FIELD: aviation.
SUBSTANCE: invention relates to spacecrafts (SC) for scientific research of physical phenomena and development of various systems and elements of a spacecraft in the satellite orbit and during descent in the atmosphere. The returned spacecraft contains a laboratory compartment (1) connected to the instrument compartment body (2), a frontal aerodynamic screen (3) of a segmentally conical shape and a braking motor installation (4). The screen (3) consists of a rigid central part (5) and a peripheral part in the form of a main inflatable braking device (6), covered externally by a flexible thermal protection. Test objects, for example heat protection samples can be asrranged on the rigid part (5). To reduce the landing speed, the RSC is equipped with an additional inflatable braking device (7) of toroidal form. The device (7) is connected to the compartment body (1) by a power conical shell of a fabric material with low gas permeability. It opens at subsonic flight speeds. In the transport position, the RSC has small dimensions due to the tight packing of the sealed shells of the braking devices.
EFFECT: expansion of the complex of scientific and technological problems solved by the returning research space apparatus both in orbit and during descent in the atmosphere.
3 cl, 3 dwg
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Authors
Dates
2017-11-01—Published
2015-12-23—Filed