laminate composite 中文意思是什麼
laminate composite
解釋
成層材料-
In this paper, the mechanical character of composite level - stability - panel is analyzed, and the software clop is developed for the analysis of composite laminate strength
論文分析了某型直升機復合材料平尾的力學特性，並開發了能夠用於層合結構強度分析的計算機程序。 -
This article gives the subsistent ability and the analysis result of intensity after repair in the open field airplane composite material structure by research the intensity, rigid and repair problem under a axis compress loads on a typical three stiffened composite laminate which has a penetrability crack ( a scatter damage ) by a shrapnel
本文通過飛機典型復合材料三加筋層壓板結構在被彈片劃開一穿透性切口（離散源損傷）后，在軸向壓縮載荷作用下所產生的強度、剛度以及修理問題展開了技術研究及探討，給出軍機復合材料加筋板在彈擊後生存力以及外場修理后強度恢復分析結果。 -
Using the complex potential method in the plane theory of elasticity of an anisotropic body, the series solution of finite anisotropic thin plate containing an elliptical inclusion is proposed with the help of faber series. a hybrid element with an elliptical inclusion for anisotropic materials is obtained by using the hybrid variable principle, and the element efficiency is verified by numerical examples. the state of the damage is modeled by an elliptical soft inclusion, and using the point stress criterion based on characteristic curve and yamada - sun etc. criteria, the prediction of the strength of a composite laminate with damage is set up
首先基於經典層板理論，將復合材料層板的彈性問題化歸為均勻各向異性板來求解；採用各向異性體平面彈性理論中的復勢方法，以faber級數為工具，給出了有限大含橢圓核各向異性板彈性問題的級數解形式；利用雜交變分原理，成功導出含橢圓核各向異性板雜交應力有限元，並用算例驗證了該單元的可行性和有效性；採用含剛度折減橢圓形彈性核的沖擊損傷模型，引入基於特徵曲線和yamada - sun破壞準則的點應力判據，建立了含損傷復合材料層板剩餘強度的分析方法；通過數值計算詳細討論了各種幾何參數對損傷層板應力分佈、剩餘強度的影響，得到了一系列對工程應用具有實用價值的結論。 -
Damage analysis of aluminum alloy plate and composite laminate
鋁合金及復合材料板開孔損傷分析 -
The research is presented based on the classical laminate theories for special boundary conditions and few papers have been formulated based on higher - order laminate theories with various cases of boundary conditions. the paper will create the structural - engineering program with mathematica to solve the problem of composite laminated plates based on higher - order laminate theories with various cases of boundary conditions
目前僅局限於有特殊邊界條件的古典板理論，很少有文章涉到各種邊界條件的高階板理論。本文將利用mathematica的計算環境，編制結構分析程序，在各種邊界條件下，應用多種板理論求解各向異性矩形層合板的振動控制問題。 -
Based on the method of cell ( moc ), the effective elastic properties of resined fiber bundle with parallel or arbitrary orientation was studied, and a micro - mechanical model of resined plain - woven carbon fabric was established with the classical laminate theory, then, the method of calculation of the elastic moduli of resined plain - weave carbon fabric was presented, and can be extended to the whole carbon / phenolic composite
基於元胞法（ moc ）計算了預浸樹脂的平直以及任意取向的纖維束的有效彈性常數。基於經典層板理論用替代層法建立了預浸樹脂平紋機織碳布的細觀力學模型，進而給出了預浸氨酚醛樹脂的平紋機織碳布的彈性模量的計算方法，該方法可推廣到碳酚醛復合材料。 -
Laminate : a composite material made by bonding together several layers of same or different materials
積層板（層壓板） ：由數層相同或不同材料黏合製成的復合材料。 -
The in - plane equivalent elastic modulus and tensile strength of stitched composite laminates are studied, and it ' s found that the in - plane equivalent elastic modulus decreases with the increase of stitch density, stitch thread diameter, maximal misalignment angle and the distortion width, and the range is about 5 %. the tensile strength of stitched composite laminate increases with the increase of stitch step and decreases with the stitch space. the
研究結果表明：隨著縫紉密度、縫紉線直徑、最大纖維偏轉角和縫紉變形區寬度的增加，縫紉復合材料層合板面內等效模量逐漸降低，最大降幅一般在5 %左右；縫紉復合材料層合板的拉伸強度隨縫紉針距的增加而增大，隨縫紉行距的增加而降低，因此縫紉密度對拉伸強度的影響程度要看具體的縫紉針距和行距。 -
