FIELD: astronautics.
SUBSTANCE: invention relates to space engineering, particularly, to spacecraft (SC) thermal-vacuum testing in full-scale conditions. Test bench for thermal testing of spacecraft in conditions simulating full-scale, includes a vacuum chamber with a loading cover, a vacuum system, a cryogenic screen, a simulator of solar radiation, a support-rotary device for placing spacecraft, vacuum chamber operation control system and solar radiation simulator, SC operation control system. Vacuum chamber is made in the form of two cylinders. Cylinders are perpendicular to each other. Support-turning device is arranged in lower part of horizontal cylinder. Simulator of solar radiation is made in the form of two sources of solar radiation - horizontal and vertical. When the spacecraft is placed on the rotary support device, the solar radiation is exposed to high accuracy characteristics as a result of inhomogeneity of the levels of density of the incident radiation flux, non-parallelism and specific thermal power of the incident heat flux.
EFFECT: higher reliability of test results.
1 cl, 1 dwg
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Authors
Dates
2020-10-21—Published
2020-01-20—Filed