飛機構型 的英文怎麼說

中文拼音 [fēijīgòuxíng]
飛機構型 英文
aircraft configuration
  • 飛 : Ⅰ動詞1 （鳥、蟲等在空中活動） fly; flit 2 （利用動力機械在空中行動） fly 3 （在空中飄浮遊動） fly...
  • 機 : machineengine
  • 構 : Ⅰ動詞1 （構造; 組合） construct; form; compose 2 （結成） fabricate; make up 3 （建造; 架屋） bui...
  • 飛機 : airplane; plane; aeroplane; kite; bird; aircraft
  • 構型 : [物理化學] （分子空間結構） configuration構型分析 [物理化學] conformational analysis; 構型作用 [...
  1. This research work on bird striking has a long history and already got plentiful achievemellts in theories and experiments, howevef, still a long way no doubt waits to go for sophisticated research work on it more detailed to apply to airframe engineering quantitatively in combination wth the technical reformation of the birdstrike experimelltal system in our laboratory, this thesis deeply studies and analyses the numerica1 computation and simulation methods to birdstrike dynamic response problem based on finite - elemefit - method ( fem ) numerical emulation and modem large - scale scientfic computation software

    本文結合我公司鳥撞實驗體系技術改造項目，應用有限元數值計算模擬技術及現代大型科學計算工具，對鳥體撞擊飛機風擋結構的動力學響應問題進行了系統學習與研究探討，初步掌握了科學計算方法，獲得了計算模擬的實踐經驗，為今後深入應用大型科學計算手段進行撞擊類科學問題的研究以及深入應用於工程實踐奠定了強有力的工作基礎。
  2. In summary the major research work in this thesis can be drawn as follows : 1. the techncal data and research information from woridwide aviation history about bird striking to airframe have been collected and reviewed more carefully the evolutions of bird striking load models and fem numerical compatation methods to bird strike also have been sununarized. this informational research makes great help to position further thesis work scientifically 2

    本文研究工作可歸納總結為以下三個方面： 1 、較全面整理綜述了鳥體撞擊飛機結構在國內外航空史上的技術資料以及鳥撞問題理論與工程研究的歷史沿革，總結了撞擊載荷研究模型、有限元數值計算方法的發展歷程等，明確了本文研究工作的科學定位。
  3. All of the design 、 produce and management cadreman are came from large well - known automobile and aircraft corporation 、 welding machine manufacture company 、 japan well - knownwelding jig professional design corporation ; 16 professional jig designer with abundant experience and advanced design hardware and software ; comeplete various machining facility ; integrated organization

    公司設計、生產、管理骨幹均來自於國內大型知名汽車飛機企業、焊裝設備生產廠家、日本知各焊裝夾具專業設計公司；擁有專業夾具設計人員20餘名，具備豐富的經驗和先進的設計手段，各類加工設備齊全，組織機構完善。
  4. It is not only created favorable conditions for the city s reconstruction, industrial shifting, optimum allocation of resources and restructuring of beijing, but also provides the state - own enterprises with such important base for their changes, reforms and or restructuring. here is a galaxy of multi - national companies and of new and hi - tech enterprises and of science and technology research institutions. it is considered as the hope of the trans - centurial economic soaring and new economic focus of the capital

    它不但為北京市城市改造，產業轉移，資源優化配置和產業結構調整創造了十分有利的條件，也為國有大中型企業的改革改組改造提供了重要基地，是著名的跨國公司高新技術企業科研機構的薈萃之地，是北京跨世紀經濟騰飛的希望所在，是北京經濟發展新的增長點。
  5. Although aircraft designers and engineers continued to employ wing - warping techniques for years afterward ( especially on early monoplanes such as the bleriot xi ), ever faster flight speeds eventually led them to beef up wing structures to resist the resulting stresses

