本文關(guān)鍵詞：平紋編織復(fù)合材料層壓板低速沖擊損傷特性研究　出處：《南昌大學(xué)》2016年碩士論文　論文類型：學(xué)位論文

  更多相關(guān)文章： 平紋編織復(fù)合材料 低速沖擊損傷 ABAQUS數(shù)值模擬 剩余壓縮強(qiáng)度 吸濕

【摘要】：平紋編織復(fù)合材料由于其高比強(qiáng)度、面內(nèi)性能好等優(yōu)點(diǎn),在航空、航天、機(jī)械及軍工領(lǐng)域得到了廣泛應(yīng)用。但和傳統(tǒng)復(fù)合材料一樣,在遭受低速沖擊后,其材料內(nèi)部會因為基體開裂、分層和纖維斷裂等原因?qū)е缕淠承┬阅艿南陆?影響結(jié)構(gòu)的承載力和安全使用壽命。本文對T700SC-12k-50C/#2510平紋編織復(fù)合材料層壓板的低速沖擊損傷問題開展了研究:通過低速沖擊試驗,研究三種典型鋪層層壓板的低速沖擊特性;采用ABAQUS有限元軟件對層壓板沖擊過程進(jìn)行模擬仿真,研究其損傷特點(diǎn);通過沖擊后壓縮試驗,研究了剩余強(qiáng)度與沖擊能量的關(guān)系及溫濕度環(huán)境的影響。(1)確定了三種典型鋪層層壓板的臨界沖擊能量,超過該能量時,正面會出現(xiàn)不同深度的凹坑和裂紋,背面則出現(xiàn)纖維斷裂。凹坑深度曲線會因纖維斷裂出現(xiàn)明顯的拐點(diǎn),三種層壓板由于厚度和鋪層的不同出現(xiàn)拐點(diǎn)時對應(yīng)的沖擊能量也不相同,發(fā)生拐點(diǎn)后,基體開裂嚴(yán)重。(2)引入Hashin面內(nèi)損傷判據(jù)和層間cohesive單元模擬了低速沖擊過程對層壓板內(nèi)部造成的損傷。建立了只考慮層壓板面內(nèi)損傷和同時考慮面內(nèi)、層間損傷的兩種模型,前者的纖維斷裂和基體開裂損傷通常發(fā)生在受沖擊的中心位置處沿板寬度?45?方向,在受損傷嚴(yán)重時會呈現(xiàn)“X”形;后者損傷區(qū)域會呈現(xiàn)類似雙葉、花生等形狀,分層損傷是由層壓板的沖擊背面開始并向著沖擊正面發(fā)展的,正面的分層損傷面積與背面相比較小,但損傷程度深。數(shù)值模擬的損傷面積與超聲C掃描得到的損傷投影面積結(jié)果基本吻合。(3)確定了沖擊能量與剩余強(qiáng)度的關(guān)系:沖擊能量越大,沖擊損傷越嚴(yán)重,剩余強(qiáng)度下降得越多,層壓板的承受壓縮載荷的能力越差。低速沖擊并不影響壓縮失效的模式,出現(xiàn)了分層擴(kuò)展、屈曲等損傷擴(kuò)展現(xiàn)象,最終發(fā)生剪切分層失效。但是其失效特征以及失效區(qū)域不同。(4)在同一沖擊能量作用下,吸濕后的試件由于脆性下降,比未吸濕的試件對沖擊作用更不敏感,但層壓板的剩余壓縮強(qiáng)度會明顯下降。
[Abstract]:Plain weave composites have been widely used in aviation, aerospace, mechanical and military fields because of their high specific strength and good in-plane properties. However, after being subjected to low velocity impact, the properties of the composites will decrease due to cracking, delamination and fiber breakage, which will affect the performance and safety life of the composite. The impact of the T700SC-12k-50C/#2510 plain weave composite laminates damage is studied by low velocity impact test, low impact characteristics of three typical paving laminates; using ABAQUS finite element software to simulate the impact process of laminate, study the damage characteristics; through the compression after impact test, the influence of residual strength and impact energy and the relationship between temperature and humidity environment. (1) the critical impact energy of three typical laminated laminates is determined. When the energy exceeds this energy, there will be different depths of pits and cracks, and fiber breakage will appear on the back side. The dent depth curve will have obvious inflection point due to fiber fracture. The impact energy of the three laminate plates is different when the inflection point occurs due to the thickness and ply difference. After the turning point, the matrix cracking is serious. (2) the damage criterion in the Hashin surface and the interlayer cohesive element are introduced to simulate the damage caused by the low velocity impact process to the laminates. Established only consider laminate in-plane damage and considering the in-plane and interlaminar damage of the two models, the fiber breakage and matrix cracking damage usually occurs in the width of the center position by the impact plate along the 45 direction??, in serious injury may occur when the "X" shape; the latter will damage area similarly, double peanut shape, delamination is the impact on the back of laminate and start toward the positive impact the development of delamination area and positive phase back is relatively small, but the damage degree of depth. The damage area of the numerical simulation is in agreement with the result of the damaged projection area obtained by the ultrasonic C scan. (3) the relationship between impact energy and residual strength is determined. The larger the impact energy is, the more serious the impact damage is, and the more the residual strength decreases, the worse the compressive capacity of the laminate will be. The low velocity impact does not affect the mode of the compression failure, and the damage expansion, such as delamination expansion, buckling, and so on appears, and the shear layering failure occurs eventually. But the failure characteristics and the failure area are different. (4) under the same impact energy, the fragility of specimens after moisture absorption is more insensitive to impact than UNWETTING specimens, but the residual compressive strength of laminates will decrease significantly.
【學(xué)位授予單位】：南昌大學(xué)
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2016
【分類號】：TB33

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