In this research, fatigue life of laminate composite is predicted phenomenologically, dealing mainly with in - plane stresses without accounting for out - of - plane failures such as delamination. fatigue modulus is used as a physical parameter which helps to describe the basic fatigue behaviour of unidirectional laminates and obtain expressions for cumulative damages defined by strains. based on some typical fatigue test data for unidirectional composite laminates, a cumulative fatigue damage model is presented for predicting the fatigue life of multidirectional laminates with arbitrary stacking sequence under complicated fatigue loadings
本文以碳纖維/樹脂基t300 / qy8911層壓結構為研究對象，從唯象的觀點出發，以疲勞模量為參量構造損傷函數，基於幾組最典型的單向板疲勞試驗數據，建立單向板在多軸循環應力作用下的疲勞壽命模型，並以此為基礎，發展同種材料體系的任意鋪層形式的多向層壓板在復雜循環載荷作用下的疲勞壽命預測方法。 -
The rigidity and strength performance such as tension bend, torsion of composite laminated plates are calculated by use of classical lamination theory, and then analyses the experiment methods for rigidity and strength of laminate in detail, the comparison of theoretical analysis and experimental result shows good consistent, which indicate that the theoretical analysis and experimental method presented there is applicable for design and manufacture of military medical shelter laminate. in addition, theoretical analysis is taken for heat preservation and insulation performance of the laminate material by use of stable plate heat conduction method
採用經典迭層理論，計算了軍用醫療方艙復合夾層大板材料的拉伸、彎曲及扭轉等剛強度性能，由此深入研究了夾層大板材料彎曲剛強度性能試驗方法，對理論分析進行了試驗驗證，結果表明該課題提出的理論分析和試驗方法適于軍用醫療方艙鋁塑復合夾層大板力學分析，對軍用醫療方艙鋁-聚氨酯-鋁復合夾層大板的力學結構設計和製造具有重要的應用價值。 -
And, the coefficient of heat conduction, temperature rise and fall in shelter chamber experiment are made, the result shows the stable plate heat conduction method is applicable, the integration of experience formula for calculation of heat and cool load and experiment analysis is suitable for design and validation of temperature in shelter chamber, the integration can nicely reflect the condition of microclimate temperature in shelter chamber, and have importance reference value for research of microclimate condition in shelter chamber. at last, in article the comparison is made between the felt techniques and foam techniques of the laminate plates, and improved manufacture techniques of composite laminate is brought forward. the experiment indicates the improved techniques can ensure the structure strength and heat preservation and insulation performance
基於軍用醫療方艙特殊的微環境使用要求，運用穩定平壁傳熱分析方法建立了軍用醫療方艙鋁塑復合夾層大板傳熱系數理論計算模型，對軍用醫療方艙鋁-聚氨酯-鋁復合夾層大板材料隔熱保溫性能進行了理論分析；運用經驗分析方法進行了冷熱負荷計算分析；並對兩計算採用傳熱系數和艙室升溫、降溫試驗進行了對比試驗研究，結果表明穩定平壁傳熱分析方法計算傳熱系數方法可行，為方艙鋁塑夾層大板的隔熱保溫結構和性能設計提供重要依據，並準確表徵艙室內部微環境溫度條件，對軍用醫療方艙艙室微環境設計提供參考。 -
The selection of material, typical the structural designs, the mechanical property and the forming pressure of unmanned aircraft sandwich composite material have been studied in this paper. it has analysed and discussed the flexural properties of honeycomb sandwich plate delamination under bending loads in detail. and then the mechanical properties of the laminate panel are studied which are compared with honeycomb sandwich panel
在圍繞某無人機蒙皮選用材料的基礎上，重點對蜂窩夾層結構的結構設計、力學性能、成型壓力對力學性能的影響，以及缺陷對蜂窩夾層結構復合材料的彎曲性能影響進行了較深入的實驗研究和理論分析，同時比較了蜂窩夾層結構中面板與同樣材料鋪層的疊層板力學性能的差異。 -
A study on micro - damage of laminate composite
層板復合材料的微損傷研究 -
Based on the homogenization method, the basic elastic properties prediction theory and method for stitched composite laminate were discussed
利用數學均勻化理論，討論了縫紉層壓板基本彈性性能預測的理論和方法。 -
