Starprobe thermal shield system design concepts
Starprobe thermal shield system design concepts
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Starprobe热屏蔽系统设计概念
DOI：
10.2514/6.1982-78
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发表时间：
1982
期刊：
影响因子：
--
通讯作者：
R. Miyake
中科院分区：
文献类型：
--
作者：
C. Maag;J. Millard;R. Miyake
回顾了NASA恒星探测器航天器的任务目标、飞行轨迹和材料耐久性要求。航天器将使用木星引力辅助装置，在太阳四个太阳半径内通过，研究太阳附近的场和粒子，进行相对论和重力实验，并观察从光球层到日冕的太阳大气结构。给出了系统尺寸和质量设计的约束，并指出系统需要在近日点承受2500K，对仪器有效载荷进行热绝缘，有用于光学测量的管子，并提供防止陨石损坏的保护。还需要一个次级屏蔽来分配通过初级屏蔽并可能危及有效载荷的热辐射。讨论了设计选项，以及温度控制要求和具有足以满足2.5 mg/秒标准的质量损失率特性的圆锥形碳-碳主屏蔽体。
The mission goals, flight trajectory, and material durability requirements for the NASA Starprobe spacecraft are reviewed. The spacecraft will use a Jovian gravity assist to pass within four solar radii of the sun to study fields and particles near the sun, perform experiments dealing with relativity and gravity, and observe the structure of the solar atmosphere from the photosphere to the corona. Constraints on the system size and mass design are given, and the system is noted to be required to withstand 2500 K at perihelion, thermally insulate the instrument payload, have a tube for optical measurements, and provide protection from meteorite damage. A secondary shield is also required to dispense thermal radiation that passes the primary shield and could endanger the payload. Design options are discussed, along with temperature control requirements and a conical carbon-carbon primary shield with mass-loss rate characteristics sufficient to meet a 2.5 mg/sec criterion.