机载飞行器挂机结构强度分析及试验方法
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摘要
挂机结构是机载飞行器的关键承载结构,采用两种方法对挂机结构进行强度分析。首先采用惯性释放方法,该方法可准确模拟挂飞边界条件但无法据此开展地面静力试验;因此又根据机载飞行器的结构特点提出了边界约束方法,通过对比两种方法的分析结果,找出既能满足分析精度要求又适合开展地面静力试验的边界条件;最后据此开展地面静力试验,进一步验证了挂机结构对挂飞载荷的适应性。
The suspension structure is the key bearing structure of airborne missiles. In this paper, two methods are used to analyze the strength of the suspension structure. First, the inertia release method is used. This method can accurately simulate the boundary conditions of the hang up flight but the ground static test can't be carried out accordingly. So the boundary constraint method is put forward according to the structural characteristics of airborne missile. By comparing the numerical results of these two methods, it is found out that the boundary conditions that can meet the analytical accuracy requirements and are suitable for carrying out ground static test. Finally, ground static test was carried out accordingly. Which further validates the adaptability of the suspension structure to the flying load.
The suspension structure is the key bearing structure of airborne missiles. In this paper, two methods are used to analyze the strength of the suspension structure. First, the inertia release method is used. This method can accurately simulate the boundary conditions of the hang up flight but the ground static test can't be carried out accordingly. So the boundary constraint method is put forward according to the structural characteristics of airborne missile. By comparing the numerical results of these two methods, it is found out that the boundary conditions that can meet the analytical accuracy requirements and are suitable for carrying out ground static test. Finally, ground static test was carried out accordingly. Which further validates the adaptability of the suspension structure to the flying load.
引文
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