基于最小二乘法的飞机发动机安装节动态力识别

韩峰; 沈承; 徐俊伟

doi:10.21656/1000-0887.410054

基于最小二乘法的飞机发动机安装节动态力识别

doi: 10.21656/1000-0887.410054

¹上海飞机设计研究院功能结构部, 上海 201210;²南京航空航天大学航空学院, 南京 210016

详细信息

作者简介:
韩峰(1983—)，男，高级工程师，硕士生(通讯作者. E-mail: hanfeng@comac.cc).

中图分类号: TB122;V228
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出版历程
- 收稿日期: 2020-02-19
- 修回日期: 2020-07-02
- 刊出日期: 2020-09-01

Identification of Dynamic Forces on Aircraft Engine Mounts With the Least Squares Method

¹Department of Functional Structures, Shanghai Aircraft Design and Research Institute, Shanghai 201210, P.R.China;²College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, P.R.China

摘要

摘要: 飞机舱内噪声与振动控制的一个关键技术是获取发动机安装节处的动态力，从而实现对发动机振动引发的机体结构振动和舱内噪声进行预测和控制.但对于飞机，在飞行状态下不可能对发动机安装节处的动态力进行直接测量.通过采用最小二乘法正则化逆运算，利用地面状态下发动机安装节至吊挂或发动机安装节至安装节上的结构频率响应函数，以及飞行状态下吊挂或发动机安装节上相同位置处的振动加速度响应，对发动机安装节上的动态力进行识别.通过对比逆运算过程中的矩阵条件数，判定两组动态力识别的相对准确度.通过对两组数据识别的动态力均方根值进行对比，确认通过最小二乘法识别的发动机安装节动态力满足工程使用要求.
- 动态力识别 /
- 最小二乘法 /
- 频率响应函数 /
- 发动机安装节
Abstract: For aircraft noise and vibration control, it is vitally important to identify dynamic forces on engine mounts caused by engine operation. Although such dynamic forces are needed to predict and control structural vibration and structure-borne noise in the cabin, they cannot be measured directly in the flight state. The least squares method was employed to identify the dynamic forces based on the frequency response function (FRF) between excitation points and response positions with the actual acceleration measurements in the flight state. A norm condition number criterion was used to evaluate the accuracy of the inverse calculation process, and relative errors of the predicted dynamic forces were calculated. The results show that, the identified forces meet engineering requirements.
- dynamic force identification /
- least squares method /
- FRF /
- engine mount

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参考文献(13)

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