Aerodynamic and Aeroelastic Characteristics of a Tension Cone Inflatable Aerodynamic Decelerator
Aerodynamic and Aeroelastic Characteristics of a Tension Cone Inflatable Aerodynamic Decelerator
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张力锥充气气动减速器的气动和气动弹性特性
DOI：
10.2514/6.2009-2967
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发表时间：
2009
期刊：
影响因子：
--
通讯作者：
R. Braun
中科院分区：
文献类型：
--
作者：
I. Clark;J. Cruz;M. Hughes;J. Ware;Albert Madlangbayan;R. Braun
通过风洞试验研究了张力锥充气气动减速器的超声速气动和气动弹性特性。进行了两组测试：一组使用刚性模型，另一组使用纺织模型。使用刚性模型进行的测试，马赫数范围为 1.65 至 4.5，攻角为 -12 至 20 度。发现在测试范围内，轴向力矩、法向力矩和俯仰力矩系数对马赫数不敏感。相对于攻角，轴向力系数几乎恒定（C(sub A) = 1.45 +/- 0.05）。法向力矩系数和俯仰力矩系数与迎角几乎呈线性关系。俯仰力矩系数表明模型关于参考点是静态稳定的。纹影图像和视频显示了分离的弓形激波，没有证据表明在所有调查的马赫数下存在大面积的分离流和/或嵌入式激波。使用马赫数为 2.5 的纺织模型获得了定性相似的静态空气动力系数和流动可视化结果。使用充气纺织模型，确定将模型维持在完全充气配置所需的环面压力。人们发现这种压力对充气模型结构配置的细节很敏感。其他测试包括刚性模型的表面压力测量以及充气模型的展开和充气测试。
The supersonic aerodynamic and aeroelastic characteristics of a tension cone inflatable aerodynamic decelerator were investigated by wind tunnel testing. Two sets of tests were conducted: one using rigid models and another using textile models. Tests using rigid models were conducted over a Mach number range from 1.65 to 4.5 at angles of attack from -12 to 20 degrees. The axial, normal, and pitching moment coefficients were found to be insensitive to Mach number over the tested range. The axial force coefficient was nearly constant (C(sub A) = 1.45 +/- 0.05) with respect to angle of attack. Both the normal and pitching moment coefficients were nearly linear with respect to angle of attack. The pitching moment coefficient showed the model to be statically stable about the reference point. Schlieren images and video showed a detached bow shock with no evidence of large regions of separated flow and/or embedded shocks at all Mach numbers investigated. Qualitatively similar static aerodynamic coefficient and flow visualization results were obtained using textile models at a Mach number of 2.5. Using inflatable textile models the torus pressure required to maintain the model in the fully-inflated configuration was determined. This pressure was found to be sensitive to details in the structural configuration of the inflatable models. Additional tests included surface pressure measurements on rigid models and deployment and inflation tests with inflatable models.