| 摘要 |
FIELD: space engineering; space vehicles designed for flight to Sun. SUBSTANCE: solar probe has front heat shield made in form of cone and additional heat shield made in form of truncated cone whose larger base is connected with cone. Inverted cone consists of three structurally identical sections. Each section of inverted cone consists of shield- diaphragm arranged perpendicularly relative to longitudinal axis of vehicle, lateral surface and L-shaped thermal tubes. Evaporating section of each thermal tube is mounted on surface of shield-diaphragm and its condensing section is mounted on lateral surface. Cone and section of inverter cone are inter- connected through heat-insulating members. Mounted on end of last section is load-bearing ring which holds heat-insulated wall and instrument container made in form of flat thermal accumulator. Some sensors of scientific equipment are arranged on hinged rods. Main thermal load is taken up by front heat shield. Part of thermal flow is reflected from its surface and other part is absorbed by cone. Integral thermal flow sets equilibrium surface temperature at cone corresponding to given moment of time. When turning cone will re-reflect thermal energy to shield-diaphragm of first section of inverted cone. Present equilibrium temperature corresponding to secondary thermal flow is set at diaphragm. Part of thermal energy is transferred from shield-diaphragm to lateral surface of inverter cone by means of thermal tubes; lateral surface of inverted cone is used as radiation panel of this part of cone. Part of heat is released from it to surrounding space. This scheme of reduction of density of thermal flow energy may be considered as first stage in three-stage thermal protection of instrument container. EFFECT: enhanced efficiency of thermal protection of equipment against solar thermal flow. 4 cl, 4 dwg |
