FIELD: aircraft engineering.
SUBSTANCE: invention can be used for thermal control over payload. Proposed device comprises heat-insulating web, heat-insulating coats, orifices for feed and release of thermal control component in head cowl and adapter section. Simultaneously, thermal control gas component is fed via orifices above or under heat-insulating web rigidly fitted between rocket carrier and payload inside head cowl and adapter section. Said thermal control gas component flows along payload lower part and heat-insulating web or along heat-insulating web and connected to rocket carrier head end.
EFFECT: efficient payload thermal control.
2 cl, 5 dwg
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