Response of Heatshield Material at Stagnation Point of Pioneer-Venus Probes
Response of Heatshield Material at Stagnation Point of Pioneer-Venus Probes
复制标题
先驱者-金星探测器驻点处隔热罩材料的响应
DOI：
10.2514/2.6697
复制
发表时间：
2002
影响因子：
2.1
通讯作者：
K. Sawada
中科院分区：
文献类型：
--
作者：
H. Ahn;Chul Park;K. Sawada
重新计算了四架先锋-金星探测器在隔热罩驻点处的烧蚀、热解气的形成和去除以及热传导现象。热解气体的运动是通过求解气体的质量和动量方程来计算的，考虑了摩擦力和惯性力。所开发的计算机代码在两个地面用例和一个e - 8测试用例中得到了满意的结果。为了计算先锋-金星e - ight的情况，使用了最近计算的对流和辐射加热率值。在热电偶温度为日探头和北探头，其中进入角和e光轨迹是已知的很好的协议。对于夜间探测器和大型探测器，由于进入角和光线轨迹未知，一致性较差。
The ablation, pyrolysis gas formation and removal, and heat conduction phenomena at the stagnation point of theheatshieldforthefourPioneer-Venusprobevehiclesarecalculated.Themotionofthepyrolysisgasiscalculated by solvingthemassand momentum equationsforthegas,accountingforfrictionandinertial forces. Thedeveloped computer code gives satisfactory results when applied to two ground-based cases and one e ight-test case. For the calculation of the Pioneer-Venus e ight cases, recently calculated values of convective and radiative heating rates are used. Good agreement is seen in thermocouple temperature for the day probe and north probe for which the entry angle and e ight trajectory are known. For the night probe and large probe, for which entry angle and e ight trajectory are unknown, agreement is poor.