FIELD: astronautics.
SUBSTANCE: invention relates to space engineering, particularly, to design of spacecrafts (SC) for calibrating radar stations. SC comprises a body with instrument compartment, engine unit, orientation and stabilization systems, solar batteries. SC body is made in the form of a rectangular prism, one of the faces of which has a radio-reflecting surface, and is equipped with a flat rectangular plate of radio-reflecting material pivotally connected to the face of the rectangular prism, having radio-reflecting surface. Flat rectangular plate is equipped with a opening mechanism and the fixing unit to one of the faces of the SC body rectangular prism. SC additionally has command radio link equipment (CRLE), consumer navigation equipment (CNE) of GLONASS and/or GPS space systems, onboard computer system (OCS), microcontroller (MC), unit for interfacing the orientation and stabilization systems and fixing assembly with the microcontroller. CRLE, CNE, OCS, MC, unit for interfacing the orientation and stabilization systems and fixing assembly with the microcontroller are interconnected.
EFFECT: high efficiency of calibrating a radar station, expanded performances of the SC during calibration of ground and sea-based radar stations operating on circularly polarized waves with parallel reception of reflected signals, as well as possibility of calibration by value of the SCS of the potential radar stations at small elevation angles (3-5) of degrees and in the operation mode with low radiation power.
11 cl, 6 dwg
