Visualization of a Capsule Entry Vehicle Reaction-Control System (RCS) Thruster
Visualization of a Capsule Entry Vehicle Reaction-Control System (RCS) Thruster
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太空舱进入飞行器反应控制系统 (RCS) 推进器的可视化
DOI：
10.2514/6.2006-1532
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发表时间：
2006
期刊：
影响因子：
--
通讯作者：
D P. Patry
中科院分区：
文献类型：
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作者：
P. Danehy;J. Wilkes;G. Brauckmann;D. W. Alderfer;S. B. Jones;D P. Patry
在美国宇航局兰利研究中心31英寸马赫10空气风洞中，使用平面激光诱导荧光(PLIF)对阿波罗几何结构太空舱试件尾部发射的反应控制系统(RCS)射流进行可视化。RCS喷流垂直于模型后表面，标称马赫数为2.94。喷射气的质量组成为95%的氮气(N2)和5%的一氧化氮(NO)。RCS射流流量在0到0.5标准升/分钟之间变化，攻角和隧道滞留压力也不同。用PLIF对NO分子进行激发，以实现流动显示。这些流动可视化图像被处理以确定轨迹并量化RCS喷嘴的扑动。喷流轨迹测量的空间分辨率约为1 mm，在喷流羽流远场的单次测量精度估计为0.02 mm。根据喷口中心线位置的标准偏差测量，喷口扑动的大小为0.9 mm，而喷口直径为1.5-4 mm(半大全宽)。获得纹影流动显示图像，并与PLIF进行比较。表面压力也被测量和呈现。NASA兰利开发的虚拟诊断界面(VIDI)技术被用来叠加和可视化数据集。这些测量显示了PLIF方法的一些能力，同时为计算流体动力学(CFD)验证提供了测试案例。
Planar laser-induced fluorescence (PLIF) was used to visualize the reaction control system (RCS) jet flow emanating from the aft-body of an Apollo-geometry capsule test article in the NASA Langley Research Center 31-Inch Mach 10 Air wind tunnel. The RCS jet was oriented normal to the aft surface of the model and had a nominal Mach number of 2.94. The composition of the jet gas by mass was 95% nitrogen (N 2 ) and 5% nitric oxide (NO). The RCS jet flowrate varied between zero and 0.5 standard liters per minute and the angle of attack and tunnel stagnation pressure were also varied. PLIF was used to excite the NO molecules for flow visualization. These flow visualization images were processed to determine the trajectory and to quantify the flapping of the RCS jet. The spatial resolution of the jet trajectory measurement was about 1 mm and the single-shot precision of the measurement was estimated to be 0.02 mm in the far field of the jet plume. The jet flapping, measured by the standard deviation of the jet centerline position was as large as 0.9 mm, while the jet was 1.5-4 mm in diameter (full width at half maximum). Schlieren flow visualization images were obtained for comparison with the PLIF. Surface pressures were also measured and presented. Virtual Diagnostics Interface (ViDI) technology developed at NASA Langley was used to superimpose and visualize the data sets. The measurements demonstrate some of the capabilities of the PLIF method while providing a test case for computational fluid dynamics (CFD) validation.