等值翼 的英文怎麼說

中文拼音 [děngzhíyì]
等值翼 英文
wing; equivalent
  • 等 : Ⅰ量詞1 （等級） class; grade; rank 2 （種; 類） kind; sort; type Ⅱ形容詞（程度或數量上相同） equa...
  • 翼 : Ⅰ名詞1 （翅膀） the wing of a bird 2 （像翅膀的東西） the wing of an aeroplane etc : 鼻翼 wing of...
  • 等值 : equivalent; equivalence
  1. It is the key of ebfs, therefore, furthermore calculation about link are carried out in this thesis, introduced achieved research, summarized the affect of link on whole capability in the first, the second, numerical calculation are proceeded on link with ansys : with the purpose of discussing yielding mode critical length of link, established five different specimens ; with the purpose of discussing the influence of h / tw of web, b / tf of flange and h / b, established eighteen different specimens ; with the purpose of discussing the affect of stiffener, established four different specimens, and elaborated the affect of stiffener on link based on achieved test researches

    因此，本文對耗能梁段進行進一步計算分析，概述耗能梁段對整體性能的影響，並利用有限元程序ansys對耗能梁段進行數值計算：針對耗能梁段的屈服類型建立5種不同長度的模型，計算討論耗能梁段屈服類型的長度劃分；針對耗能梁段腹板高厚比、翼緣寬厚比以及梁段截面形狀等因素共建立了18種模型進行計算分析；針對加勁肋對耗能梁段的作用建立了4種模型，並結合已有的試驗闡述了加勁肋對耗能梁段的影響。
  2. The numerical algorithm of solving the adjoint equations for different design cases have been developed by using finite volume methodology which is usually used to solve the flow governed equation. it includes the some important aspects, such as flux formulation, wall and far - field boundary treatment methodology, dissipative term formulation, etc. after the solution of the adjoint equations is obtained, the derivatives of the cost function with respect to all the design variables can be evaluated with the same operation. this can yields a significant saving over the other gradient - based techniques when there are many design variables

    （ 3 ）進行了應用控制理論和三維歐拉方程的機翼氣動反設計研究，以及有升力約束情形下機翼跨音速減阻問題研究，分別推導了相應的共軛方程及邊界條件數學表達形式，研究與發展了三維共軛方程的有限體積數值求解方法，及相應梯度公式的數值求解方法，通過對計算網格生成、流場計算、共軛方程數值求解、梯度求解和優化演算法等多方面的有效結合，成功發展了三維機翼的氣動反設計和跨音速減阻優化設計程序，成功地進行了多個設計算例研究。
  3. The wing - in - ground - effect ( wig ) vehicle is a new type of high performance vehicle with many advantages such as high speed, good economics, good stealth, easy to take off or land, and so on

    地效翼船作為一種高性能的新型高速運載工具，具有經濟性好，起降方便，隱蔽性強等多種優點，具有巨大的軍事和民用應用價值。
  4. As is well known, the effective width depends on several factors, such as the cross - section width, the height of web, the spacing of span and so on. we can conclude that width / span ratio ( overhang width / span and central width / span ) is the governing factor of the effective width

    影響箱形截面樑上翼緣有效寬度的因素很多，如上翼緣寬度、梁高、跨度以及結構體系等，通過大量計算表明寬跨比[翼緣部分寬度、箱室部分寬度與跨度的比值]是有效寬度的控制影響因素。
  5. This variation of stresses is due to the action of in - plane shear strain in the plate, which is termed “ shear - lag ”. stresses larger than the elementary bending uniform stress thus develop at the web - flange connection. an appropriate reduced “ effective width ” of the plate - with the uniform stress equal to the maximum longitudinal stress - has been widely used by engineers in conjunction with the elementary beam bending theory

    但實際上翼緣中剪切變形是不均勻的，由此導致正應力沿橋寬呈曲線分佈，從而引出了有效寬度的概念，即按初等梁理論的公式也能得與真實應力峰值接近相等的那個翼緣折算寬度。
  6. 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。
  7. 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
  8. 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
  9. The dissertation presents the combined theoretical, numerical and experimental studies on the experimental modeling of the actuator, the design of test rig and control system, the modeling of two - dimensional airfoil aeroelastic system, the control design of active flutter suppression, and the effect of group delay in the digital filter on the stability of aeroelastic closed - loop system

