固体火箭技术
固體火箭技術
고체화전기술
JOURNAL OF SOLID ROCKET TECHNOLOGY
2015年
4期
585-590
,共6页
杨涛%于湛卉%牛雪娟%杜宇
楊濤%于湛卉%牛雪娟%杜宇
양도%우담훼%우설연%두우
复合材料梁%层间损伤%模态柔度曲率改变率%试验研究
複閤材料樑%層間損傷%模態柔度麯率改變率%試驗研究
복합재료량%층간손상%모태유도곡솔개변솔%시험연구
composite beam%interlaminar damage%change ratio of modal flexibility curvature%experimental study
利用复合材料梁的模态柔度曲率改变率（MFCI）来探讨复合材料无损检测方法。采用锤击法测量计算出复合材料梁的前三阶固有频率和加速度幅值，并采用频谱转换法将加速度幅值转换成振型位移幅值，计算出复合材料梁的模态柔度曲率改变率（MFCI）值，进而检测出复合材料梁的损伤位置。以损伤的大小、位置、层为要素制作了4组不同工况的对比试件。实验结果表明，损伤单元 MFCI 的值5．2006明显高于各无损伤单元 MFCI 的平均值0．7205，并且它所对应的横坐标的值反映出损伤位置，发生突变单元的间距反映出损伤的大小；3个不同层上损伤 MFCI 的值分别为5．2006、5．9828、6．8830，可间接反映出损伤发生在不同的层间位置上。多损伤的情况下，损伤 MFCI 的平均值为1．192也能识别出损伤位置，但比单损伤 MFCI 的平均值5．294小很多，说明复合多损伤互相干扰，消弱了损伤识别的效率。通过实验证明了模态柔度曲率改变率法对判断复合材料梁的层间损伤有显著效果。
利用複閤材料樑的模態柔度麯率改變率（MFCI）來探討複閤材料無損檢測方法。採用錘擊法測量計算齣複閤材料樑的前三階固有頻率和加速度幅值，併採用頻譜轉換法將加速度幅值轉換成振型位移幅值，計算齣複閤材料樑的模態柔度麯率改變率（MFCI）值，進而檢測齣複閤材料樑的損傷位置。以損傷的大小、位置、層為要素製作瞭4組不同工況的對比試件。實驗結果錶明，損傷單元 MFCI 的值5．2006明顯高于各無損傷單元 MFCI 的平均值0．7205，併且它所對應的橫坐標的值反映齣損傷位置，髮生突變單元的間距反映齣損傷的大小；3箇不同層上損傷 MFCI 的值分彆為5．2006、5．9828、6．8830，可間接反映齣損傷髮生在不同的層間位置上。多損傷的情況下，損傷 MFCI 的平均值為1．192也能識彆齣損傷位置，但比單損傷 MFCI 的平均值5．294小很多，說明複閤多損傷互相榦擾，消弱瞭損傷識彆的效率。通過實驗證明瞭模態柔度麯率改變率法對判斷複閤材料樑的層間損傷有顯著效果。
이용복합재료량적모태유도곡솔개변솔（MFCI）래탐토복합재료무손검측방법。채용추격법측량계산출복합재료량적전삼계고유빈솔화가속도폭치，병채용빈보전환법장가속도폭치전환성진형위이폭치，계산출복합재료량적모태유도곡솔개변솔（MFCI）치，진이검측출복합재료량적손상위치。이손상적대소、위치、층위요소제작료4조불동공황적대비시건。실험결과표명，손상단원 MFCI 적치5．2006명현고우각무손상단원 MFCI 적평균치0．7205，병차타소대응적횡좌표적치반영출손상위치，발생돌변단원적간거반영출손상적대소；3개불동층상손상 MFCI 적치분별위5．2006、5．9828、6．8830，가간접반영출손상발생재불동적층간위치상。다손상적정황하，손상 MFCI 적평균치위1．192야능식별출손상위치，단비단손상 MFCI 적평균치5．294소흔다，설명복합다손상호상간우，소약료손상식별적효솔。통과실험증명료모태유도곡솔개변솔법대판단복합재료량적층간손상유현저효과。
In this paper,the change ratio of modal flexibility curvature MFCI of composite beam modal was used to discuss the NDT method of composite materials.Firstly, the first three natural frequencies and acceleration amplitudes of the composite beam were tested and calculated through hammering method.Then acceleration amplitude was exchanged to modal displacement amplitude with the method of spectrum conversion.The interlaminar damage of composite beam was detected by calculating the MFCI.The four groups of samples considering damage size,damage location and damage layers were designed and made.The experimental results show that the MFCI 5.200 6 of the damage unit is significantly higher than the average MFCI 0.720 5 of the Non?damage unit,the value of abscissa reflects the damage location and mutated spacing shows the size of damage;the MFCI of damage in three different layers are 5.200 6,5.982 8 and 6.883 0,which can indirectly reflect the damage occurred in different interlaminar position.In the multiple damage cases,the damage location can be indentified,but the average value of MFCI 1.192 is much smaller than 5.294 in the single damage case. Due to mutual interference,the multiple damage weakenes the efficiency of damage identification.The exper?imental results prove that the method of the change ratio of modal flexibility curvature has the significant effect on the judgment of composite beam interlaminar damage.
