NASA Conference Publication, 3275. izdevums,3. daļaScientific and Technical Information Office, National Aeronautics and Space Administration., 1993 |
No grāmatas satura
1.–3. rezultāts no 50.
1062. lappuse
... thickness which provided the best match to the measured reflectance data , the thickness of nickel oxide on the surface was determined . The pre - flight reflectance measurements indicated that 10 Å of oxide was already present . After ...
... thickness which provided the best match to the measured reflectance data , the thickness of nickel oxide on the surface was determined . The pre - flight reflectance measurements indicated that 10 Å of oxide was already present . After ...
1302. lappuse
... thickness in the Ram fluence of LDEF , but these lost only 0.0055 inches in thickness or about 1/2 the predicted loss . In the case of fluoropolymers like FEP Teflon , the effect was reversed . The EOIM - 2 data predicted only a 0.00025 ...
... thickness in the Ram fluence of LDEF , but these lost only 0.0055 inches in thickness or about 1/2 the predicted loss . In the case of fluoropolymers like FEP Teflon , the effect was reversed . The EOIM - 2 data predicted only a 0.00025 ...
1364. lappuse
... thickness S > 0 , discharge ; S < 0 , no discharge 100 Top contact thickness Silicon Wafer 0.3 mm thick Aluminum .1 micron thickness 10 Threshold Velocity ( km / sec ) 0.1 Dielectric Thickness 1.7 micron 1.0 micron Bottom Contact MOS ...
... thickness S > 0 , discharge ; S < 0 , no discharge 100 Top contact thickness Silicon Wafer 0.3 mm thick Aluminum .1 micron thickness 10 Threshold Velocity ( km / sec ) 0.1 Dielectric Thickness 1.7 micron 1.0 micron Bottom Contact MOS ...
Saturs
Four Space Application Materials Coatings on the LongDuration | 854 |
Author Index | 857 |
Early Results from the Ultra Heavy Cosmic Ray Experiment 129 | 860 |
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absorptance active addition aluminum ambient analysis anodized Archive areas atomic oxygen attached beam calculated carbon cell Center coatings components composite contamination cover debris degradation detectors determined developed direct distribution Earth effects efficiency electron energy EOIM-III erosion Evaluation experiment exposed exposure Facility Figure flight flown fluence flux ground hardware heated impact increase indicated Interactions Kapton laboratory layer LDEF loss lubricant mass mass spectrometer materials measurements mirrors mission NASA O-atom observed obtained operations optical orbit oxide paint particle passive payload peak performed photographs plate polymer post-flight produced properties protection radiation reaction reactivity reflectance region requirements Research resistance samples scattering sensor showed shown in figure Shuttle significant silicon similar solar space environment Space Station spacecraft specimens spectra structure substrate surface System Table Teflon temperature thermal thermal control thickness tray vacuum values wavelength