    本文通過理論分析、數值模擬與風洞實驗相結合的方法，研究了超聲電機作動器建模、翼段顫振實驗裝置和控制系統設計、二維翼段氣動彈性系統建模、顫振抑制控制律設計以及數字濾波器群時延對顫振抑制閉環系統穩定性影響等問題。
  10. The investigation in this dissertation shows the capabilities of ausm + scheme, such as the exact resolution of shock, low numerical dissipation, simple and requiring less computational effort. the successful applications on supercritical airfoils and wings show that the present flow solvers based on ausm + scheme are of valuable and promising in practical application

    通過本文的研究工作，展示了ausm +格式的激波高解析度、數值耗散小、編程簡潔、計算量較小等特性，同時，將其成功地應用於跨音速超臨界翼型、機翼的定常或非定常氣動特性的數值模擬和顫振研究中，具有一定的工程應用價值和良好的發展前景。
  11. In the examples we get some evolution curves, such as the growth rates and shape functions, which are used to analyze the stability problems for the boundary layers of the fuselage and the wing

    算例給出了擾動幅值增長和形狀函數等演化曲線，並對機翼、機身的邊界層穩定性進行了分析和研究。
  12. Extensive numerical studies have been performed in order to access the accuracy of the present approach, for example, the supersonic flow over the shuttle, and so on. all of results demonstrate the capability of simulating complex flow fields efficiently and robustly

    應用上述方法進行大量的數值實驗，如計算航天飛機的超音速繞流、 m6機翼的跨音速繞流等，數值結果顯示，上述方法是行之有效的。
  13. The main numerical method of this code is coming from scheme ( jameson, schimit and turkel ) : using cell - centered finite volume method as spatial discretization tools, and a system of ordinary differential equations for time variable is obtained, which is solved by utilizing five - step runge - kutta scheme as time marching method, introducing artificial dissipation to damp high frequency oscillations near the shock and stagnation point

    本論文採用歐拉方程作為控制方程，利用中心有限體積法進行空間離散，得到對時間變量的常微分方程組，採用龍格庫塔多步法進行時間積分，加入人工粘性以消除激波和駐點附近的壓力振蕩等方法來對naca0012翼型的實際流動進行并行數值模擬。
  14. We studied four eddy viscosity models ( evm ) and three nonlinear easm models in detail. the two - equation turbulence models are validated through simulating the flow fields over flat plate, airfoils and onera m6 wing. the capabilities of different turbulence models are accessed in this study

    加入兩方程湍流模型后，通過對平板、翼型、 oneram6機翼等繞流流場的數值計算，驗證了加入的各湍流模型的準確性，測試了它們對不同湍流流場的預測能力。
  15. Convergence is accelerated by means of local time stepping, implicit residual smoothing. the numerical results have been obtained for the flows over n ac ago 12 or rae2822 airfoils

    並且基於點雲離散結構，引入了當地時間步長、殘值光顧等加速收斂技術，數值模擬了對稱和非對稱翼型繞流，獲得較好的計算結果。
  16. On the basis of analysis previous experiment data, it is conclusion that allowable value of drift angle of elastic and elastic - plastic is 1 / 550 and 1 / 75 respectively, which is applicable to r. c. frame structure with special - shaped column is given out. the conclusion explains that the deformabiliry of r. c. frame structure with special - shaped column lies between rectangle column frame structure and shear wall structure. the calculating formula of allowable value of axial load ratio of special - shaped column is derived, it is compared with that of equaling areas rectangle column

    根據對前人試驗數據的統計分析，給出了適用於異形柱框架結構的彈性和彈塑性層間位移角限值分別為1 550和1 75 ；指出了異形柱框架結構的層間變形能力介於普通矩形柱框架結構和剪力墻結構之間；以t形柱為例，推導了異形柱軸壓比限值的計算公式，通過與等面積矩形柱的對比分析，認為異形柱的軸壓比限值與其截面尺寸的比例關系有關；當腹板受壓或翼緣受壓時， t形柱軸壓比限值存在較大差異；不同的荷載角作用，軸壓比限值變化較大；矩形柱的軸壓比限值要大於異形柱的軸壓比限值。
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