrared reflectometer. The experimental results show that solar absorptance (αs) of nanotitanium dioxide doped ZnO/silicone thermal control coating is lower in all wavelength region than the coatings without doping, especially in visible region and infrared region. The total solar absorptance of 1% nanotitanium dioxide doped coating is 0.09, which decreases by 36% than the undoped coating..

scholarly journals Tailoring Thin-Film/Lacquer Coatings for Space Applications

2000 ◽  
Vol 12 (1) ◽  
pp. 105-112 ◽  
Author(s):  
Wanda C Peters ◽  
George Harris ◽  
Grace Miller ◽  
John Petro
Keyword(s):  
Thin Film ◽  
Thermal Control ◽  
Radiative Properties ◽  
Space Applications ◽  
Solar Absorptance ◽  
Film Coatings ◽  
Thin Film Coatings ◽  
Thermal Radiative Properties ◽  
Wide Range ◽  
Specular Surfaces

Thin-film coatings have the capability of obtaining a wide range of thermal radiative properties, but the development of thin-film coatings can sometimes be difficult and costly when trying to achieve highly specular surfaces. Given any space mission’s thermal control requirements, there is often a need for a variation of solar absorptance (αs), emittance (∊) and/or highly specular surfaces. The utilization of thin-film coatings is one process of choice for meeting challenging thermal control requirements because of its ability to provide a wide variety of αs/∊ ratios. The radiative properties of thin-film coatings can be tailored to meet specific thermal control requirements through the use of different metals and the variation of dielectric layer thickness. Surface coatings can be spectrally selective to enhance radiative coupling and decoupling. The application of lacquer to a surface can also provide suitable specularity for thin-film application without the cost and difficulty associated with polishing.

Design of an electrostatic lunar dust repeller for mitigating dust deposition and evaluation of its removal efficiency

2014 ◽  
Vol 69 ◽  
pp. 21-31 ◽  
Author(s):  
Nima Afshar-Mohajer ◽  
Chang-Yu Wu ◽  
Robert Moore ◽  
Nicoleta Sorloaica-Hickman
Keyword(s):  
Removal Efficiency ◽  
Dust Deposition ◽  
Lunar Dust

Lunar Cargo Transportation (LuCaT): Semi-Autonomous Vehicle With Suspended Cable and Solar Power

2020 ◽  
Author(s):  
Hershle Ellis ◽  
Chase Casher ◽  
Jamal Longwood ◽  
Abel Taye ◽  
Laura Ruhala ◽  
...  
Keyword(s):  
Waste Heat ◽  
Cooling System ◽  
Autonomous Vehicle ◽  
Thermal Control ◽  
Lunar Cycle ◽  
The Moon ◽  
Unique Problem ◽  
Lunar Dust ◽  
Vehicle Operation ◽  
High And Low Temperatures

Abstract NASA is planning to send astronauts to the moon and then establish sustainable lunar exploration during the 21st Century under the Artemis program. The lunar south pole target site will need ground transportation to transport materials such as lunar ice from one location to another. This paper explores an alternative transportation system that is based on earth aerial tramways, which involves a chassis, wheels, drivetrain, and elevated cables with supporting structure. The wear of regolith lunar dust and the difficulties in traversing the uneven lunar terrain are reduced. Also, the speed and size of the cargo being transported should be superior to the lunar roving vehicle. By implementing a drivetrain system powered by solar energy, long term power generation and vehicle operation is achieved in the south polar region, which remains in sunlight at near horizontal incidence during the lunar cycle. Because of the extreme high and low temperatures of the moon, strength of materials that vary with temperature must be considered. The internal components of the vehicle and the chassis are protected by a lightweight shell. On earth, heat generated by electric charging and use of batteries can be removed by convection with the surrounding air. The lunar atmosphere presents a unique problem of possessing virtually no heat transfer through convection, while solar radiation will add or remove heat more extremely than earth-based conditions. A thermal control system is designed to manage the battery waste heat, utilizing optical solar reflectors and an internal conductive cooling system.

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