摘要
为研究高速飞行中飞行器仪器舱段结构的振动问题,在某跨音速风洞中对缩比模型进行了实验。实验中采用弹性薄壁结构模型,考虑了结构弹性变形与气动力的耦合作用。通过应变片传感器及信号处理仪器获得了从0.2至1.05之间13个实验马赫数下结构关键部位的振动响应数据。通过计算获得了测量信号的功率谱密度分布、结构上信号能量的分布以及信号能量随实验马赫数的变化情况,定性分析了结构的动态响应特性。分析结果表明：各测点处的振动信号功率谱密度主要峰值出现于高频段2 000~2 100 Hz内,结构的动态响应并非通常的低阶模态响应;虽然仪器舱段具有一定的迎风角度,但该段的弹性振动能量并非最大;在跨音速过程中,随着实验马赫数的增加,结构各测点处的振动信号能量将会出现突变。
Wind-tunnel experiment was carried out for the study of aircraft structural dynamic characteristics.Elastic thin-shell structure model was applied in this experiment in order to calculate the effect of structural elastic deformation in fluid-structure interaction.Through strain gauges and signal processing device,experimental data for structural key part were obtained under 13 different mach numbers which change from 0.2 to 1.05.Distributions of signal power spectrum density（PSD）,distributions of vibration signal energy on structure,and the energy change with mach number were respectively studied.Results show： the main values of PSD all occur in the high frequency domain which ranges from 2 000 Hz to 2 100 Hz,and frequencies in this domain are not the structural low-order natural frequencies;the maximum signal energy for measuring-point doesn＇t arise in apparatus-cabin section although it is a windward section;signal energies for measuring-points will abruptly change with the increase of mach number during the transonic course.
出处
《武汉理工大学学报》
CAS
CSCD
北大核心
2010年第9期153-156,共4页
Journal of Wuhan University of Technology
关键词
飞行器
弹性薄壁结构
流固耦合
风洞实验
aircraft
elastic thin-shell structure
fluid-structure interaction
wind-tunnel experiment