    雖然其後許多年間，飛機設計師和工程師仍繼續採用翹曲機翼設計（尤其是布雷修xi型等早期單翼機） ，但由於飛行速度不斷提升，終于迫使他們加強機翼結構，以承擔所增加的應力。
  6. Pulp, boxes, frames, general construction, woodwoking ( flooring, siding, ceiling, doors, blinds, etc. ), airplanes, musical istruments ( especially sounding boards of pianos ), cabinets, ships, railroad coaches, furniture, wares, kegs and ladders

    紙漿材、箱盒材、線條、地板、天花板、木門、窗? 、模型飛機、樂器構造材（如鋼琴響板） 、櫥櫃、造船材、傢俱等。
  7. 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。
  8. In this system, we use a computer model to simulate the true aeromodelling ' s wing, and then we simulate the state of aeromodelling ' s wing under the real flying conditions by computer. moreover, we simulate two fault - models for wing ' s model, and then we get the state ' s date of wing ' s model structure when the two faults are happening

    在建立這個健康監控系統中我們採用在計算機上建立的模型來模擬航模飛機的機翼並在計算機上模擬了飛機在真實情況下的飛行受力狀態，接著我們在計算機上針對機翼模型模擬了二個故障，並計算出了在這二個故障發生時機翼結構的受力狀況。
  9. In this paper at last. the localized anti - collapsing effect of the cave depot of single aircraft under the explosive load is calculated and analyzed. the explosive result shows that 3d ripped steel plate and ribbed shell structure are effective to raise the capacity of anti - collapsing of the protective structures

    對飛機單機掩蔽庫工程在爆炸荷載作用下，抗局部震塌效應進行了計算分析，模擬直接命中的爆炸試驗結果表明：鋼筋混凝土內襯三維波紋鋼板組成拱型復合結構，是提高防護結構抗震塌破壞的一種十分有效的措施。
  10. It also analyzed the whole stress of the ribbed shell structure under the explosive load. the analytic result keeps well with that of the dynamic response of 6. 8kg tnt. it shows that this analytic method in this paper is feasible for the design and inspection of cave depot of single aircraft

    通過理論計算與6 . 8kgtnt裝藥爆炸時的動力響應實測比較，兩者數值吻合很好，表明本文計算分析方法是可行的。為鋼板-混凝土拱型復合結構的設計與檢驗提供了理論基礎，為飛機單機掩蔽庫工程的設計檢驗提供了一條可行的計算分析方法。
  11. When solving the tna problem based on fleet balance application, a flight pairing network model is build, by which the primary problem transferred to a directed path decomposition problem to minimize target function, and a simulated annealing algorithm is constructed

    在解決使飛機均衡使用的飛機排班問題時，本文利用航班節的網路模型將原問題轉化為一個使目標函數最小的航班節編組問題，在此基礎上構造了一個模擬退火演算法。
  12. Finally, the thesis developed 3d animation flight simulation platform for helicopter using opengl in visual c + +. and the 3d terrain and helicopter model are constructed. the simulation of two typical maneuver ( s maneuver flight and bopup - bopdown ) and terrain following shows that the fight control system of attack helicopter is improved by the realistic optical impact

    本文最後在vc環境下用opengl開發了直升機三維動畫模擬平臺，構造了三維地形和直升機模型，模擬了直升機做蛇形機動、急躍升急躍降、地形跟隨等機動飛行，通過逼真的視覺效果驗證了飛控系統的正確性。
  13. The modern unmanned helicopter flight control system is generally composed of the flight control computer, the servo driving mechanism, the sensor, and the ground monitor control system etc. in this thesis the research to the helicopter flight characteristics was conducted at first, and its flight dynamic model was preliminary discussed, especially the mathematic model under hung - stop condition was formulated and the algorithm of the controller was designed in detail

    現代無人直升機飛行控制系統一般由飛行控制計算機、伺服驅動機構、傳感器、地面監測控制等分系統組成。本文首先對直升機的飛行特性進行了研究，並且對飛行動力數學模型做了初步探討，尤其對在懸停狀態下的數學模型做了較為詳盡的公式推導和控制器的演算法設計。
  14. Focusing on the flight control computer system of some type of airplane, this paper first analyzes the advantage and disadvantage of the structures of many kinds of fault tolerant flight control computer systems and their ability in tolerating fault, followed by summarizing the key design technology. the dual similar redundancy fault tolerant computer system is brought forward as the design scheme for the required flight control computer. also brought forward is the particular system design

