Research on test technology of dynamic force measurement of rotating missile in wind tunnel
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摘要: 常规风洞静态气动力测量技术无法得到旋转导弹的非定常气动特性数据，需要研究在风洞中模拟旋转导弹运动特征以及对气动力实现动态测量的试验技术。在1.2 m量级超声速风洞中，研究了大长细比导弹模型旋转运动主动控制技术以及与旋转运动对应的动态测量试验技术。采用旋转导弹模型（长细比为20）对建立的试验技术进行了风洞试验验证。结果表明：采用微型驱动系统并对旋转组件与导弹模型进行一体化设计，可以对大长细比导弹模型转速进行稳定控制；建立的风洞动态测力试验技术可以对导弹模型旋转运动下的动态数据进行测量，试验数据重复性精度良好。Abstract: The missile encounters complex aerodynamic problems during the rotating flight. The rotary motion causes unsteady aerodynamic characteristics. The conventional static force measurement wind tunnel test cannot meet the requirements of the dynamic aerodynamic characteristics research, and the dynamic aerodynamics of missile model needs to be measured in the wind tunnel, the rotational motion of missile model performs similar simulations. In the 1.2 m-level supersonic wind tunnel, the active control technology of the rotary motion of the long slender missile model and the dynamic aerodynamic measurement technology corresponding to the rotary motion are studied. The established test technique was verified by the wind tunnel test using a rotating missile model with a slenderness ratio of 20. The experimental results show that the micro-drive system and the integrated design of the rotating component and the missile model can stably control the rotational speed of the missile model with large slenderness ratio. The established wind tunnel dynamic force test technology can obtain the dynamical data of the missile model in rotating motion, and the test data was reproducible with good precision.
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Key words:
- rotating missiles /
- wind tunnel test /
- unsteady aerodynamics /
- dynamic test technique /
- rotating motion
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图 5 中空五分量环式天平结构图和实物
Figure 5. Structural drawing and photo of hollow five-component ring balance
图 7 模型与天平系统固有频率测试结果
Figure 7. Natural frequency test results of the model and balance system
图 8 模型转速ω随迎角α变化的对比曲线
Figure 8. Contrast curves of model rotating speed with angle of attack
图 9 典型旋转导弹动态气动力试验结果
Figure 9. Dynamic aerodynamic test results of typical rotating missiles
图 10 周期平均处理后的试验结果重复性对比
Figure 10. Repeatability comparison of test results after cycle average treatment
图 11 周期平均处理后的模型不同转速下的试验数据对比
Figure 11. Comparison of data at different speeds after cyclic average processing
表 1 天平设计载荷
Table 1. Design load of balance
偏航力矩
Nb/(N·m)侧向力
C/N俯仰力矩
M/(N·m)法向力
N/N滚转力矩
L/(N·m)50 100 80 300 10 
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