Downloaded from https://www.everyspec.com MIL-STD-81OC D 2.2 Heat source (radiant). Heat source systems shall be capable of producing the heating effects of SOlar energY, planet radiation, and albedo on test specimens within the space simulator.““” 2. 2.1 Solar-simulator. The simulator shall be capable of providing radiant energy correspondingto that of ‘the Sun.in space. The total solar energy shall be equal to the “applicablevalue of table 517.2-11, column 2. The degree to which the solar environmentmust be simulated for particular tests is speci- fied in table 517.2-IV. Table 517.2-11. Average Radiation Characteristicsof Planets Incident Planet.
Planetary radiation Planet thermal equivalent inten ity 5 ALBEDO 5 radia ion black body (w/m ) (w/m ) temperature Planet .(KO) Earth 1383 0.34 213 250 Mars 583 0.148 134 226 2586 ,0.67 226 249 I Venus . 284 moon I v Performance requirements for a specific test should reference the space solar simulator classification specified in table 517.2-111. Earth’s 1353 0.072 336 b Table 517.2-111. Solar Simulator Classification :lassI Class II Class III Solar beam c 2° *3% max. tS.O% max. ~ 4° Greater than *5% Greater than divergence angle Spectrum In accordance with table g/ 1/ Calculated effective absorptancewithin S percent of calculated Johnson solar absorptance.
~/ Calculated effective absorptancewithin 10 percent of calculated Johnson solar absorptance, S17.2-3 METHOD 517.2