Reentry Demonstration of Flare-type Membrane Aeroshell for Atmospheric Entry Vehicle using a Sounding Rocket
Reentry Demonstration of Flare-type Membrane Aeroshell for Atmospheric Entry Vehicle using a Sounding Rocket
复制标题
使用探空火箭进行大气进入飞行器的喇叭形膜航空壳再入演示
DOI：
10.2514/6.2013-1388
复制
发表时间：
2011
影响因子：
2.1
通讯作者：
D. Akita
中科院分区：
文献类型：
--
作者：
Kazuhiko Yamada;Yasunori Nagata;T. Abe;Kojiro Suzuki;O. Imamura;D. Akita
柔性空气动力壳体作为一种新型的航天运输系统，由于其低的弹道系数，可以有效地降低大气层内的气动加热，因而受到人们的广泛关注。我们进行了风洞试验，数值模拟和飞行演示使用气球，重点是一个胶囊型飞行器与耀斑型膜气动力壳体由一个可充气的环面框架支持。下一步，计划使用探空火箭进行再入演示，作为一个重要的里程碑。正在研制一种试验飞行器，它有一个直径为1.2米、由一个可充气的圆环支撑的耀斑型薄膜空气动力壳体，用于再入演示。在使用探空火箭的再入演示中，实验飞行器从150 km高度再入大气层，并经历高超声速自由飞行，马赫数为4.5，中等气动加热，停滞时的热通量约为20 kW/m。在再入过程中，飞行轨迹、气动壳体的行为和气动加热条件将由机载传感器和遥测系统测量。在这次飞行试验中可以证明柔性空气动力学壳体作为再入飞行器减速器的性能，并且可以利用这次飞行数据验证事先在地面试验中获得的结果和知识。
A flexible aeroshell for atmospheric entry vehicles has attracted attention as an innovative space transportation system because the aerodynamic heating during the atmospheric entry can be reduced dramatically due to its low ballistic coefficient. We carried out wind tunnel tests, numerical simulations and flight demonstrations using balloons, focusing on a capsule-type vehicle with a flare-type membrane aeroshell sustained by an inflatable torus frame. For the next step, a reentry demonstration using a sounding rocket is planned as a important milestone. The experimental vehicle which has a 1.2-meter diameter flare-type thin membrane aeroshell sustained by an inflatable torus is being developed for the reentry demonstration. In the reentry demonstration using a sounding rocket, the experimental vehicle reenters the atmosphere from an altitude of 150 km and experiences a hypersonic free flight where the Mach Number is 4.5 and the moderate aerodynamic heating where the heat flux at a stagnation is about 20kW/m. The flight trajectory, the behavior of the aeroshell and the aerodynamic heating condition will be measured by onboard sensors and a telemetry system during the reentry. The performance of the flexible aeroshell as a decelerator for reentry vehicles can be demonstrated in this flight test and the results and knowledge obtained in ground tests beforehand can be validated using this flight data.
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