翼構件 的英文怎麼說
中文拼音 [yìgòujiàn]
翼構件
英文
wing member-
In addition to, the fatigue crack between web and upper flange of welded steel crane beam on heavy duty service was discussed, and based on long - term observation and research, the author classified fatigue crack into bearing type and middle type crack along the horizontal direction. the causation, distributive law and mechanism of the crack were analyzed, and the precautions to take and the measures to remedy crack were presented. the main defacts including damage, crack, erosion and aging in structures, especially in concrete structure were introduced ; the defact mechanism was analyzed and the precautions to take were also given
另外，作者對重級工作制焊接鋼吊車梁腹板與上翼緣連接焊縫的縱向水平疲勞裂縫進行了長期的觀察和研究，根據疲勞裂縫產生的不同機理，將其分為支點裂縫和肋間裂縫，並討論了兩類裂縫產生的原因、分佈規律、機理以及防治的措施；對工程中經常遇到的結構構件，尤其混凝土構件的幾種主要病害（損傷、裂縫、腐蝕與老化）進行了機理分析並提出了防治措施。Along with the winglet / chimneys seen in saturday ' s european update, these triangular air vents form another definitive part of ferrari ' s latest aero package
同周六歐洲站的技術分析中已經介紹過的小翼/風道一樣，這些三角形的通氣孔也構成了法拉利賽車最新空力學套件的另外一個部分。In this thesis, four types of steel beam - rectangular cfst column connections, including normal welded flange plate ( wfp ) connection, bolted flange plate ( bfp ) connection, stiffened end plate ( sep ) connection and double split - tee plate ( dst ) connection, were designed based on the configuration of steel frame connection. total 8 models, 2 models of each kind of connections were tested under low - reversed cyclic loading at the end of cfst columns. the relationships between force and displacement at the end of columns, the relationships between the moment and rotation of the joints, degradations of strength and stiffness, ductility, failure mechanism and failure characteristics of these four connections under different axial - compression ratios were presented
本文借鑒鋼框架節點構造，設計了四種類型矩形鋼管混凝土柱與鋼梁連接節點，包括常規栓焊（ wfp ）節點、翼緣全螺栓連接（ bfp ）節點、雙t板連接（ dst ）節點以及加勁端板連接（ sep ）節點，進行了四類節點8個模型試件在柱端低周反復荷載作用下的抗震性能試驗研究，比較了不同軸壓比下節點的滯回性能、強度與剛度退化、延性、破壞機理與破壞特徵，主要結論有： 1 、節點的位移滯回曲線與轉角滯回曲線為塊型分佈，沒有或略有捏攏現象，耗能能力強； 2 、軸壓比對節點滯回曲線有顯著影響，全部節點都有顯著的剛度退化； 3 、位移與轉角骨架曲線在峰值荷載後有較長的水平或下降段，具有良好的延性性能； 4 、從整體抗震性能上看，翼緣全螺栓連接節點、雙t板連接與加勁端板連接節點都優于常規栓焊節點，可在實際工程中加以推廣。Compared with a delta wing aircraft, the double - delta wing configuration has better aerodynamic performance at high angles of attack. an operational analysis was introduced as a method for evaluating training effectiveness of trainer aircraft. approaches to the engineering estimation of aerodynamic characteristics for aircraft with a double - delta wing configuration were studied, and the procedures for determining aircraft performance indices formulated. taking training effectiveness as the objective function and geometric parameters of the wing platform as design variables, through a numerical multivariate optimization arithmetic, the conceptual design optimization for a certain fighter trainer aircraft with double - delta wing configuration was carried out under the constraints of tactical and technical requirements and interrelated geometry. agreement of a calculation example with engineering practice indicates that the optimal design has higher training effectiveness than the baseline design, and in addition, improves the structural force - bearing conditions
