氣動力設計 的英文怎麼說

中文拼音 [qìdònglìshèjì]
氣動力設計 英文
aerodynamic design
  • 氣 : Ⅰ名詞1 （氣體） gas 2 （空氣） air 3 （氣息） breath 4 （自然界冷熱陰晴等現象） weather 5 （氣味...
  • 力 : Ⅰ名1 （力量; 能力） power; strength; ability; capacity 2 [物理學] （改變物體運動狀態的作用） forc...
  • 設 : Ⅰ動詞1 （設立; 布置） set up; establish; found 2 （籌劃） work out : 設計陷害 plot a frame up; fr...
  • 計 : Ⅰ動詞1 （計算） count; compute; calculate; number 2 （設想; 打算） plan; plot Ⅱ名詞1 （測量或計算...
  • 設計 : devise; project; plan; design; excogitation; layout; layout work; styling
  1. In order to design the autopilot for a rear controlled missile we must make a first estimate of the required aerodynamic derivatives.

    為了設計尾部控制導彈的自動駕駛儀，我們必須首先估算一下所需要的氣動力導數。
  2. The additional flow is formed by the device of dentoid baffle, and the application of the device of dentoid baffle cooperated with a stilling basin has been investigated by systematic model tests. based on the research results, the hydraulic problems such as the characteristics of hydrodynamic pressure and cavitation on the head of the denotid baffle, the properties of flow under the condition that the device of denotid baffle is used with a stilling basin, the hydraulic computation about a stilling basin, the estimation of energy dissipation and its various affection factors, the mechanism and effect of energy dissipation, and distributions of velocity and pressure and aerating concentration, etc, have been analyzed ; the method and step of hydraulic design of device of denotid baffle by which the additional flow is produced has also been proposed

    文中利用齒墩設施實現附加射流，對齒墩設施與消力池聯合應用進行了大量的和系統的模型試驗，分析研究了中低佛勞德數條件下，齒墩墩頭的動水壓強及空化特性，齒墩設施與消力池聯合應用時的流態特性，消力池的水力計算，消能量的估算及其各種影響因素，消能機理和效果，消力池內的流速、壓強特性，摻氣濃度分佈等水力學問題，並提出了實現附加射流齒墩設施的水力設計方法和步驟。
  3. The paper designed aerodynamic control system of pith and yaw channels and roll angle stabilization system, by using unsteady - state error follow - up control theory and state observation station theory in modern control theory

    本文使用現代控制理論中的無靜差跟蹤控制系統理論與狀態觀測器理論，設計了俯仰、偏航兩個通道的氣動力控制系統和滾轉角穩定系統。
  4. Gin factory test pilots wanted a wing with nice dynamic handling ， good for fun and tricks ， smooth and light ， precise in the turn ， thermal biting

    試飛員們的目標是設計出一款擁有出色的空氣動力學性能，輕便，平穩，轉向精確，良好的氣流攀升性能的雙人傘！
  5. Water drainage, waste water treatment, outdoors water supply drainage, and the fire protection water system. - gas utility team : specialized in design of cold water, bulk gas h2, o2, n2 preparation, purified gas supply, compressed air preparation, and special gas co2, ar2, hcl. etc preparation system, etc

    氣體動力設計組：冷凍水供給大宗氣體制備提純供給系統，空氣壓縮制備供給工程，特種氣體r cl等制備提純供給工程等。
  6. Attestation car of gmp : the special wall face with the ground material, in addition to the dust equipments, in addition to the wet equipments, constant temperature equipments, the pure water decontamination system, purify the air condition, cleanness to deliver the machine, cleanness to deliver the window, breeze to pour the room and transport with connect the appropriation tube piece with to pump the valve, stainless steel ware, professional clothing and product, the air compressor, calculator related system and software, the factory motive equipments and attestation of gmp of other products and equipments

    Gmp認證車間特別墻面與地面材料除塵設備除濕設備恆溫設備純水凈化系統凈化空調潔凈傳遞器潔凈傳遞窗風淋室輸送與連接專用管件與泵閥不銹鋼製品專業服裝與製品空氣壓縮機計算機相關系統與軟體工廠動力設備及gmp認證的其它產品與設備。
  7. It is necessary to study the unsteady nonlinear aerodynamic characteristics of a wig flying in air with disturbed waves for the design of high - performance wig vehicle, especially for the subject that how to improve the safety, maneuver ability near sea wave, and economics of the wig flying over sea waves

    研究地效翼在風浪擾動氣流場中掠海飛行的非定常氣動力問題，對于高性能地效翼船的設計，特別是對于提高地效翼船在風浪中飛行的安全性，操縱性以及經濟性都是十分重要的。
  8. 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。
  9. Electro - hydraulic servo loading system ( ehsls ) is an important simulation system in hard ware - in - loop flight simulation laboratory, which can simulate aerodynamic loads acting on flight vehicle, such as missiles, planes. its performance of test is important on the design of flight vehicle

    電液伺服負載模擬器是半實物模擬試驗室中模擬飛行器在飛行中舵面所受空氣動力載荷的重要設備，它的試驗能力高低對飛行器設計起著重要作用。
  10. According to the measuremental data of the two ammunications, the anti - designed computation and analysis of aerodynamic characteristic, flight stability, exterior ballistic characteristic for the two ammunications are studied with the advanced methods of the exterior ballistics. using the monte calo algorithm, the statistic mathematical model about ammunication ' s intensity is established and the 1000 miter vertical target intensity and the fall intensity are discussed in detail for the two ammunications. the improval potential and the main technical approachs of these ammunication ' s exterior ballistic performances are presented by compositive optimal algorithm

