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。
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.
出处
《实验流体力学》
CAS
CSCD
北大核心
2004年第4期62-66,共5页
Journal of Experiments in Fluid Mechanics
基金
空气动力学预先研究项目基金(413130501)
关键词
风洞试验
对称特性
气动力建模
wind tunnel test
symmetry characteristic
aerodynamic modeling