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论文:2012,Vol:30,Issue(2):206-211 |
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引用本文： |
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周敏, 周军, 林鹏, 郭建国. 基于变弹翼方式的非结构动网格建模方法研究[J]. 西北工业大学 |
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Zhou Min, Zhou Jun, Lin Peng, Guo Jianguo. Research on and Development of a New and Efficient Dynamic Unstructured Grid Method for Missiles with Morphing Wings Based on the Principle of Spring Shape Changing[J]. Northwestern polytechnical university |
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| 基于变弹翼方式的非结构动网格建模方法研究 |
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| 周敏, 周军, 林鹏, 郭建国 |
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| 西北工业大学 精确制导与控制研究所,陕西 西安 710072 |
| 摘要: |
| 针对变弹翼导弹包含运动边界的复杂非定常流场的求解问题,基于弹簧变形原理,即在网格变形时,网格点与静止边界和运动边界的相对位置关系均保持不变,分别推导了旋转弹翼运动边界上的网格点和受运动边界扰动流场子域上网格点的变形算法,从而发展了一种新的非结构动网格方法,该方法在不降低计算效率的前提下,大大提高了网格的变形能力,并解决了现有研究通常忽略弹翼运动受弹身影响而产生的非刚性变形问题,是基于非结构网格框架下,求解具有复杂运动边界且网格变形较大的非定常流场的一种简单有效的方法。 |
| 关键词:
变弹翼导弹
非结构动网格
弹簧变形
非定常流动
N-S方程
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| Research on and Development of a New and Efficient Dynamic Unstructured Grid Method for Missiles with Morphing Wings Based on the Principle of Spring Shape Changing |
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| Zhou Min, Zhou Jun, Lin Peng, Guo Jianguo |
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| Institute of Precision Guidance and Control,Northwestern Polytechnical University,Xi'an 710072,China |
| Abstract: |
| To solve the complex unsteady flow of a missile with morphing swept wings, we propose a new dynamicunstructured grid method according to the principle of spring shape changing, under which the grid points’relativepositions between stationary boundary and moving boundary are fixed. Sections 1 through 3 of the full paper explainour research and development mentioned in the title, whose algorithm we believe is new and efficient and whosecore consists of: (1) we establish the swept wing mesh deformation algorithm and the flow field internal mesh de-formation algorithm respectively, thus developing our new dynamic unstructured grid method; (2) we use the finitevolume method to solve the 3-D Navier-Stokes equations and apply our new dynamic unstructured grid method to thenumerical analysis of the flow field of a certain missile with morphing swept wings. The simulation results, given inFigs 5 through 10, and their analysis show preliminarily that: (1) our new method can greatly improve the grid de-formation ability and the quality of the grids; (2) our new method takes into consideration the non-rigid deforma-tion caused by the effects of the missile body on the motion of the swept wings; (3) it is an effective and simplemethod for solving a complex unsteady flow field that contains complex motion boundary and large-scale mesh de-formation. |
| Key words:
computational efficiency
computational geometry
deformation
finite volume method
flow fields
mesh generation
missiles
models
Navier-Stokes equations
swept wings
unsteady flow
three di-mensional;computational fluid dynamics
dynamic unstructured grid
mesh deformation
springshape changing
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| 收稿日期: 2011-06-12
修回日期:
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| DOI: |
| 基金项目: 航天支撑基金(N11XW001)；西北工业大学基础研究基金(JC201024)资助 |
| 通讯作者:
Email： |
| 作者简介: 周敏(1987-),女,西北工业大学博士研究生,主要从事飞行器总体优化与控制研究。
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| 相关功能 |
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| 作者相关文章 |
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| 周敏 在本刊中的所有文章 |
| 周军 在本刊中的所有文章 |
| 林鹏 在本刊中的所有文章 |
| 郭建国 在本刊中的所有文章 |
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参考文献: |
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[1] Bowman J, Sanders B, Weisshaar T. Evaluating the Im-pact of Morphing Technologies on Aircraft Performance．AIAA-2002-1631
[2] Martin E T, Crossley W. Multiobjective Aircraft Designto Investigate Potential Geometric Morphing Features．AIAA-2002-5859
[3] Pascal de Marmier and Norman M Wereley. MorphingWings of a Small Scale UAV Using Inflatable Actuatorsfor Sweep Control. AIAA-2003-1802
[4] Neal D A, Good M G. Design and Wind-Tunnel Analysisof a Fully Adaptive Aircraft Configuration. AIAA-2004-1727
[5] 张天翼, 郭建国, 周 军. 变弹翼导弹动力学控制及仿真. 计算机仿真, 2011, 28(2):39-42Zhang Tianyi, Guo Jianguo, Zhou Jun. Dynamics andControl of Missile with Morphing Wings. Computer Simu-lation, 2011, 28(2): 39-42 (in Chinese)
[6] 邹运佳, 白俊强, 王军利. 非结构动网格在变后掠翼气动问题中的应用. 科学技术与工程, 2008, 8 (5):1368-1373Zou Yunjia, Bai Junqiang, Wang Junli. Dynamic Un-structured Grids Method with Applications to UnsteadyFlows Involving Wings Sweeping Back. Science Technolo-gy and Engineering, 2008, 8(5): 1368-1373 (in Chinese)
[7] 伍贻兆, 田书玲, 夏 健. 基于非结构动网格的非定常流数值模拟方法. 航空学报, 2011, 32(1):15-26Wu Yizhao, Tian Shuling, Xia Jian. Unstructured Grid Method for Unsteady Flow Simulation. Acta Aeronautica et AstronauticaSinca, 2011, 32(1):15-26 (in Chinese) |
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