以多层复合材料结构为研究对象，按照国军标GJB150.17A—2009规定的噪声载荷谱，完成了总声压级168 dB的宽带噪声随机响应分析，获得了应力较大位置处的频率响应曲线，并根据宽带随机响应分析结果，选取两个不同宽度的窄带频段分别完成了随机响应分析和疲劳寿命分析。结果表明：在声压谱级相同的情况下，宽带加载时结构的主要模态/响应与窄带加载时基本相同，但窄带加载下的结构疲劳寿命长于宽带加载，宽带加载下单位时间内的峰值数大于窄带加载；当窄带加载时的声压谱级提高0.5 dB，计算得到的寿命与宽带加载时基本相同。利用行波管对多层复合材料结构完成了宽带、窄带响应特性试验和疲劳寿命研究，结果表明：根据宽带响应结果选取合适的加载带宽，窄带加载能够代替宽带加载。
关键词：
高量级; 噪声; 等效加载; 宽带; 窄带
In light of multi-layer composite materials, random response analysis was achieved with the broadband noise of 168 dB according to GJB150.17A-2009, and frequency response curves were obtained at the position of maximum stress. Based on the analysis results with the broadband noise, two narrowbands were chosen for random response analyses and fatigue life analyses. Experimental results show that fatigue life under the narrowband loading is longer, number of peaks per unit time under the broadband loading is more. When sound pressure spectrum level under narrowband loading increases 0.5 dB, fatigue life under the narrowband loading and the broadband loading is almost equal. Experiments were completed with broadband and narrowband noises at the assistance of traveling wave tubes. Experimental results show that narrowband loading is equivalent to that of the broadband with the selection of appropriate loading bandwidth according to the broadband response results.
[1] 冯志高, 关成启, 张红文. 高超声速飞行器概论[M]. 北京:北京理工大学出版社, 2016. FENG Z G, GUAN C Q, ZHANG H W. An introduction to hypersonic aircraft[M]. Beijing:Beijing Insititute of Technology Press, 2016(in Chinese).
[2] MOSES P L, RAUSCH V L, NGUYEN L T, et al. NASA hypersonic flight demonstrators-Overview, status, and future plans[J]. Acta Astronautica, 2004, 55(3-9):619-630.
[3] CAP J. A comparison of the response of a captive carried store to both reverberant and progressive wave acoustic excitation:SANP-95-1577C[R]. Washington, D.C.:Department of Defense, 1995.
[4] 艾邦成, 宋威, 董垒, 等. 内埋武器机弹分离相容性研究进展综述[J]. 航空学报, 2020, 41(10):023809. AI B C, SONG W, DONG L, et al. Review of aircraft-store separation compatibility of internal weapons[J]. Acta Aeronautica et Astronautica Sinica, 2020, 41(10):023809(in Chinese).
[5] SMALLWOOD. A method for predicting structural responses from lower level acoustic tests[J]. The Shock and Vibration Bulletin, 1970, 41:87-93.
[6] BOOTLE R. Acoustic facility developments to meet changing requirements[C]//Institute of Environmental Sciences, 37th Annual Technical Meeting, 1991.
[7] BERTIN J, CUMMINGS R. Fifty years of hypersonics:Where we've been, where we're going[J]. Progress in Aerospace Sciences, 2003, 39:511-536.
[8] LEE J. Energy-conserving Galerkin representation of clamped plates under a moderately large deflection[J]. Journal of Sound and Vibration, 2004, 275(3-5):649-664.
[9] 刘泽锋, 单雪利, 于田霖, 等. 行波管与混响室噪声试验等效转换方法研究[J]. 环境技术, 2021, 39(5):132-138. LIU Z F, SHAN X L, YU T L, et al. Research on the equivalent conversion method for progressive wave tube and reverberation chamber nosie test[J]. Environmental Technology, 2021, 39(5):132-138(in Chinese).
[10] SHIMOVETZ R M, WENTZ K R. High intensity acoustic testing of flight structures[C]//ICIASF'95 Record International Congress on Instrumentation in Aerospace Simulation Facilities, 1995:50/1-50/8.
[11] STEPHEN A R, TRAVIS L. Enhanced capabilities of the NASA Langley thermal acoustic fatigue apparatus[C]//Proceedings of the 6th International Conference on Recent Advances inStructural Dynamics, 1997:919-933.
[12] Improvements to progressive wave tube performance through closed-loop control:NASA/TM-2000-210623[R]. Washington, D.C.:NASA, 2000.
[13] 王琰, 郭定文. 航空发动机转子叶片的声振疲劳特性试验[J]. 航空动力学报, 2016, 31(11):2738-2743. WANG Y, GUO D W. Experiment on acoustic vibration fatigue properties of the aero-engine rotor blade[J]. Journal of Aerospace Power, 2016, 31(11):2738-2743(in Chinese).
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