Aerodynamic Heating Around Flare-Type Membrane Inflatable Vehicle in Suborbital Reentry Demonstration Flight
Aerodynamic Heating Around Flare-Type Membrane Inflatable Vehicle in Suborbital Reentry Demonstration Flight
复制标题
亚轨道再入示范飞行中喇叭形薄膜充气飞行器周围的气动加热
DOI：
10.2514/1.a33170
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发表时间：
2015
影响因子：
1.6
通讯作者：
Kojiro Suzuki
中科院分区：
文献类型：
--
作者：
Yusuke Takahashi;Kazuhiko Yamada;T. Abe;Kojiro Suzuki
使用探空火箭进行了先进再入飞行器的演示飞行。该飞行器配备了一个由可充气圆环结构展开的柔性（膜）空气动力学壳体。其最显著的特点是弹道系数低，能够减少高空的气动加热和减速。在亚轨道再入过程中，通过嵌入式热电偶测量了柔性空气动力学壳体背面和密封舱内部几个位置的温度。使用测量的温度历史，结合数值预测，其中进行的流场模拟加热的飞行器的气动加热行为进行了研究。在流场模拟中，假设了层流和湍流，并考虑了柔性壳体的变形。建立了囊式和膜式气动壳体的热模型，计算了飞行器气动加热过程中表面热流分布。
A demonstration flight of an advanced reentry vehicle was carried out using a sounding rocket. The vehicle was equipped with a flexible (membrane) aeroshell deployed by an inflatable torus structure. Its most remarkable feature was the low ballistic coefficient that enables reduction in aerodynamic heating and deceleration at a high altitude. During the suborbital reentry, temperatures at several locations on a backside of the flexible aeroshell and inside the capsule were measured by means of embedded thermocouples. The aerodynamic heating behavior of the vehicle was investigated using the measured temperature history, in combination with a numerical prediction in which a flow-field simulation of the heating was conducted. In this flow-field simulation, both laminar flow and turbulent flow were assumed, and the deformation of the flexible aeroshell was considered. A thermal model of the capsule and membrane aeroshell was developed, and the heat flux profiles of the vehicle surface during aerodynamic heat...
影响因子：
1.6
作者：
Kazuhiko Yamada;D. Akita;E. Sato;Kojiro Suzuki;T. Narumi;T. Abe
通讯作者：
Kazuhiko Yamada;D. Akita;E. Sato;Kojiro Suzuki;T. Narumi;T. Abe