本文選題：編織材料 + 層合結(jié)構(gòu)�。� 參考：《蘭州理工大學》2017年碩士論文

【摘要】：纖維編織復合材料是一種新型高溫結(jié)構(gòu)復合材料和功能材料,不僅具有極好的生物相容性、高比強度、高比剛度、優(yōu)異的抗燒蝕性能及高溫下良好的力學性能保持度等特點,而且具有抗沖擊損傷性能好、抗分層、垂直結(jié)構(gòu)方向強度高、開裂不敏感、損傷擴展慢的優(yōu)良品質(zhì),因而廣泛應(yīng)用于航空航天領(lǐng)域。針對大型異質(zhì)層合制件在制造過程中通常出現(xiàn)一定變形的問題,利用有限元仿真技術(shù),探索異質(zhì)層合變形的內(nèi)在原因,通過結(jié)構(gòu)和工藝等手段實現(xiàn)異質(zhì)層合材料變形的有效控制,提升大型異質(zhì)層合復合材料方向的工程技術(shù)水平。本研究在分析所用纖維編織復合材料微觀組織結(jié)構(gòu)特點的基礎(chǔ)上,從材料研究新視角出發(fā),以纖維增強樹脂基復合材料微觀組織結(jié)為研究對象,在碳纖維大小的尺度上,依據(jù)纖維編織結(jié)構(gòu)和樹脂基體各自的性質(zhì)、各自的幾何狀態(tài)與取向狀態(tài)來預測及設(shè)計纖維編織材料的性能與行為,確立了以“數(shù)字化、數(shù)值化、虛擬化、可視化”和“虛擬材料”技術(shù)手段為前提的“材料模型”建模思想,采用三維商用建模軟件CATIA完成了某飛機蒙皮CKFR-PMCs編織型層合結(jié)構(gòu)幾何模型的建立。在有限元分析階段,首先對大型整體異質(zhì)層合制件做模流分析,旨在研究制件注射過程中出現(xiàn)變形情況,再設(shè)計一種使得注件在注塑過程中不會產(chǎn)生翹曲變形的虛擬材料和虛擬工藝,比較兩次注射過程各物理量隨時間的演變。模流分析真實地再現(xiàn)了注射過程中塑料熔體(流變體)在模具型腔內(nèi)的流動;準確地預測了制件“注射-壓縮保持-冷卻”工藝流程中各個階段溫度、壓力等隨時間的演變。再對注塑過程狀態(tài)數(shù)值化,進一步將數(shù)值化的狀態(tài)傳輸?shù)接邢拊治鲕浖嗀BAQUS中進行工藝分析,再現(xiàn)注射成型整個過程中制件表面溫度與應(yīng)力變化,研究工藝參數(shù)對制件變形的影響,達到優(yōu)化工藝的目的,得到了異質(zhì)層合復合材料在溫度載荷作用下的應(yīng)力場、應(yīng)變場以及位移場的分布,實現(xiàn)了不同有限元分析軟件之間數(shù)據(jù)的交換和狀態(tài)的繼承,建立了“注射壓縮模塑成型仿真平臺”,在此仿真平臺上可以完成“模具預熱-注射成型-壓縮成型-冷卻固化”這一完整的工藝流程中各個環(huán)節(jié)技術(shù)指標參數(shù)與工藝參數(shù)的計算性優(yōu)化,對大尺寸、跨尺度的多元多相異質(zhì)復合材料的成型工藝及變形預測具有一定的指導作用。
[Abstract]:Fiber braided composite is a new type of high temperature structure composite and functional material. It not only has excellent biocompatibility, high specific strength, high specific stiffness, excellent ablation resistance and good mechanical performance retention at high temperature, etc. It is widely used in aeronautics and astronautics because of its good impact damage resistance, good delamination resistance, high vertical structural strength, insensitive cracking and slow damage expansion. In view of the problem of deformation in the manufacturing process of large heterogeneous laminates, the internal causes of the deformation of heterogeneous laminates are explored by using finite element simulation technology. By means of structure and technology, the deformation of heterogeneous laminates can be controlled effectively, and the engineering technology level in the direction of large heterogeneous laminated composites can be improved. Based on the analysis of the microstructure characteristics of the fiber braided composites, the microstructure of fiber reinforced resin matrix composites was studied from a new perspective of material research, and on the scale of carbon fiber size, According to the properties of fiber braiding structure and resin matrix and their geometric and orientation states, the properties and behaviors of fiber braiding materials are predicted and designed. Based on the idea of "material model" modeling based on visualization "and" virtual material "technology, the geometric model of a aircraft's CKFR-PMCs braided laminated structure is established by using the three-dimensional commercial modeling software CATIA. In the stage of finite element analysis, first of all, the mold flow analysis is done for the large integral heterogeneous laminated parts, in order to study the deformation in the injection process. A virtual material and a virtual process are designed to prevent the injection from warping in the injection molding process. The physical quantities of the two injection processes are compared with each other over time. The flow of plastic melt (rheological body) in the mold cavity during injection process is reproduced by mold flow analysis, and the evolution of temperature and pressure with time in each stage of the injection, compression, retention and cooling process is accurately predicted. Then the state of the injection molding process is digitized, and the numerical state is further transferred to the finite element analysis software ABAQUS for process analysis, and the change of surface temperature and stress during the whole process of injection molding is reproduced. The effect of process parameters on the deformation of the workpiece is studied, and the distribution of stress field, strain field and displacement field of heterogeneous laminated composites under temperature load is obtained. The data exchange and state inheritance between different finite element analysis software are realized, and the simulation platform of injection compression molding is established. On this simulation platform, the computational optimization of the technical parameters and process parameters of each link in the complete process of "Mould preheating, injection Molding, Compression Molding and cooling curing" can be completed. The forming process and deformation prediction of multi-phase heterogeneous composite materials with cross-scale are instructive.
【學位授予單位】：蘭州理工大學
【學位級別】：碩士
【學位授予年份】：2017
【分類號】：TB332

