| 引用本文: | 徐一航,陈少松,魏恺,邱佳伟.正、余弦指令控制方式旋转导弹气动特性分析[J].哈尔滨工业大学学报,2022,54(1):114.DOI:10.11918/202109059 |
| XU Yihang,CHEN Shaosong,WEI Kai,QIU Jiawei.Analysis of aerodynamic characteristics of a rotating missile with sine and cosine command control[J].Journal of Harbin Institute of Technology,2022,54(1):114.DOI:10.11918/202109059 |
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| 摘要: |
| 为了研究正、余弦控制式鸭舵对旋转导弹气动特性的影响,在CFD软件中采用嵌套网格方法模拟导弹的旋转和鸭舵的偏转。在与风洞试验结果进行对比,验证了数值模拟准确性基础之上,对不同转速、迎角、马赫数下正、余弦控制方式旋转导弹的气动特性进行数值模拟,得出如下结论:当采用相同最大舵偏角时,导弹进行正、余弦控制时其法向力系数要比静态条件下小,其侧向力系数和偏航力矩系数要比静态条件下大；导弹进行正、余弦控制时的偏航力矩系数大小要比不控时小；转速的变化对全弹法向力、侧向力特性以及鸭舵提供的法向力影响相对较小；亚声速条件下导弹的侧向力系数和偏航力矩系数数值比超声速条件下大；导弹做锥进运动时,合成迎角Г的变化对周期平均升力系数和侧向力系数影响较小,Г的变大会使周期平均偏航力系数、周期平均阻力系数数值变大；旋转效应是正、余弦控制方式旋转导弹产生侧向力的原因,并且鸭舵、尾翼产生的侧向力占主导地位。 |
| 关键词: 气动特性 数值模拟 鸭舵偏转 正、余弦控制 旋转导弹 风洞试验 |
| DOI：10.11918/202109059 |
| 分类号:Tj765.3 |
| 文献标识码:A |
| 基金项目: |
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| Analysis of aerodynamic characteristics of a rotating missile with sine and cosine command control |
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XU Yihang,CHEN Shaosong,WEI Kai,QIU Jiawei
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(School of Energy and Power Engineering, Nanjing University of Science and Technology, Nanjing 210094, China)
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| Abstract: |
| To study the influence of positive and cosine control canard on the aerodynamic characteristics of rotating missile, the nested grid method is used to simulate the missile rotation and the deflection of the canard in CFD software. Based on the comparison with the wind tunnel test results and the verification of the accuracy of numerical simulation, numerical simulation was carried out on the aerodynamic characteristics of the rotating missile with positive and cosine control modes at different speeds, angles of attack and Mach numbers, and the following conclusions were drawn: When the same maximum canard deflection angle is used, the normal force coefficient of the missile is smaller than that of the static condition, while the lateral force coefficient and lateral moment coefficient are larger than that of the static condition. The lateral moment coefficient of the missile under the control of sines and cosines is smaller than that under the control of no control. The variation of rotational speed has relatively little effect on the normal force, lateral force and the normal force provided by the canard. The lateral force coefficient and lateral moment coefficient of the missile under subsonic condition are larger than those under supersonic condition. During the coning motion of the missile, the changes of the synthetic angle of attack Г have little effect on the periodic average lift coefficient and the lateral force coefficient, and the greater the Г makes the periodic average yaw force coefficient increase. The rotation effect is the reason for the lateral force of the rotating missile with positive and cosine control mode, and the lateral force of the canard and tail is dominant. |
| Key words: aerodynamic characteristics numerical simulation rudder deflection sine and cosine command control rotating missile wind tunnel experiments |
