| 摘要 |
FIELD: aircraft engineering. ^ SUBSTANCE: invention relates to space engineering and can be used in developing and producing rocket-carrier ascent unit. In compliance with this invention, the proposed ascent unit comprises a nose cone, spacecraft made up of, at least, one compartment with its surface furnished with vacuum thermal shield insulation. Additionally, it comprises the device that ensures required durability and thermal properties of aforesaid insulation and represents a set of through draining holes uniformly arranged on the insulation surface to communicate interlayer spaces of gas medium of the said insulation and, under it, with gas medium spaces below the nose cone. Reflecting shields are mounted above the said draining holes with a clearance with respect to aforesaid insulation. The nose cone is furnished with drain holes, at least, one of which communicates gas medium space under the said nose cone with atmosphere. ^ EFFECT: reduced pressure differences acting on vacuum thermal shield insulation and nose cone and provision of required thermal properties of insulation. ^ 4 dwg |
