Lunar surface thermal characteristics from Surveyor 1

Lucas, J. W.; Conel, J. E.; Hagemeyer, W. A.; Garipay, R. R.; Saari, J. M.

doi:10.1029/jz072i002p00779

Cited by 31 publications

(13 citation statements)

References 3 publications

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“…Apollo 15 and 17 missions are the only two experiment sites for probing temperature on lunar surface. And the results showed that the highest temperature of Apollo 15 landing site was 374 K and the lowest was 92 K. Besides, the highest and the lowest temperatures of Apollo 17 landing site were almost 10 K higher than that of Apollo 15 landing site [2]. But according to reanalysis of Apollo 15 and 17 landing sites surface and subsurface temperature by Wieczorek and Huang [3], the lunar surface temperature was nearly correlated to 18.6-year orbital period of the Moon.…”

Section: Methods Of Obtaining Temperature and Temperature Profile Of mentioning

confidence: 81%

“…The highest tempera- ture at Apollo 15 landing site was 374 K, and the lowest was 92 K. The highest and the lowest temperatures of Apollo 17 landing site were about 10 K higher than those of Apollo 15 landing site [2]. Figure 10 shows simulated temperatures at Apollo landing sites by our methods above, showing that the highest temperature at Apollo 15 is about 370 K and the lowest is about 80 K. The highest and lowest temperatures at Apollo 17 are about 380 and 90 K, respectively, which are consistent with the probed results.…”

Section: The Variations Of Lunar Surface Temperature At Special Pointmentioning

confidence: 80%

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Simulations on the influence of lunar surface temperature profiles on CE-1 lunar microwave sounder brightness temperature

Wang

Jiang

2010

Sci. China Earth Sci.

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Surface temperature profile is an important parameter in lunar microwave remote sensing. Based on the analysis of physical properties of the lunar samples brought back by the Apollo and Luna missions, we modeled temporal and spatial variation of lunar surface temperature with the heat conduction equation, and produced temperature distribution in top 6.0 m of lunar regolith of the whole Moon surface. Our simulation results show that the profile of lunar surface temperature varies mainly within the top 20 cm, except at the lunar polar regions where the changes can reach to about 1.0 m depth. The temperature is stable beyond that depth. The variations of lunar surface temperature lead to main changes in brightness temperature (T B ) at different channels of the lunar microwave sounder (CELMS) on Chang'E-1 (CE-1). The results of this paper show that the temperature profile influenced CELMS T B , which provides strong validation on the CELMS data, and lays a solid basis for future interpretation and utilization of the CELMS data. CE-1 lunar Microwave Sounder (CELMS), lunar surface temperature, lunar surface temperature profile, heat conduction equation, simulation of brightness temperature Citation:Li Y, Wang Z Z, Jiang J S. Simulations on the influence of lunar surface temperature profiles on CE-1 lunar microwave sounder brightness temperature.CE-1 lunar Microwave Sounder (CELMS) is a main payload of Chang'E-1 Moon orbit satellite, which is used to obtain brightness temperatures of lunar surface and then retrieve thickness of lunar regolith. The microwave radiation of lunar regolith is consisted of brightness temperature contribution from all layers under the surface. The probing depth of CELMS depends on frequency. The physical characteristics of lunar regolith at different depth, such as temperature, dielectric constant, density, thermal conductivity and specific heat, etc., are different. So are the emissivity, transmissivity, and physical temperature of different layers.In addition, the rates that different layers' radiation brightness temperatures reach the surface are different. Thus, by analyzing T B obtained by CELMS, we can retrieve the depth where the radiation came from and then retrieve the physical characteristics of lunar regolith in that depth. The influences of these physical parameters on T B received by CELMS are different, and the parameters are the scientific objectives of CELMS, therefore, it is necessary to analyze the relationship among them and study the mechanism that leads to the influences. This paper focuses on the influence of different lunar temperature at different regolith layer on microwave brightness temperature. The Sun is the sole source of energy for lunar surface temperature. Since there is no atmosphere on lunar surface, lunar surface temperature changes dramatically following rising and setting of the Sun. Because

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Section: Methods Of Obtaining Temperature and Temperature Profile Of mentioning

confidence: 81%

Section: The Variations Of Lunar Surface Temperature At Special Pointmentioning

confidence: 80%

Simulations on the influence of lunar surface temperature profiles on CE-1 lunar microwave sounder brightness temperature

Wang

Jiang

2010

Sci. China Earth Sci.

