composite laminate的意思

composite laminate中文翻譯：

復合層壓板

復合材料層壓板

相似詞語短語

composite───v.合成（圖片）；使混合；n.復合材料，合成物；綜合提案；菊科植物；混合柱式；（嫌疑犯的）合成照片；adj.復合的，合成的；（火車車廂）綜合的；（柱式）混合的；菊科的

laminate───adj.薄片狀的；層狀的；v.將鍛壓成薄片；分成薄片；n.薄片制品；層壓制件

laminate countertops───層壓臺面

durion laminate───durion層壓板

laminate flooring───強化地板；復合地板；層壓木地板

formica laminate───formica層壓板

recurved composite bow───[體]兩端反曲合成材料弓

climatize laminate flooring───氣候強化木地板

laminate wood flooring───強化木地板

雙語使用場景

Parametric FEM technique is used to analyze the mechanical performance and structural reliability of composite laminate structures. The parametric FEM code based on ANSYS is given.───參數化有限元技術分析復合材料層合結構力學性能和結構可靠度的方法，并基于ANSYS軟件平臺開發相應的參數化有限元程序。

method was also used to measure strain in the tensile test of a composite laminate plate. The results agree fairly well with those obtained by the conventional measurement.───并進行了復合材料板拉伸試驗，復合材料平板實驗計算結果和應變電測法得到的結果進行了對比，實驗表明兩種測量方法得到的結果相吻合。

The change in critical load value of both composite laminate plates with embedded and through-width delamination shows the same pattern for various delamination size.───對不同的脫層損傷尺寸，層合板分別有整體、混合和局部三種屈曲模態，穿透脫層和埋藏脫層的層合板其臨界載荷的變化規律是相同的。

Delamination is one of the important defect forms of composite laminate construction.───局部分層屈曲是復合材料層殼結構的一種重要損傷形式。

For instance the material forming the composite laminate may be reinforced, and the resin forming the impact indicator may be un-reinforced.───例如，制造復合層壓制品的材料可以是加強的，而制造撞擊指示物的樹脂可以是非加強的。

The fracture mechanics feature of elliptical delaminations in a composite laminate is studied.───對復合材料層板中橢圓分層的斷裂力學問題進行了研究。

The first and second scrim layers constitute exposed surfaces of the composite laminate.───上下兩層薄亞麻仍作為復合材料片層的表層裸露在外。

The transient response of delaminated composite laminate under low velocity is discussed in the present paper.───研究了含脫層損傷的復合材料層板在低速沖擊下的瞬態響應問題。

Study of Delamination Buckling for a Symmetric Cross-ply Composite Laminate under Uniaxial Loads───單軸載荷作用下對稱正交鋪設層合板的脫層屈曲研究

英語使用場景

In this paper, Full Strain Design method and Sublaminate are combined to optimize fibre - enhanced composite laminate.

The stacking sequence of composite laminate was calculated at given in - plane geometry and bend factors.

Based on two hypothesis, a new kind of four parameters model was posed that used on S N curve over long and middle life range of composite laminate.

The Rayleigh-Ritz method is used to calculate the critical load at which delamination buckling will occur for a symmetric cross-ply composite laminate containing a single delamination.

Finally aeroelastic tailoring technique of composite laminate is applied to forward - wing structure to improve divergence speed.

The effect of hole diameter on bearing capacity of alloy plate and composite laminate was analyzed.

The transient response of delaminated composite laminate under low velocity is discussed in the present paper.

The first and second scrim layers constitute exposed surfaces of the composite laminate.