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Tail-wing Flutter Analyses of a Balloon-based Operation Vehicle for Microgravity Experiments

机译:基于气球的微重力实验飞行器尾翼颤振分析

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Three-dimensional aeroelastic phenomena are numerically simulated for the development of a balloon-based operation vehicle (BOV) proposed by the Japan Aerospace Exploration Agency. The structures of the all-moving tail wing composed of several materials are modeled in detail using a finite element method. The vibration modes obtained from the eigenvalue analysis of the three-dimensional solid model are mapped to two-dimensional iso-parametric shell elements for efficient fluid-structure coupled analysis using unstructured computational fluid dynamics. The methods are validated by the fluttering of the National Aerospace Laboratory wing, which has a similar planform to the BOV tail and is referred to as a standard problem. The shape of the flutter boundary is explained by the characteristic shift of the aerodynamic center. The simulation results show the BOV tail has a sufficient safety margin for flutter along the freefall flight path.
机译:对三维气动弹性现象进行了数值模拟,以开发日本航空航天局提出的基于气球的作业车(BOV)。使用有限元方法对由多种材料组成的全动尾翼的结构进行了详细建模。从三维固体模型的特征值分析获得的振动模式映射到二维等参壳单元,以便使用非结构化计算流体动力学进行有效的流固耦合分析。国家航空航天实验室机翼的颤动验证了这些方法,该机翼与BOV机尾的平面图相似,被称为标准问题。颤振边界的形状由空气动力学中心的特征偏移来解释。仿真结果表明,BOV尾翼具有足够的安全裕度,可以沿自由落体飞行路线扑动。

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