含低速冲击损伤复合材料层板剩余强度及疲劳性能研究
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摘要
复合材料层合板由于其比强度、比刚度高，可设计性强，在南南、南南领域已得到的广泛的应用。然而层合板对低速冲击十分敏感，低能量物体的冲击往往在层板内部造成诸如纤维断裂，基体开裂，层间分层等损伤，这些损伤严重影响了结构的承载能力和安全使用寿命。现有的基于“静力覆盖疲劳”的复合材料结构设计思想将复合材料的许用应变值限制在一个较低的水平上，降低了复合材料结构的减重效果。为了提高复合材料的应用水平和效率，需要开展对复合材料低速冲击损伤和冲击后剩余强度、疲劳性能的研究。本文围绕这点，开展的主要研究内容包括：
（1）针对某典型铺层T300/QY8911复合材料层板开展了8种能量的低速冲击和冲击后压缩试验研究，获得了冲击后层板的损伤规律，讨论了冲击能量和冲击损伤特性及剩余压缩强度之间的关系；分析了含低速冲击损伤层板在压缩载荷下的破坏机理，研究表明：低速冲击造成的损伤对该类层板的剩余压缩强度影响很南，在仅3.75J/mm的冲击能量下，层板剩余压缩强度就下降了65%。含冲击损伤层板的压缩破坏模式与含孔层板类似，孔（损伤区）周围纤维屈曲是主要的失效模式。
（2）选取了受13.75J能量冲击后的层板进行冲击后压-压疲劳试验研究。详细测量了疲劳加载过程中试件内部的损伤扩展情况，获得了损伤扩展规律。研究发现：含冲击损伤层板压-压疲劳载荷下的损伤扩展过程可分为平稳期和扩展期两个阶段，平稳期约占整个疲劳寿命的前60%，该阶段内损伤扩展较缓慢；而疲劳寿命的后半阶段为扩展期，损伤开始加速扩展，在临近材料破坏时，还会出现明显的整体刚度下降。
（3）建立了用于预测复合材料层合板在低速冲击作用下损伤演化的有限元分析模型，有限元模型中包含了用于模拟分层损伤的界面单元和用于模拟纤维断裂，纤维挤压，基体开裂，基体挤裂等面内损伤形式的三维实体单元，模型中考虑了面内基体损伤对层间强度的影响。模型使用ABAQUS/Explicit模块和用户材料子程序VUMAT来实现，讨论了主要损伤模式的产生机理和影响低速冲击后层板内部分层面积的主要因素。
（4）通过损伤导入模块，将冲击损伤模型分析得到的各类损伤导入到压缩破坏模型中，建立了预测含冲击损伤层板在压缩载荷作用下损伤演化和剩余强度的有限元分析方法，实现了从冲击到冲击后压缩的全程分析。
（5）将冲击损伤等效为一圆形开孔，应用含椭圆形夹杂的杂交应力单元分析含圆孔有限南板的应力分布，采用特征曲线和点应力判据相结合的方式并通过引入损伤扩展规律建立了含低速冲击损伤复合材料层板剩余强度和压-压疲劳寿命预报模型。并详细讨论了相关参数对剩余强度和疲劳寿命的影响。
Composite laminates have been widely applied to the aeronautics and astronautics industrybecause of their high specific strength, high specific stiffness and advantages of designability.However, laminates are susceptible to low-velocity impact which can lead to significant damageincluding matrix cracks, fiber fractures and internal delaminations etc. The internal damage canconsiderably reduce the residual strength and safely service life of composite structures. Theallowable strain of composite laminates was restricted to a low level according to traditional designphilosophy of composite structures based on the concept of “static covering fatigue”, which partlyoffset the advantages of composite laminates. To enhance the application level of composites, researchon the residual strength and fatigue performance of composite laminates after low-velocity impactshould be carried out. On this thesis, the main contents are as follow:
(1) Impact damage and residual compressive strength after impact tests of T300/QY8911laminates were conducted with eight impact energy levels. The damage characteristic of impactedlaminates was obtained. The relationship between damage area, compressive strength after impact andimpact energy was discussed and the dominant damage mechanism of damaged composites undercompressive loads was also analyzed. The results show that low velocity impact damage has a greateffect on compressive strength; residual compressive strength was reduced by65%when thelaminates were impacted with energy level of3.75J/mm. The damage mechanism of impactedlaminates under compressive load is similar to notched laminates and fiber bending around the hole(or damage region) is the main failure mode.
(2) Compress-compress fatigue test of T300/QY8911laminates after13.75J impact was carriedout. Damage propagation in compression-compression fatigue test was measured in detail and thedamage propagation law was obtained. It shows the damage propagation under fatigue load can bedivided into two stages: during the initial60%of fatigue life, damage grows slowly; during the rest offatigue life, damage experiences an accelerated propagation; and the stiffness of laminate willdramatically decline at the stage near final failure.
(3) A finite element model was established for predicting the damage evolution of compositelaminates under transverse low-velocity impact. The model included cohesive elements whichallowed simulating delaminations between layers and three-dimensional solid elements which couldmodel fiber tensile failure, fiber compress failure, matrix crushing, and matrix cracking etc. inside layers. This model also considered the effects of in-plane damage on interlaminar strength. Model wasexecuted by ABAQUS/Explicit module with material subroutine VUMAT, the mechanism of damageand the main factor of delaminations under low-velocity impact were also discussed.
(4) The damage data gathered by the impact model above was imported to a compressive finiteelement model using an import process and a finite element analytic method was established topredict residual compressive strength and damage evolution of composite laminates after low-velocityimpact. It is achieved to simulate the whole process from initial low-velocity impact damage to finalcompressive failure of composite laminates.