雙三角翼氣動布局比三角翼飛機具有更好的大攻角空氣動力特性.引入了評估教練機訓練效能的作戰分析法，研究了雙三角機翼布局飛機空氣動力特性的工程計算途徑以及飛機性能指標的確定方法.以訓練效能作為目標函數並選取機翼平面形狀的幾何參數為設計變量，採用多變量數值尋優方法，在戰術技術指標及相關幾何約束條件下，對某高級教練機的雙三角機翼氣動布局方案進行了優化選擇.算例表明最優方案不僅比原準方案具有更高的訓練效能，還改善了結構的受力情況，與工程實踐吻合First, on the base of investigating geleshan geologic environments, the author carefully analyzes them, studies their water storage structure, discusses the relationship of underground water dynamic changes and tunnel drainage by desiccation ; secondly, the author makes the dynamic analysis, regression analysis, routine hydrochemistry analysis, isotope analysis, so draws to guan - yin gorge anticlire east and west slot ' s karst developing features, alternated conditions underground water and supplying drain ways ; thirdly, by stating the fissuring ' s surveying data, the author calculates the seeping tensor
作者在進行歌樂山地質環境調查的基礎上，仔細分析了大量觀測資料，研究其儲水構造，掌握地下水動態變化與隧道施工涌水的關系，及補給受降雨的影響情況。對隧道周圍的地下水進行動態分析、回歸分析、常規水化學分析以及同位素分析，得出觀音峽背斜東西翼槽谷的巖溶發育特徵，及地下水的循環交替條件、補給排泄途徑；統計分析裂隙測量數據，計算滲透張量。The critical crack and stress put forward provides theoretic foundation for monitoring portal machine. 3. applying steady theory of board, studying the problem of early curvature, flexibility model, welding remaining stress, elastic transmutation and brace condition and so on, conclude that structure of beam is primary place where metal structure of portal crane lose stabilization and the break of main beam is result of losing partial stabilization of main board
文章提出的界限應力和臨界裂紋對于港口機械的監測提供了理論依據； 3 、運用板的穩定理論，探索了作為薄壁構件的門機金屬結構在失穩破壞中所涉及到的初曲率問題、彈性模量問題、焊接殘余應力問題、彈塑性變形問題以及支承條件問題等，得出了門機金屬結構發生失穩破壞的主要部位為臂架結構，且主臂架的折斷是由於受壓翼板局部失穩引起整體破壞； 4 、探討了焊接對結構承載的影響。Gabled frames are widely used in industry and civil engineering, it ' s web plates " local buckling calculated formula in the technical specification for steel - structure of one - storey light - weight buildings with gabled frames ( cecs102 : 98 ) are based on the rectangular plates " and did n ' t consider the interaction of the fringe plate. so, there are some different between the actual members and the prescript of the specification, and the post - buckling strength ' s calculated formula is based on the local buckling ' s, it must have some unreasonable
楔形門式剛架廣泛地應用於工業與民用建築中， 《門式剛架輕型房屋鋼結構技術規程》 （ cecs102 ： 98 ）中楔形腹板局部屈曲的計算公式來自矩形板，並且沒有考慮翼緣的相關作用，因此，規程中的規定與構件的實際工作狀況有一定的差異，且屈曲后強度的計算公式也是以局部屈曲系數為基礎的，勢必有其不合理性。The form of variable cross - section, used mostly in the practical projects, just has the change of the linear variation on the height of the web plate while keep the width of the flange c hangeless
實際工程中使用最多的變截面構件形式是僅構件腹板高度線性變化，翼緣寬度保持不變的形式。Self - diagnosing system based on the fiber optic smart network is built, which function is force identification of wing box
構建了基於光纖智能傳感網路的自診斷系統，實現了機翼盒段試驗件的載荷識別。In order to determine the relations between the four main bond - anchoring factors - concrete strength, concrete cover thickness, steel shape embedment length and the ratio of the transverse hoops - and the bond strength, and establish the bond - slip constitutive relations, 16 standard push - out test specimens were designed, and 4 comparison specimens were additionally designed to find the difference of the bond performance between the web, inside and outside of flanges the steel shape
設計了16個型鋼混凝土標準推出試件，以考察混凝土強度、型鋼的混凝土保護層厚度、型鋼埋置長度及橫向配箍率四個主要錨固條件與粘結強度的相互關系和型鋼混凝土粘結滑移本構關系；設計了4個對比試件，以考察型鋼翼緣內側、外側和腹板與混凝土粘結性能的區別。On the assumption of ignoring the distortion of thickness, this paper determines the rough shape by the geometric modeling method of equal area developing using mixed mesh cell of triangle and quadrangle for the first time, presents the equal area developing arithmetic of quadrangle - triangle. on the virtual geometric symmetry axis, we puts forward the method of determining the developed coordinate of the point on the base band in the development of using regular quadrangle cell, determines the developed shape of internal structure in plane utilizing point - to - point mapping theory. furthermore, we realize the approximate developing of undeveloped - irregular boundary surface using a few triangle cells