The residual strength of damaged composite laminates and their repaired structures are calculated, and the influence of the repair parameters is discussed by the finite element and program stated above. some useful conclusion can be drawn according to the curves, which show the influence of repair parameters to repair effect. for the laminate which contains a circle hole, the suggested patch shape is circle, the patch size is 2 to 3 times than the diameter of damaged hole, the patch thickness is equal to the parent laminate and the patch stacking sequence is the same as the parent laminate
用所建立的二維有限元模型和編寫的有限元程序計算損傷板及其修補結構的剩餘強度，並分析了修補參數對修補效果的影響；根據本文計算得到的修補參數對修補效果的影響曲線，可以得到如下結論： ?對于含孔復合材料層壓板，當圓形補片與母板鋪排順序相同、直徑為損傷孔直徑2 3倍、相對厚度為100時能夠獲得比較好的修補效果。 -
Because of the whole braid of the multi - orientations, braided composite materials overcome the defects of the traditional laminate composite and reinforce the equality of intensity in every orientation, and is a new advanced material for the time being, and widely applied in many industries, such as aerospace industry etc. in this paper, the research work is mainly including following : ( 1 ) this paper introduces the research and application conditions of 3d woven technique and rtm
由於採用多向纖維束的整體編織技術，三維紡織復合材料提高了復合材料的整體性和各個方向強度的均勻性，克服了傳統層合復合材料的缺點，是一種新型的先進材料，在航空航天等領域有著廣闊的應用前景。本文介紹了三維機織工藝和rtm工藝的現狀，敘述了三維機織復合材料的研究現狀。 -
Based on the research of the problem of reinforcement in realistic projects. sheared to the cmmr ( composite mortar laminate reinforced with mesh reinforcement ) to reinforce the rc beams to carry on the analysis and some experiments are studied in this paper. the main contents are as follows : 1 、 the problem for strengthening design of rc structure which aims at researching on shear strengthening of rc beams using cmmr and improving the effectiveness and efficiency of strengthening design is presented in this paper. put forward the strengthening methods in this paper. 2 、 the shear mechanism of the rc beams is discussed in the paper
本文是在以實際工程中提出的加固的問題為研究背景，對水泥復合砂漿鋼筋網抗剪加固混凝土梁進行了分析，進行了一些試驗研究，本文主要內容包括: 1 、針對混凝土梁抗剪加固破壞的相關問題進行研究，提出使用水泥復合砂漿鋼筋網提高混凝土梁抗剪性能，並對採用水泥復合砂漿鋼筋網抗剪加固混凝土梁的問題進行了探討。 -
In this dissertation, a global - local approach using hybrid stress element and its application in the stress distribution and the residual strength of composite laminate weakened by damage are studied in detail
本文主要研究了基於雜交應力有限元的global - local方法及其在含損傷復合材料層板的應力分佈和剩餘強度方面的應用。 -
Composite laminate shells have been applied more and more widely in aerospace structures. in order to increase thrust to weight ratio and improve the comprehensive performance of airplane, optimization design must be carried out. this thesis brings forward utilizing the method of aga - fem, which combines adaptive genetic algorithm ( aga ) and finite element method ( fem ), to optimize fibre - reinforced composite shells
本文提出採用自適應遺傳演算法（ adaptivegeneticalgorithm ）和有限元方法（ finiteelementmethod ， fem ）結合即aga - fem方法進行纖維增強型復合材料層合殼結構的優化設計，並對某航空發動機復合材料機匣進行優化設計分析，取得了很好的效果。 -
4, using the finite element method, the buckling of the case is studied under the loads including the axial force torsion and pressure. the results will be benefit for aero - engine design in the future. the buckling characteristics of the two new kinds of composite ( t300 / kh - 304 and t300 / bmp - 316 ) is studied under the same boundary conditions sizes and plies, the anti - buckling ability of t300 / kh - 304 composite laminate is better than that of t300 / bmp - 316 composite plates
4 、首次用有限元法和圓柱殼體耦合理論分析了t300 bmp - 316復合材料機匣分別在軸向力、扭矩和內壓等單獨作用以及耦合作用下的屈曲特性，為進一步研究打下了基礎；運用有限元法分析了t300 kh - 304和t300 bmp - 316兩種復合材料層合板的屈曲特性，討論了鋪層方式、尺寸、位移邊界條件等參數對屈曲特性的影響。
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