【參考文獻】

相關(guān)期刊論文 前10條

1 薛忠民;;中國玻璃鋼/復合材料發(fā)展回顧與展望[J];玻璃鋼/復合材料;2015年01期

2 李旭東;朱武峰;任懷輝;穆志韜;;碳-碳編織復合材料微結(jié)構(gòu)設(shè)計與力學性能預測[J];材料導報;2012年20期

3 吳海宏;馮蘭芳;暢同晨;蔡剛毅;成永峰;;精密注塑制品殘余應(yīng)力的試驗研究及其計算[J];機械工程學報;2012年02期

4 時慧焯;王希誠;;基于改進的BP神經(jīng)網(wǎng)絡(luò)的注塑成型翹曲優(yōu)化設(shè)計[J];化工學報;2011年09期

5 李陽;趙朋;李德群;嚴波;;三維塑料注射成形熱殘余應(yīng)力及收縮模擬[J];高分子材料科學與工程;2010年10期

6 李濤;左正興;廖日東;;結(jié)構(gòu)仿真高精度有限元網(wǎng)格劃分方法[J];機械工程學報;2009年06期

7 詹世革;孟慶國;方岱寧;;航空航天紡織結(jié)構(gòu)復合材料力學性能研究進展與展望[J];中國基礎(chǔ)科學;2008年02期

8 吳海宏;趙振峰;黃明;申長雨;;聚合物注塑內(nèi)應(yīng)力和翹曲變形的數(shù)值模擬[J];高分子材料科學與工程;2007年06期

9 顧正銘;;平流層飛艇蒙皮材料的研究[J];航天返回與遙感;2007年01期

10 馬文鎖;趙允嶺;馮偉;;三維編織復合材料理論研究進展[J];材料科學與工程學報;2006年04期

相關(guān)博士學位論文 前1條

1 孫顯俊;聚丙烯及其復合材料注塑件翹曲變形數(shù)值模擬與實驗研究[D];南京航空航天大學;2015年

相關(guān)碩士學位論文 前2條

1 謝林峰;基于ABAQUS對27SiMn無縫鋼管內(nèi)裂紋的研究[D];武漢科技大學;2013年

2 俞華英;薄壁塑件注塑成型的數(shù)值模擬和成型工藝參數(shù)優(yōu)化的研究[D];浙江工業(yè)大學;2008年

，

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