本文結合型號研製中小曲率機翼整體壁板類零件坯料展開課題，基於板料厚向變形忽略不計的先驗假設，首創混合四邊形-三角形網格等面積展開的幾何模擬法確定壁板類零件毛坯外形，給出了混合四邊形-三角形網格等面積展開演算法；提出了虛擬分割線的概念，採用虛擬幾何對稱軸，給出了規整四邊形單元展開基帶上結點的計算方法；採用映射原理和求交演算法確定了壁板內部結構信息的展開定位。After comparing between the finite - element analysis and experimental results, the author verified the fem. then according to the chinese code, the nonlinear finite model of the beam - to - column is established which are made of different size components. the responses of beam - to - column web moment connections which are made of different size components are compared and analyzed from three facets, and the conclusions about the joints behavior are drawn : thicken the connection plate, lengthen the connection plate or use a back - up stiffer can improve the connection behavior, consist of improving the behavior of load - supported and reducing the stress convergence in the flange moment plates
本文根據我國規范的有關規定，自行建立了12個不同構件尺寸的樑柱腹板連接的三維有限元模型，對不同構件尺寸的樑柱腹板剛性連接節點在單向荷載作用下的反應進行了研究，從結構的mises應力等值線示意圖、梁端加載處的荷載? ?位移曲線、翼緣連接板兩端的mises等效應力以及翼緣連接板與柱相連接的三邊的mises應力等值線示意圖四方面進行了比較與分析，從而得出了不同構件尺寸的樑柱腹板剛性連接的在受力行為上的結論：增加翼緣連接板的厚度、增加翼緣連接板的長度以及採用柱的橫向加勁肋均可以改善節點的受力性能：提高節點的承載能力；減小翼緣連接板內部與柱翼緣邊的的應力不均勻現象，從而避免試件過早地發生破壞。Abstract : a new method, collaborative allocation ( ca ), is proposed to solve the large - scale optimum allocation problem in aircraft conceptual design. according to the characteristics of optimum allocation in aircraft conceptual design. the principle and mathematical model of ca are established. the optimum allocation problem is decomposed into one main optimization problem and several sub - optimization problems. a group of design requirements for subsystems are provided by the main system respectively, and the subsystems execute their own optimizations or further provide the detailed design requirements to the bottom components of aircraft, such as spars, ribs and skins, etc. the subsystems minimize the discrepancy between their own local variables and the corresponding allocated values, and then return the optimization results to main optimization. the main optimization is performed to reallocate the design requirements for improving the integration performance and progressing toward the compatibilities among subsystems. ca provides the general optimum allocation architecture and is easy to be carried out. furthermore, the concurrent computation can also be realized. two examples of optimum reliability allocation are used to describe the implementation procedure of ca for two - level allocation and three - level allocation respectively, and to validate preliminarily its correctness and effectiveness. it is shown that the developed method can be successfully used in optimum allocation of design requirements. then taking weight requirement allocation as example, the mathematical model and solution procedure for collaborative allocation of design requirements in aircraft conceptual design are briefly depicted
文摘:探討了一種新的設計指標最優分配方法- -協同分配法，用於處理飛機頂層設計中的大規模設計指標最優分配問題.分析了飛機頂層設計中的設計指標最優分配特徵，據此給出了協同法的原理並建立了數學模型.協同法按設計指標分配關系將最優分配問題分解為主系統優化和子系統優化，主優化對子系統設計指標進行最優分配，子優化以最小化分配設計指標值與期望設計指標值之間的差異為目標，進行子系統最優設計，或對底層元件（如飛機翼梁、翼肋和翼盒等）進行設計指標最優分配，並把最優解信息反饋給主優化.主優化通過子優化最優解信息構成的一致性約束協調分配量，提高系統整體性能，並重新給出分配方案.主系統與子系統反復協調，直到得到設計指標最優分配方案.兩層可靠度指標分配算例初步驗證了本文方法的正確性與可行性，三層可靠度指標分配算例證明了本文方法的有效性.