Research on fall-evaluation method of towed decoy missile
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摘要: 针对某掠海飞行器拖曳式诱饵弹1:1试验模型，通过风洞拖曳试验与测力试验展开真实飞行条件下的落差评估方法研究。首先，通过风洞拖曳试验对不同构型诱饵弹的拖曳状态及落差进行分析研究，结果表明：诱饵弹头部外形和质心位置对其拖曳状态的稳定性影响较大，其静稳定性受拖曳线拉力和气动力共同作用，而非质心越靠前静稳定性越高。其次，通过对稳定拖曳状态下的诱饵弹的受力分析发现，利用风洞测力试验能获得诱饵弹随迎角变化的气动力与力矩系数，进而采用函数拟合方法推导出诱饵弹稳定拖曳状态下的落差，并将其与风洞拖曳试验结果对比，从而验证该方法的可行性。最后，分析了两种试验的特性及优缺点，给出了工程实践中拖曳式诱饵弹的优化设计与落差评估方法。Abstract: The wind tunnel towed test and force test were performed with the full scale model of the towed decoy missile to research the towed flight fall under real conditions. Firstly, the wind tunnel towed test was carried out on decoy missile models of different configurations, and it turns out that the head shape and the center of mass have a great influence on the final towed attitude. In addition, the static stability does not always increase with a forward movement of the center of mass by the combined effect of the strain of tether and the aerodynamic force. Then, by analyzing the stress of the decoy missile in stabilization, a new idea is recommended for the fall evaluation based on the wind tunnel force test, which can derive the fall formulas using the aerodynamic data gathered from the force test. Its feasibility is comfirmed by comparing with the towed test. Lastly, by deeply study the advantages and disadvantages of the two tests above, a detailed application method on the optimal design and fall evaluation of the towed decoy missile is proposed for engineering practice.
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Key words:
- towed decoy missile /
- wind tunnel towed test /
- force test /
- fall-evaluation /
- optimal design
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表 1 平头构型拖曳姿态信息
Table 1. Towed attitude of flat head configuration
质心位置 拖曳状态 摆动下边界 摆动上边界 α/(°) φ/ (°) α/ (°) φ/ (°) 30.3% 不稳定 —— —— —— —— 32.3% 稳定 1.99 6.41 1.20 6.71 34.3% 稳定 2.09 6.38 1.74 7.82 
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表 2 拖曳姿态计算结果
Table 2. Computed results of towed attitude
质心位置 α/(°) φ/(°) 32.3% 1.96 7.71 34.3% 2.24 7.08
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