| 根据风洞试验结果建立有尾翼导弹数学模型 |
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| 引用本文： | 何开锋,王文正,钱炜祺.根据风洞试验结果建立有尾翼导弹数学模型[J].实验流体力学,2004,18(4):62-66. |
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| 作者姓名： | 何开锋 王文正 钱炜祺 |
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| 作者单位： | 1. 西北工业大学航空学院,陕西,西安,710072;中国空气动力研究与发展中心,四川,绵阳,621000
2. 中国空气动力研究与发展中心,四川,绵阳,621000 |
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| 基金项目： | 空气动力学预先研究项目基金(413130501) |
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| 摘 要： | 通过分析有尾翼导弹气动力的对称特性,建立了有尾翼导弹空气动力系数的三角级数模型,给出了模型结构确定方法,并对某导弹风洞试验数据进行了建模研究,建模结果验证了所建模型的有效性和可行性。该套方法可以减少风洞试验量、帮助总结气动力规律、校正风洞试验的误差,并能为控制规律设计和性能分析提供方便。
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| 关 键 词： | 风洞试验 对称特性 气动力建模 |
| 文章编号： | 1007-3124(2004)04-0062-05 |
| 修稿时间： | 2004年1月7日 |
Mathematic modeling for the missile aerodynamics with tail- wing according to wind-tunnel test results |
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| HE Kai-feng.Mathematic modeling for the missile aerodynamics with tail- wing according to wind-tunnel test results[J].Experiments and Measur in Fluid Mechanics,2004,18(4):62-66. |
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| Authors: | HE Kai-feng |
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| Institution: | HE Kai-feng~ |
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| Abstract: | Triangle series model of aerodynamic coefficient of missile with tail-wing is established by analyzing symmetry characteristic of missile with tail-wing. The corresponding model structure determination methods are also presented. Modeling research has been carried out on wind tunnel test data of a certain kind missile. The modeling results show that the constructed models are feasible and very effective. The given method can help to reduce wind tunnel test times, help to summarize aerodynamic force law, help to correct the wind tunnel test error, and it can also be used conveniently for control law design and performance analysis. |
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| Keywords: | wind tunnel test symmetry characteristic aerodynamic modeling |
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