基于加权正则化的火箭发动机振动传递路径分析  

Vibration transfer path analysis of rocket engine based on weighted regularization

作　　者：路广霖 罗亚军[1] 张希农[1] 李录贤[1] 马驰骋[2] LU Guanglin;LUO Yajun;ZHANG Xinong;LI Luxian;MA Chicheng(State Key Lab for Mechanical Structural Strength and Vibration, School of Aerospace, Xi’an Jiaotong University, Xi’an 710049, China;Department of Mechanics, Shandong University of Technology, Zibo 255000, China)

机构地区：[1]西安交通大学航天航空学院机械结构强度与振动国家重点实验室,西安710049 [2]山东理工大学力学部,山东淄博255000

出　　处：《振动与冲击》2019年第9期271-276,共6页Journal of Vibration and Shock

基　　金：机械结构强度与振动国家重点实验室开放课题(SV2016-KF-07)

摘　　要：为了给火箭发动机振动控制提供依据,需要对受到多源激励的发动机进行振动传递路径分析,其主要包括载荷识别和贡献量分析两个环节。为了准确识别发动机多源激励载荷并提供可靠的振动贡献量分析结果,提出一种基于加权正则化的改进传递路径分析技术。首先,推导出了载荷识别相对误差上界,并利用加权矩阵和贝叶斯理论提高载荷识别精度,并基于此提出改进的传递路径分析理论。然后,进行某发动机地面振动试验。最后,根据所提的加权正则化载荷识别理论和参考点响应数据识别了多源激励,并计算分析了不同振源在目标点的振动贡献量。分析结果表明,相较于传统传递路径分析技术,所提方法能更准确地识别多源激励,提供更可靠的振动贡献量分析结果。To provide a basis for vibration control of a rocket engine under multi-source excitations, it is necessary to do vibration transfer path analysis (TPA), the analysis mainly consists of load identification and vibration contribution analysis. Here, to correctly identify the engine’s multi-source excitations and provide reliable analysis results of vibration contribution, an improved TPA technique based on weighted regularization was proposed. Firstly, the upper bound of load identification’s relative error was derived, and the weighted matrix and Bayesian theory were adopted to improve the accuracy of load recognition, and then the improved TPA theory was proposed. Secondly, ground vibration tests of a certain rocket engine were conducted. Finally, using response data at reference points and the proposed load identification theory based on weighted regularization, multi-source excitations were identified and different source excitations’ contributions to target points’ vibration were calculated and analyzed. The results showed that compared with the traditional TPA technique, the proposed TPA technique can be used to more correctly identify multi-source excitations and provide more reliable vibration contribution analysis results.

关 键 词：多源载荷识别 传递路径分析 火箭发动机 

分 类 号：V434.3[航空宇航科学与技术—航空宇航推进理论与工程]