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基于Measurement Studio的民机颤振试飞数据实时监控分析系统设计与研究

Design and Research of Real-time Monitoring and Analysis System for Civil Aircraft Flutter Data Based on Measurement Studio
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摘要 颤振试飞是风险极高、多学科交叉的复杂试飞科目,其实时监控及分析显得极为重要。以某型国产民机颤振试飞为背景,基于Measurement Studio平台,设计开发了颤振试飞数据实时监控分析系统。系统集成了半带宽法、快速傅里叶变换、小波转换等算法,实现了颤振数据的时频域分析、阻尼计算,并以文本格式在实时状态下记录了颤振数据,同时以多线程和DataBinding模型完成了分析结果的实时显示,为国产民机的安全试飞提供了技术保障。 Flutter flight test is highly risky,and it is a complex experiment with multidisciplinary crossover. Its real-time monitoring and analysis is extremely important. Based on the domestic civil aircraft flutter test,this paper designs and develops a real-time monitoring and analysis system using the Measurement Studio platform. The system integrates algorithms such as half-bandwidth method,fast Fourier transform and wavelet transform to realize timefrequency domain analysis and damping calculation of flutter data. In addition,the system records flutter data in real-time with text format. At the same time,the system completes the real-time display of the analysis results with multithreading and Data Binding model,which can provide technical support for the safe flight test of domestic civil aircraft.
作者 毛为 刘涛 陈家益 高祥 梁嘉弈 MAO Wei;LIU Tao;CHEN Jiayi;GAO Xiang;LIANG Jiayi(COMAC Flight Test Center,Shanghai 201323,China)
出处 《民用飞机设计与研究》 2019年第2期11-15,共5页 Civil Aircraft Design & Research
基金 大型民机试飞数据高速实时处理及异常状态检测分析平台(17511105000)
关键词 颤振 MEASUREMENT STUDIO 实时分析 DataBinding flutter Measurement Studio real-time analysis DataBinding
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  • 1Richardson M H, Formenti D L. Parameter estimation from frequency response measurements using the rational fraction polynomial method [ A]. Proceedings of the 1^5t International Modal Analysis Conference [C]. IMAC, Florida: Union College, 1982: 167-180.
  • 2Richardson M H, Formenti D L. Parameter estimation from frequency response measurements using rational fraction polynomials (twenty years of progress) [A]. Proceedings of 20^th International Modal Analysis Conference [C]. IMAC, Los Angeles: Society for Experimental Mechanics, 2002. 373 -382.
  • 3Carcaterra A, Sestieri A. A bias in modal parameters using the direct and iterative RFP identification procedures [ J ].Meccanica, 1995, 30(1) : 77- 92.
  • 4Carcaterra A, D' Ambrogio W. Iterative rational fraction polynomial technique for modal identification [ J ]. Meccanica, 1995,30(1): 63-75.
  • 5Liu G L. Higher precision curve fitting to obtain modal parameters[ A]. Proceedings of the 18^th International Modal Analysis Conference[C]. IMAC, Las Vegas, Society for Experimental Mechanics, 1999. 1923 - 1929.
  • 6Simpson A. On flexure-torsion flutter criteria[J]. Aeronautical Journal, 1999, 103(1028) : 457 - 474.
  • 7Pappa R S, Ibrahim S R. A Parametric study of the Ibrahim Time Doamin Modal Identification Algorithm [ J ]. Shock & Vibration Bulletin, 1980,51 (3) : 2 - 8.
  • 8Ibrahim S R, Pappa R S. Large modal survey testing using the ibrahim time domain (ITD) identification technique[ J ].AIAA, 1981,22(2) : 12 - 20.
  • 9管德.飞机气动弹性力学手册[M]{H}北京:航空工业出版社,1994.
  • 10霍幸莉,田福礼,裴承鸣.环境激励下运输类飞机颤振试飞技术研究[J].强度与环境,2011,38(1):22-25. 被引量:7

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