By Gilmore, David G.(eds.)
The e-book is a revised and up to date version of satellite tv for pc Thermal keep watch over instruction manual, released in 1994. The identify switch displays the extended scope of this paintings, which now comprises thermal environments and layout options for interplanetary spacecraft, as well as the Earth-orbiting satellites that have been the point of interest of the unique guide. The reader will now locate an up-to-date characterization of the thermal surroundings in Earth orbit, new fabric documenting the environments of interplanetary missions, extra specific information regarding all of the thermal regulate parts present in the 1st variation, and presentation of a few more moderen applied sciences equivalent to warmth switches and precision temperature keep an eye on techniques.
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Additional info for Spacecraft Thermal Control Handbook, Volume 1 - Fundamental Technologies
Orbit-beta-angle histories for sun-synchronous, 833-km orbits. Low Earth Orbits The chief advantage in thinking in terms of [3 is that it simplifies the analysis of orbital thermal environments. By analyzing the environments at several discrete values, one can be confident that all possible combinations of orbit RAAN and sun day angles have been covered. ,. 9_ 100 o e- ~ - (D c.. tl:l t,.. Earth IR 0 15 J 30 (W/m2) J 45 60 Beta angle (deg) 0 O9 75 Fig. 19. Cylinder in low Earth orbit.
Over the years some have questioned the appropriateness of using both the highest albedo and highest IR when performing a hot-case spacecraft thermal analysis, or both the lowest albedo and lowest IR when performing a cold-case analysis. The rationale is that if albedo is high, then the local Earth temperature, and therefore emitted planetary IR, must be low because so much sunlight is being reflected. The MSFC study shows that this reasoning is valid to some extent. As illustrated by the contour plots of 128-second data shown in Fig.
For 12-hour and geosynchronous orbits, these equations may be slightly in error. For any given satellite, [3 will vary continuously with time because of the orbit nodal regression and the change in the sun's fight ascension and declination over the year. The regression rates as a function of inclination for circular orbits of different altitudes are shown in Fig. 14. The sun's fight ascension and declination throughout the year are shown in Fig. 15. ,. 2 3200 -- 6400 . _ ° It. 16,000 0 90 80 70 60 50 40 30 Beta angle (deg) Fig.