摘要
基于一类新型飞行器特有的几何外形结构,详细分析了其侧滑飞行可以等效为无侧滑飞行这一性质,根据这个性质,建立一个该飞行器的气动数据模型,这样此飞行器的侧滑飞行空气动力学系数就可以由无侧滑飞行的空气动力学系数折算得到,而飞行器的空气动力学系数通常是通过风洞实验得到的,由此可以节省风洞实验及费用。详细推导给出了侧滑飞行的空气动力学系数由无侧滑飞行的空气动力学系数得来的计算公式,最后的仿真研究验证了模型的正确性。
A particular characteristic that was equivalent non-sideslip flight of a class of new air vehicles was analyzed on the basis of the vehicle＇s particular geometric shape. According to this characteristic, a mathematical model of the aerodynamic data was built. The aerodynamic coefficients of non-sideslip flight of the vehicle could be converted into that of sideslip flight by using the model, which might reduce considerable expenses of wind tunnel experimentation that was always conducted to get the aerodynamic coefficients of air vehicles. The mathematical formulas of converting the aerodynamic coefficients of non-sideslip flight into that of sideslip flight were deduced and simulation study demonstrated the validity of the model.
出处
《系统仿真学报》
EI
CAS
CSCD
北大核心
2007年第16期3860-3863,共4页
Journal of System Simulation
基金
总装备部武器设备预研重点基金项目(6140511)
关键词
空气动力学系数
碟型飞行器
等效
侧滑
模型
aerodynamic coefficient
saucer-like air vehicle
equivalent
sideslip
model