    本文以某型號飛機飛控計算機系統為研究對象，首先分析了各種類型容錯飛控計算機體系結構的優缺點及容錯能力，總結了容錯計算機系統設計的關鍵技術，然後提出了二模相似余度容錯飛控計算機系統設計方案，詳細設計了以motorola公司生產的先進powerpc740微處理器為核心處理器、以高性能的國際標準化通用vme總線為內總線的交叉通道通信容錯計算機系統。
  15. Model aircraft are flying or non - flying models of existing or imaginary aircraft, often scaled down versions of full size planes, using materials such as balsa wood, foam and fiberglass

    模型飛機的樣式有些是現有的有些是虛構的，通常是大型飛機縮減過后的模型居多，大部分使用浮筒木筏木頭，泡沫和玻璃纖維。
  16. Up to now, the dynamic simulation for aircraft landing and taxiing by the software adams based on the full aircraft model has not been found. in this paper, dynamic analysis for landing gear landing and taxiing is conducted for a large transportation aircraft with a post nose landing gear and two truck main landing gears. a dynamic analysis model of the landing gear and a full - scale aircraft model used in the simulation are developed by applying dynamics basic theory

    論文以我國某大型運輸飛機起落架為研究對象，應用動力學基本原理，基於adams aircraft模塊建立了起落架著陸動態性能分析模型以及由機身、前起落架緩沖支柱、前起落架機輪、主起落架緩沖支柱和主起落架機輪五個子系統構成的全機模型，進行落震、全機著陸與滑跑動力學模擬。
  17. 3 ) definition of input designer concept for flight control system ( fcs ). a input designer was successfully constructed which can provide a effect almost the same as directly control over aerodynamic control surface through the careful design of inputs of fcs. this input design concept is very important for in - service aircraft upgrade where change of the original pcs is not allowed

    3 ）提出了飛控系統輸入設計概念，並成功地構建了飛控輸入設計器，能夠在不改變原飛控系統條件下有效地提高舵面控制能力，獲得接近直接舵面操縱的性能，對于現役飛機改進、改型中飛機運動自動控制系統的設計具有非常重要的意義。
  18. Abstract : problems existed in using combined jig to assemble airplane are analyzed and the principle of how to select integral structure configuration of jig for airplane assembly is introduced. correct setting of three supporting points of the integral jig is discussed in the paper as well

    文摘:分析歸納了飛機裝配中採用組合式型架存在的問題；介紹了飛機裝配中型架總體結構形式的選擇原則；討論了整體式型架3個支承點應如何正確設置。
  19. According to the requirements of propeller aerocraft model test in wind tunnel, specifications of the driven motor is presented by aerodynamic analysis, and a short - term operated high power density three - phase induction motor is developed with reasonably designing the motor, such as electromagnetism load, heat checkout and high - efficiency heat exchanger

    摘要針對螺旋槳飛機模型帶動力風洞實驗要求，通過氣動性能分析提出驅動電機的技術指標，在滿足結構約束的條件下，通過合理設計電機的電磁負荷、校核發熱、採用高效冷卻裝置等，研製出短時工作制高功率密度三相異步電機。
  20. The effects of such elements as primary flow total pressure, flow rate, degree of fuel rich, nozzle structure, flying speed and secondary combustion on ejecting mode performance were researched. it was found that thrust augmentation can be achieved on the condition that the flying mach number is above 0. 7. to deeply analyze thrust augmentation mechanism in low speed range, the research was further continued by changing secondary combustion organization and aft - body configuration

    研究了一次流總壓、流量、富燃程度、噴管結構、二次流來流速度、二次燃燒組織對引射模態性能的影響，發現實驗樣機構型在0 . 7ma以上的飛行條件下可以獲得推力增強，而在0 . 7ma以下無推力增強。
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