最後，以重量指標分配為例，簡要敘述了針對飛機頂層設計中設計指標協同分配的數學模型和求解思路A new method, collaborative allocation ( ca ), is proposed to solve the large - scale optimum allocation problem in aircraft conceptual design. according to the characteristics of optimum allocation in aircraft conceptual design. the principle and mathematical model of ca are established. the optimum allocation problem is decomposed into one main optimization problem and several sub - optimization problems. a group of design requirements for subsystems are provided by the main system respectively, and the subsystems execute their own optimizations or further provide the detailed design requirements to the bottom components of aircraft, such as spars, ribs and skins, etc. the subsystems minimize the discrepancy between their own local variables and the corresponding allocated values, and then return the optimization results to main optimization. the main optimization is performed to reallocate the design requirements for improving the integration performance and progressing toward the compatibilities among subsystems. ca provides the general optimum allocation architecture and is easy to be carried out. furthermore, the concurrent computation can also be realized. two examples of optimum reliability allocation are used to describe the implementation procedure of ca for two - level allocation and three - level allocation respectively, and to validate preliminarily its correctness and effectiveness. it is shown that the developed method can be successfully used in optimum allocation of design requirements. then taking weight requirement allocation as example, the mathematical model and solution procedure for collaborative allocation of design requirements in aircraft conceptual design are briefly depicted
探討了一種新的設計指標最優分配方法- -協同分配法，用於處理飛機頂層設計中的大規模設計指標最優分配問題.分析了飛機頂層設計中的設計指標最優分配特徵，據此給出了協同法的原理並建立了數學模型.協同法按設計指標分配關系將最優分配問題分解為主系統優化和子系統優化，主優化對子系統設計指標進行最優分配，子優化以最小化分配設計指標值與期望設計指標值之間的差異為目標，進行子系統最優設計，或對底層元件（如飛機翼梁、翼肋和翼盒等）進行設計指標最優分配，並把最優解信息反饋給主優化.主優化通過子優化最優解信息構成的一致性約束協調分配量，提高系統整體性能，並重新給出分配方案.主系統與子系統反復協調，直到得到設計指標最優分配方案.兩層可靠度指標分配算例初步驗證了本文方法的正確性與可行性，三層可靠度指標分配算例證明了本文方法的有效性.最後，以重量指標分配為例，簡要敘述了針對飛機頂層設計中設計指標協同分配的數學模型和求解思路On the background of aeronautics and astronautics requirement, along with the line of modularization of fiber optic smart structure, aimed at the safety matter of aerofoil pivotal parts, build optic fiber smart layer self - diagnosing system
以航空航天需求為背景，以光纖智能結構的集成為主線，針對飛機機翼關鍵部件安全性問題，建立了基於光纖智能夾層的自診斷系統。Firstly, itis explained that the application research of smart layer. to laod detecting and simulative damage for the model of wing - box, fbg fiber smart layer and pzt smart layer are designed, and manufactured. so, those are surface - mounted respectively on the stiffened skin of aluminum alloy and carbon fiber reinforced. data acquisition system based on different signal processing technique are designed
針對機翼盒段試件結構載荷識別和模擬損傷監測的功能要求，結合智能夾層的設計製作工藝，設計製作了基於fbg傳感器的光纖和壓電兩種智能夾層，並分別安裝在機翼盒段試件上的鋁合金和碳纖維制蒙皮上。The analysis on the 5 " flanking region revealed tata box, putative api and nur77 response elements, prl and progesterone response elements motifs related with regulation on 20ahsd gene expression
通過軟體對克隆到的5側翼區結構和功能分析，發現了20 hsd基因的tatabox 、 prl反應元件、類固醇激素反應元件、 ap1和nur77等轉錄因子結合位點。According to the theory of boundary layer and the important of boundary - layer separation point detection of delta wing, the measuring principle and structure scheme of various system alternatives based on mems technology have been discussed, selecting the prototype of better workability. base on the master piece model of micro shear stress sensor
首先，結合空氣動力學的邊界層原理，針對三角翼邊界層分離點檢測在實現主動氣動控制方面的重要性，討論了光學式、電容式和熱敏式微型剪應力傳感器的測量原理和結構方案，選取適合加工條件的微型剪應力傳感器樣件。It is mainly made up of lognitudinal framework, latitudinal framework, airfoil shell, tie - in etc. for the frp airfoil shell, we generally use moulding method of handcraft laying
飛機機翼曲面是一個結構復雜的非回轉曲面，其整體結構主要由縱向骨架、橫向骨架、蒙皮和接頭等構件組成。With these work groundings, the working stress levels for individual component of the folded - wing are evaluated
在此基礎上，對折疊翼面機構各構件在彈性動力學運動過程中的工作應力水平給予了分析與評估。分享友人