摘要
为研究基于鸭舵执行机构的简易制导火箭弹的控制规律,在以某制式火箭弹风洞实验值验证所建模型正确的基础上,利用MATLAB对其气动特性进行工程计算,利用ANSYS进行数值计算,得到火箭弹的气动力系数。在标准气象条件下,原方案射程为10 107 m,增加鸭舵动作后,方案射程减少到10 019 m。伸缩式鸭舵气动特性对方案弹道的影响较大。
To research the control law of simple guided rockets with canard rudders,the aerodynamic coefficients of the rockets are obtained by the engineering calculation of aerodynamic characteristics using MATLAB and numerical calculation using ANSYS based on a wind tunnel experiment proving the correctness of the established model. Under standard atmosphere conditions,the original project range is 10 107 m,and the project range decreases to 10 019 m by using a canard rudder. The aero-dynamic characteristics of retractable canard rudders influence greatly on project trajectories.
出处
《南京理工大学学报》
EI
CAS
CSCD
北大核心
2014年第3期380-384,共5页
Journal of Nanjing University of Science and Technology
关键词
简易制导火箭弹
鸭舵
气动特性
弹道
风洞实验
气动力系数
标准气象条件
方案射程
伸缩式鸭舵
方案弹道
simple guided rockets
canard rudders
aerodynamic characteristics
trajectories
tunnel experiments
aerodynamic coefficients
standard atmosphere conditions
project ranges
retractable canard rudders
project trajectories