本文選題：三維六向編織復(fù)合材料　切入點：力學(xué)性能試驗　出處：《哈爾濱工業(yè)大學(xué)》2015年碩士論文　論文類型：學(xué)位論文

【摘要】：三維六向編織復(fù)合材料是在三維四向編織預(yù)成型體的基礎(chǔ)上,分別在縱向和橫向上添加不動紗而形成的一種整體結(jié)構(gòu)性能良好的編織結(jié)構(gòu),因其除了具有高比剛度、高比強(qiáng)度的優(yōu)點之外,在面外性能、剪切性能、結(jié)構(gòu)可設(shè)計性等方面表現(xiàn)優(yōu)異,故在航空航天領(lǐng)域應(yīng)用前景廣闊。但研究其力學(xué)行為的文獻(xiàn)報道較少,僅有的研究主要針對的是不同編織角、不同纖維體積分?jǐn)?shù)對材料拉伸或連接性能的影響,這是設(shè)計階段材料選型和使用過程中工藝要求所需要的,但作為一種典型的正交各向異性和拉壓雙模量復(fù)合材料,在設(shè)計和使用階段,還需重點考慮材料在不同工況下、不同方向上的力學(xué)性能差異,此外,針對材料剛度的預(yù)報,目前還缺乏與真實細(xì)觀結(jié)構(gòu)觀測結(jié)果的結(jié)合和考慮拉壓不同性能,而且借鑒于纖維增強(qiáng)層合板相關(guān)實驗標(biāo)準(zhǔn),對材料進(jìn)行性能測試,面臨實驗工作量大、周期長、效率低、費用高等困難,且在不同類型的實驗之間,由于試樣形狀不一和復(fù)合材料數(shù)據(jù)的離散性,在對數(shù)據(jù)進(jìn)行橫向比較方面存在一定難度,急需發(fā)展一種一次實驗測出多個力學(xué)性能參數(shù)的方法。因此,針對上述存在的不足和困難,本文主要進(jìn)行以下三個方面的研究。首先對小編織角、中等纖維體積含量的T300/TDE86三維六向編織復(fù)合材料進(jìn)行了不同工況下、不同方向上的力學(xué)性能試驗,包括:縱向拉伸、三個不同方向上的壓縮和面內(nèi)剪切性能試驗,獲得了相應(yīng)的強(qiáng)度和模量等數(shù)據(jù),以及破壞模式與損傷機(jī)制,并詳細(xì)橫向比較了它們之間的異同及原因。其次在四步法編織工藝的基礎(chǔ)上,對原始材料和燒去樹脂后的材料進(jìn)行了不同方位上不同紗線走向的觀測,確定了材料的細(xì)觀結(jié)構(gòu)形式和特征參數(shù),以及紗線之間的扭結(jié)、接觸情況,在一定假設(shè)條件的基礎(chǔ)上,考慮到材料宏觀實際尺寸,建立了厚度方向上的全尺寸幾何分析模型,采用已有文獻(xiàn)關(guān)于纖維束和基體的組分材料力學(xué)性能參數(shù),利用剛度組裝技術(shù)對幾何分析模型進(jìn)行了不同方向上的剛度預(yù)報,預(yù)報結(jié)果與實驗數(shù)據(jù)相比,除厚度方向壓縮性能和面內(nèi)剪切剛度誤差較大外,其余吻合均較好,說明了本章剛度預(yù)報方法的準(zhǔn)確性;最后聯(lián)合使用數(shù)字圖像相關(guān)技術(shù)(DIC)和有限元對三維六向編織復(fù)合材料的開孔試樣在拉伸條件下進(jìn)行了真實應(yīng)變場和模擬應(yīng)變場之間的誤差分析,并搭建了優(yōu)化更新平臺,以支反力為約束條件,應(yīng)變場誤差為目標(biāo)函數(shù),采用單純形法對四個面內(nèi)性能參數(shù)為設(shè)計變量進(jìn)行了優(yōu)化,收斂結(jié)果與相應(yīng)試驗測試數(shù)據(jù)吻合較好,說明了該平臺的可行性。
[Abstract]:Three-dimensional six-direction braided composite material is a kind of braided structure with good structural performance based on three-dimensional four-direction braided preform, which is composed of longitudinal and lateral immobility yarn respectively, because of its high specific stiffness. In addition to the advantages of high specific strength, it has excellent performance in such aspects as out-of-plane properties, shear properties and structural designability, so it has a broad application prospect in the field of aeronautics and astronautics, but there are few reports on its mechanical behavior. The only research focuses on the effects of different braiding angles and fiber volume fraction on the tensile or bonding properties of the material, which is required by the process requirements in the process of material selection and use in the design phase. However, as a typical orthotropic and tension-compression composite, in the design and application stage, it is necessary to consider the difference of mechanical properties of the material in different working conditions and in different directions. In addition, the prediction of the stiffness of the material is carried out. At present, there is a lack of combination with the observation results of real meso-structure and consideration of different properties of tension and compression, and the performance of the material is tested by referring to the relevant experimental standards of fiber reinforced laminates, which is faced with a large amount of experimental work, a long period and low efficiency. The cost is high, and it is difficult to compare the data horizontally between different types of experiments because of the different shapes of samples and the discreteness of composite material data. There is an urgent need to develop a method for measuring multiple mechanical properties in one experiment. Therefore, in view of the shortcomings and difficulties mentioned above, this paper mainly studies the following three aspects: firstly, for the small braiding angle, T300 / TDE86 3D hexagonal braided composites with medium fiber volume content were tested in different directions under different working conditions, including longitudinal tensile tests, compression tests in three different directions and in-plane shear tests. The corresponding data such as strength and modulus, failure mode and damage mechanism are obtained, and the similarities and differences between them and their causes are compared in detail. Secondly, on the basis of the four-step braiding process, The original material and the material after burning resin were observed in different directions, the meso-structure and characteristic parameters of the material were determined, as well as the kink and contact between the yarns. On the basis of certain assumptions, Considering the actual size of material, a full-scale geometric analysis model in thickness direction is established. The mechanical properties of fiber bundle and matrix are used. The stiffness prediction of the geometric analysis model in different directions is carried out by means of stiffness assembly technique. Compared with the experimental data, the predicted results are in good agreement with the experimental data except that the compression performance in the thickness direction and the in-plane shear stiffness error are larger. The accuracy of the stiffness prediction method in this chapter is explained. Finally, the error analysis between the real strain field and the simulated strain field of 3D hexagonal braided composites under tensile condition is carried out by using the digital image correlation technique (DIC) and finite element method, and the optimization updating platform is built. The four in-plane performance parameters are optimized by simplex method with the support reaction force as the constraint condition and the strain field error as the objective function. The convergence results are in good agreement with the corresponding test data, which shows the feasibility of the platform.
【學(xué)位授予單位】：哈爾濱工業(yè)大學(xué)
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2015
【分類號】：TB332

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本文編號：1580515