    根據工廠對俄ak130艦炮彈藥的測繪數據，利用先進的外彈道數值分析方法對兩種彈藥的空氣動力特性、飛行穩定性特性、外彈道特徵量等進行了反設計計算分析；採用montecarlo方法，建立了艦炮彈藥密集度性能統計分析數學模型，對兩種彈藥的立靶密集度和地面密集度進行了詳細的計算分析；利用外彈道性能綜合優化設計方法對兩種彈藥的外彈道性能指標的改進潛力和主要技術途徑進行了分析。
  11. Using detailed computer simulations, its designers have arranged its orientation and aerodynamic exterior to accelerate the gale - force winds that blow over the pole and channel them underneath the station

    通過嚴密復雜的電腦模擬，設計師安排設計建築的方位和其空氣動力學外殼，讓強風加速吹過鋼筋柱使風力轉移到基地之下。
  12. Abstract : this paper introduces briefly the control principle of trajactory correction technique and analyzes the structures and application areas of several typical trajectory correction mechanisms such as paddle type ring and d - ring etc. moreover, it makes the aerodynamics simulation and dynamics simulation of trajectory correction mechanism as paddle type damping ring. the simulation result proves the correctness and feasibility of the design

    文摘:簡要介紹了彈道修正技術的控制原理；分析了槳式、 d型環等幾種典型彈道修正裝置的結構特點和應用范圍；並對其中的槳式阻尼環彈道修正裝置分別進行了空氣動力學模擬和運動學模擬，驗證了設計的可行性和正確性。
  13. The 4th generation fighters are designed to have the ability of supersonic cruise. stealth and supermaneuverability which is based on the high - tech achievements of various fields including advanced aerodynamics, modern control theory and so on. in order to achieve the air superiority in modern air combats

    為了在現代空戰環境和空戰方式下取得空中優勢，第四代戰斗機設計提出了超音速巡航、隱身、超機動性等設計目標，綜合了多學科先進技術，包括：先進的空氣動力學、控制理論、航空電子技術等。
  14. The design undertaken mainly from the following aspects : 1, mechanism ddesign : included the base and the joints : 2, trasmission mechanism design : adopted a synchronous toothelike transmission bell ; 3, balance system design : adopted springs and a brake and a lay air cylinder ; 4, design parameter and verify alculation ; 5, established motion equation by d - h method ; 6, simulated the motion locus by matlab software ; 7 ^ mapping out the part drawing or asesembly drawing

    本設計主要是從以下幾個方面入手： 1 、機構設計：包括底座和臂關節的設計； 2 、傳動機構設計：將驅動電機安裝在底座上，利用同步齒型帶、離合器傳遞手臂的動力；利用齒輪傳動帶動底座回轉； 3 、平衡系統設計：採用了彈簧平衡系統、電磁式制動器和單向延時氣缸； 4 、設計參數和校核計算； 5 、用d ? h法建立運動學方程； 6 、利用matlab軟體對手臂的運動空間進行模擬； 7 、利用autocad2000繪圖：包括零件圖和裝配圖。
  15. With fluid dynamic derived from marine mammals and subtle character lines stretching down the body ; the powerful imposing view of our canopy in flight is simply stunning

    為了營造出古代羅馬戰神盔甲的雄壯氣勢，極度誇張霸氣進氣口的設計，搭配腮狀進氣側孔，飛行時氣流直達動力核心，增強熱能疏散。
  16. 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
  17. Download our bulletin 16 pneumatic conveying concepts for an overview of pneumatic conveying applications and material handling equipment designed and manufactured by dynamic air

    要了解空氣動力設計製造的物料處理設備和氣動傳輸的實例，歡迎下載我們的「濃相氣動輸送系統」簡介。
  18. The effective optimization design programs for different cases are developed by integrating the following several aspects which involves the flow analysis, adjoint equation solution, gradient solution, optimal arithmetic and grid generation. some practical design tests for airfoil and wing show that the continuous adjoint approach is very effective and useful method for aerodynamic optimization design. at the same time, we have done the research of aerodynamic optimum design for airfoils by using navier - stokes equations

    （ 4 ）研究了基於控制理論和三維navier一stokes方程的優化設計理論，在計算坐標下詳細推導了該優化設計理論，得到了計算坐標系下描述的共扼方程數學描述形式，並以給定目標壓力分佈的氣動反設計為例，導出了相應的共扼方程邊界條件，以及關鍵的梯度求解具體表達形式，為了求解方便，把計算空間上描述共扼方程表達形式變換到物理空間中進行描述，通過與ns方程表達形式對比分析，最終給出了一種直觀的共轆方程表達方式。
  19. We generated its grid surface on the fuselage or missile body according to the geometry projection relation between aerodynamic components and the bilinear interpolation approach. finally, we successfully developed a new algebra grid generation technique in virtue of the improved four - boundary interpolation. in this thesis, we put emphasis on the researches of aerodynamic inverse design and drag reduction questions for airfoil and wing using euler equations and control theory proposed by jameson

    （ 2 ）進行了應用控制理論和二維歐拉方程的翼型氣動反設計，以及有升力約束情形下翼型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的數學形式，並給出了相應的梯度求解公式形式，研究發展了共軛方程及梯度的數值求解方法，成功進行了多個翼型的反設計和減阻問題研究。
  20. Thus, the disc design method offers an efficient approach to aerodynamic design

    因此，本文的disc設計法為氣動力設計提供了一個行之有效的方法。
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