基于直升机耦合分析的振动响应预测研究

目的预测直升机振动响应。方法采用中等变形梁理论建立直升机旋翼桨叶结构有限元模型,以准定常气动力模型及Pitt动态入流理论模拟旋翼上的气动作用力,结合旋翼结构及气动模型形成旋翼动力学分析模型,并以旋翼动力学试验结果验证模型的正确性。基于Patran建立直升机机体动力学模型,根据旋翼动力学分析结果,筛选并提取机体模态信息。结果耦合旋翼动力学及机体动力学模型,形成直升机全机耦合动力学分析模型,采用时间有限元方法求解耦合模型,以此模型进行直升机机体振动响应预测及与试验对比分析研究。结论该方法机体振动响应计算值与试验值变化规律相同。

Vibration Response Prediction Based on Helicopter Coupling Analysis

The paper aims to predict the vibration response of helicopter. The moderate deflection beam theory was adopted to establish the finite element model of rotor blade. The quasi-steady aerodynamic model and Pitt dynamic inflow theory were used to simulate the aerodynamic force on the rotor wing. Combining the rotor structure and aerodynamic model, the dynamic analysis model of rotor wing was formed, and the correctness of the model was verified by the rotor wing dynamic tests. The helicopter fuselage dynamic model was established based on Patran. According to the results of rotor wing dynamic analysis, the model information of the fuselage was screened and extracted. Coupled rotor dynamics and fuselage dynamics formed the coupling dynamic analysis model of helicopter, which was resolved by time finite element method. The model is used to predict the vibration response of helicopter fuselage and to compare with experimental results. The results show that the vibration response calculated by this method is the same as the test.