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基于不完整正弦基礎(chǔ)激勵響應(yīng)數(shù)據(jù)的模型修正方法

Model updating method based on imperfect sine vibration test response data

  • 摘要: 文章直接應(yīng)用航天器正弦振動試驗所獲取的結(jié)構(gòu)動力學(xué)特性響應(yīng)數(shù)據(jù)，開展了模型修正方法的研究。在試驗數(shù)據(jù)不完整時，需進(jìn)行模型縮聚。首先對比分析了Guyan縮聚和IRS縮聚方法的優(yōu)缺點和適用范圍；然后以縮聚后模型為基礎(chǔ)，推導(dǎo)了基于基礎(chǔ)激勵響應(yīng)數(shù)據(jù)的模型修正方法；最后以GARTEUR桁架結(jié)構(gòu)的不完整的基礎(chǔ)激勵試驗數(shù)據(jù)為基礎(chǔ)對歸一化的結(jié)構(gòu)參數(shù)進(jìn)行修正。結(jié)果表明：IRS縮聚模型修正后對模態(tài)頻率具有良好的復(fù)現(xiàn)能力和預(yù)示能力，對響應(yīng)曲線的修正也得到了明顯改善。

     

    Abstract: The spacecraft sine vibration test can be used to reveal multiform dynamic characteristics, so a model updating method based on the sine vibration response data is important. The model reduction is necessary in an incomplete test data process. Firstly, the Guyan reduction method and the IRS reduction method are compared to show their merit/defect and application range. Secondly, an updating method based on excitation response data is derived by using the reduced model. Lastly, the unitary non-updated parameters are updated based on the incomplete test data of the GARTEUR. The results show that the IRS reduced updated model performs good in calculating/predicting the modes in/outside the updating frequency range with favorable results of response updating.

     

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