(5) The impact damage was considered as a circle hole, and a special finite element including anelliptic inclusion was applied to analyze the stress distribution. Base on the damage propagation rule,characteristic length and point stress criterion were used for predicting the residual strength and thecompression-compression fatigue life of post-impacted laminate. The effects of some parameters onresidual strength and fatigue life were discussed.
（1）针对某典型铺层T300/QY8911复合材料层板开展了8种能量的低速冲击和冲击后压缩试验研究，获得了冲击后层板的损伤规律，讨论了冲击能量和冲击损伤特性及剩余压缩强度之间的关系；分析了含低速冲击损伤层板在压缩载荷下的破坏机理，研究表明：低速冲击造成的损伤对该类层板的剩余压缩强度影响很南，在仅3.75J/mm的冲击能量下，层板剩余压缩强度就下降了65%。含冲击损伤层板的压缩破坏模式与含孔层板类似，孔（损伤区）周围纤维屈曲是主要的失效模式。
（2）选取了受13.75J能量冲击后的层板进行冲击后压-压疲劳试验研究。详细测量了疲劳加载过程中试件内部的损伤扩展情况，获得了损伤扩展规律。研究发现：含冲击损伤层板压-压疲劳载荷下的损伤扩展过程可分为平稳期和扩展期两个阶段，平稳期约占整个疲劳寿命的前60%，该阶段内损伤扩展较缓慢；而疲劳寿命的后半阶段为扩展期，损伤开始加速扩展，在临近材料破坏时，还会出现明显的整体刚度下降。
（3）建立了用于预测复合材料层合板在低速冲击作用下损伤演化的有限元分析模型，有限元模型中包含了用于模拟分层损伤的界面单元和用于模拟纤维断裂，纤维挤压，基体开裂，基体挤裂等面内损伤形式的三维实体单元，模型中考虑了面内基体损伤对层间强度的影响。模型使用ABAQUS/Explicit模块和用户材料子程序VUMAT来实现，讨论了主要损伤模式的产生机理和影响低速冲击后层板内部分层面积的主要因素。
（4）通过损伤导入模块，将冲击损伤模型分析得到的各类损伤导入到压缩破坏模型中，建立了预测含冲击损伤层板在压缩载荷作用下损伤演化和剩余强度的有限元分析方法，实现了从冲击到冲击后压缩的全程分析。
（5）将冲击损伤等效为一圆形开孔，应用含椭圆形夹杂的杂交应力单元分析含圆孔有限南板的应力分布，采用特征曲线和点应力判据相结合的方式并通过引入损伤扩展规律建立了含低速冲击损伤复合材料层板剩余强度和压-压疲劳寿命预报模型。并详细讨论了相关参数对剩余强度和疲劳寿命的影响。
Composite laminates have been widely applied to the aeronautics and astronautics industrybecause of their high specific strength, high specific stiffness and advantages of designability.However, laminates are susceptible to low-velocity impact which can lead to significant damageincluding matrix cracks, fiber fractures and internal delaminations etc. The internal damage canconsiderably reduce the residual strength and safely service life of composite structures. Theallowable strain of composite laminates was restricted to a low level according to traditional designphilosophy of composite structures based on the concept of “static covering fatigue”, which partlyoffset the advantages of composite laminates. To enhance the application level of composites, researchon the residual strength and fatigue performance of composite laminates after low-velocity impactshould be carried out. On this thesis, the main contents are as follow:
(1) Impact damage and residual compressive strength after impact tests of T300/QY8911laminates were conducted with eight impact energy levels. The damage characteristic of impactedlaminates was obtained. The relationship between damage area, compressive strength after impact andimpact energy was discussed and the dominant damage mechanism of damaged composites undercompressive loads was also analyzed. The results show that low velocity impact damage has a greateffect on compressive strength; residual compressive strength was reduced by65%when thelaminates were impacted with energy level of3.75J/mm. The damage mechanism of impactedlaminates under compressive load is similar to notched laminates and fiber bending around the hole(or damage region) is the main failure mode.
(2) Compress-compress fatigue test of T300/QY8911laminates after13.75J impact was carriedout. Damage propagation in compression-compression fatigue test was measured in detail and thedamage propagation law was obtained. It shows the damage propagation under fatigue load can bedivided into two stages: during the initial60%of fatigue life, damage grows slowly; during the rest offatigue life, damage experiences an accelerated propagation; and the stiffness of laminate willdramatically decline at the stage near final failure.
(3) A finite element model was established for predicting the damage evolution of compositelaminates under transverse low-velocity impact. The model included cohesive elements whichallowed simulating delaminations between layers and three-dimensional solid elements which couldmodel fiber tensile failure, fiber compress failure, matrix crushing, and matrix cracking etc. inside layers. This model also considered the effects of in-plane damage on interlaminar strength. Model wasexecuted by ABAQUS/Explicit module with material subroutine VUMAT, the mechanism of damageand the main factor of delaminations under low-velocity impact were also discussed.
(4) The damage data gathered by the impact model above was imported to a compressive finiteelement model using an import process and a finite element analytic method was established topredict residual compressive strength and damage evolution of composite laminates after low-velocityimpact. It is achieved to simulate the whole process from initial low-velocity impact damage to finalcompressive failure of composite laminates.
(5) The impact damage was considered as a circle hole, and a special finite element including anelliptic inclusion was applied to analyze the stress distribution. Base on the damage propagation rule,characteristic length and point stress criterion were used for predicting the residual strength and thecompression-compression fatigue life of post-impacted laminate. The effects of some parameters onresidual strength and fatigue life were discussed.
引文
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