FIELD: space engineering. SUBSTANCE: proposed method includes placing the spacecraft in vacuum chamber and irradiating its external surfaces with thermal flux simulating solar radiation at change of spacecraft orientation relative to this flux. In the course of tests definite densities of thermal flux are set and angles of turn of spacecraft relative to normal to datum planes of sensors are measured. Simulation of external thermal flux is ensured through simultaneous change of angle of turn of spacecraft relative to said normal and density of thermal flux; synchronization of turn and change of density of flux is performed in accordance with definite relationships. Device proposed for realization of this method includes vacuum chamber with swivel unit inside it for mounting the spacecraft and solar radiation simulator including illuminating part in form of shield with lights, projection part consisting of mirror and lens optical system and input unit including scatterer and flat- convex lens; it also includes control damper located between illuminating part and input unit; said damper is used for control of illumination intensity and is provided with drive. Damper is made in form of two convergent shields whose planes are normal relative to axis of optical system and are shifted relative to each other; shields are provided with cuts forming flow section for thermal flux; cuts are made in form of square with center lying in optical system axis and diagonally coinciding with direction of motion of shields; damper drive ensures motion of shields depending on change in density of thermal flux falling on spacecraft under test. EFFECT: enhanced informativeness of tests; reduced testing time. 3 cl, 4 dwg