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“…Luna 15 crashed into the lunar surface while Armstrong and Aldrin were on it, but Luna 16, 20 and 24 soft-landed and then returned a total of about 300 g of lunar soil to the Earth. Television cameras on Luna 1 and Surveyor 1 had observed dust and made limited deductions about its mobility (Lucas et al 1967;Rennilson & Criswell 1974). Surveyor 2 also crashed, but Surveyor 3 landed on 30 April 1967.…”

Section: Apollo Culture Of Disdain Of Dust Except By Astronautsmentioning

confidence: 96%

Apollo measurements of lunar dust amidst geology priorities

O’Brien

2012

Australian Journal of Earth Sciences

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“…11 "" 24 To the uncertainties in solar irradiation given in Table 2, the effect of seasonal variation must be added (0.966 to 1.034). Discussions of the differences, total and spectral, between Johnson 15 and Nicolet 16 (see Fig.…”

Section: Uncertainty In Input Informationmentioning

confidence: 99%

“…22 -23 Surveyor I data also indicated a non-Lambertian surface. 24 However, a cosine (Lambertian) surface is generally assumed.…”

Section: Uncertainty In Input Informationmentioning

confidence: 99%

Temperature variance in spacecraft thermal analysis.

Bevans¹,

Ishimoto²

1968

Journal of Spacecraft and Rockets

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Fig. 4 Figure-of-merit for the max rp and tan strategiesfor a near-circular orbit whose apogee devaluation factor is 6.7.orbit have the same lifetime. The ratio 10 naut miles/1.5 naut miles = 6.7 is the factor that specifies the lifetime increasing capability of a perigee increase compared to an apogee increase. This ratio is valid only for small changes in altitude. A comparison of the following kind may now be formulated. A figure-of-merit for the max rp strategy may be determined by dividing values of (Ar^Ap |max r P )/(AV/Vp) by 6.7, as an example, and adding these to corresponding values of (Afp/fp jmax rp)/(ATVFp). As indicated, apogee increases are devalued by the factor that specifies their relative ineffectiveness for increasing lifetime. A figure-of-merit curve for the max r P strategy is presented as a function of v in Fig. 4. A similar curve is presented for the tan strategy. The max TP strategy is clearly-superior for all values of v except near perigee and exactly at apogee. The tan strategy is superior for 0 < v < 36° and for 324° < v < 360° and is equal to the max r P strategy at apogee. Max r P is superior to tan for 36° < v < 324° by differences that vary from zero to approximately 10% near v = 65° and v = 295°. Of course, the differences and the exact boundaries between max r P and tan superiority depend on the apogee effectiveness factor used, 6.7 in this case. For larger factors, max r P superiority over tan increases, and vice versa. For example, for e = 0.8, max r P is better than tan by a factor of 1.9 at v = 90° and 270°, and by a factor of 3.7 at v = 30° and 330°. Over-All StrategyThe over-all strategy appears to be to use max rp for all elliptic orbit locations except for a region near perigee where tan should be applied. A further investigation into the regions near v = 36° and v -324° revealed that the $ for maximum figure-of-merit fell between <£ = 0 and 3> ma x /•/>. Thus, the best strategy to follow in these regions is to contour to provide a smooth transition between the max r P and tan strategies. Unfortunately, maximizing the figure-of-merit as a function of v in these transitional regions is not a simple process.However, one other factor should be considered. The effectiveness of max rp decreases with increasing or decreasing departure from apogee. From Fig. 4, the effectiveness is maximum at apogee but is reduced to one-half maximum at v = 75° and 285°. In view of this reduction it may be advisable to turn off the engines as perigee approaches and then turn them on again when the effectiveness increases to an acceptable level. This strategy is reasonable only if the present lifetime is not critical. In the limit, the most effective way to increase lifetime would be to turn on the engines briefly at each apogee passage. The best switching sequence depends on each individual situation. Validity of the EquationsSince the entire analysis assumed small velocity increments, i.e., AF/Fp <$c 1, the range of validity of the derived equations with respect to AF/Fp was examined. It w...

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Lunar surface thermal characteristics from Surveyor 1

Cited by 31 publications

References 3 publications

Simulations on the influence of lunar surface temperature profiles on CE-1 lunar microwave sounder brightness temperature

Simulations on the influence of lunar surface temperature profiles on CE-1 lunar microwave sounder brightness temperature

Apollo measurements of lunar dust amidst geology priorities

Temperature variance in spacecraft thermal analysis.

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