飛機機動點 的英文怎麼說

中文拼音 [fēijījīdòngdiǎn]
飛機機動點 英文
airplane maneuver point
  • 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
  • 點 : Ⅰ名詞1 （液體的小滴） drop （of liquid） 2 （細小的痕跡） spot; dot; speck 3 （漢字的筆畫「、」）...
  • 飛機 : airplane; plane; aeroplane; kite; bird; aircraft
  • 機動 : 1 （利用機器開動的） motor driven; motorized2 （權宜; 靈活） flexible; expedient; mobile; manoeuv...
  1. This thesis firstly introduces new demands of aerial product logistics support under high - tech war and some defects of traditional logistics support, and puts forward a kind of system model of aerial product logistics support following data - sharing of cals, and emphasizes detm. secondly it sets forth application of step and xml in the ietm, researchs conversion of xml schema and relation schema, and simply researchs mapping of xml and express. afterword, a based - xml framework of info - transfer between different platform are presented, according to this framework, the author establish a archetypal system of helicopter information query system based xml and dbms

    本文首先介紹了現代高科技戰爭條件下對航空產品維修保障的新要求，概述了傳統的後勤保障技術的不足，遵循cals的數據共享的理念，提出了航空產品維修保障系統模型，重點研究了互動式電子技術手冊；接著分析了step標準和xml技術在製作互動式電子技術手冊中的應用，重點研究了肌模式和關系模式之間的相互轉換，初步研究了xml和express語言之間的映射關系；然後，提出了基於xml的一種解決航空產品信息跨平臺傳遞的解決方案，給出了該方案的具體實現流程和詳細的通訊協議，並開發了基於xul和數據庫的某型號直升飛機的信息查詢原型系統。
  2. Using coordinate transformation method, the formula of imv on every point of image plane was deduced, and it included almost all motorial factors : the flight velocity of aircraft, roll, pitch, yaw, camera ' s scan and so on. thus, it is a precise formula, and it is also applied to frame cameras and push _ room cameras with array ccd

    利用坐標系變換的方法可推出像面上各點的像移速度公式，該公式包含了幾乎所有的運動因素：飛機的前向飛行、飛機的姿態角變化、相機自身的擺掃運動等等，是精確的像移速度公式。本公式同樣適用於畫幅式航空相機和線陣ccd推掃型航空相機。
  3. Tilt - rotor aircraft combine the vertical takeoff and landing ( vtol ) capability of helicopters with the high speed performance of turboprop airplanes. located at the tips of the wing, the prop - rotors act as helicopter rotors when flying vertically and as airplane propellers in cruising flight

    傾轉旋翼飛機翼尖安裝可以傾轉的發動機短艙和旋翼系統，可以在飛行中根據需要在固定翼模式和直升機模式之間轉換，充分發揮直升機垂直起降、懸停及固定翼飛機高速巡航的優點。
  4. The thesis roots in the item supported by " fifteen " aviation funds, - new type aeronautic linear dc motor ( ldcm ), study its classes characteristics and work principle, mainly researches the drive and control technique of aeronautic linear dc step motor ( ldcsm ) using in emergency discharging oil valve on airplane

    本文源於「十五」航空支撐基金項目-新型航空用直線直流電動機。論文研究了直線直流電動機的分類、特點及其工作原理，重點針對飛機應急放油閥用航空直線直流步進電動機驅動控制技術進行了研究。
  5. Armoured ignition cable ends for piston engined aircraft

    飛機活塞發動機用鎧裝點火電纜端頭
  6. Load features of flight conditions on dynamic component of helicopter

    直升機某動部件飛行狀態的載荷分佈特點研究
  7. According to the characteristics of the load on the canopy, the method for measuring the load on the canopy with a pressure sensor is presented, and then the flight measurement of the load spectrum of the canopy is realized for the first time

    根據實測活動艙蓋載荷曲線特點，提出了任務類型劃分方法，建立了活動艙蓋載荷譜數據統計方法和載荷譜編制方法，並依此編制出k8飛機活動艙蓋載荷譜。
  8. As to the modelling of integrated flight / propulsion system, this paper mainly investigated and the modelling methods of flight kinetics and propulsion system thermodynamics, building up the real - time models of body kinetics. then we integrated the component - level thermodynamics model of engine, solved the problem of matching of initial points in the integrated simulation of flight / engine and the interactive parts of flight system and propulsion system

    對于綜合飛行/推進系統建模，本文主要研究的是飛行動力學和推進系統熱力學的建模方法，建立了飛機動力學實時模擬模型。並結合前人已建立的發動機部件級熱力學模型，本課題在解決了飛機/發動機綜合模擬中的起始點匹配問題的基礎上，完成飛行系統和推進系統的交互部分，最終建立飛行/發動機綜合實時模擬模型。
  9. Both advantages of rocket engine and air - breathing engine are integrated into one kind of propulsion system, called rocket - based - combined - cycle ( rbcc ), which has multiple operating woke modes, including ejecting, subsonic combustion, supersonic combustion and rocket mode, with each mode operating at varying flying stage. rbcc has prominent potential of high efficiency and low cost, and so it is recognized as an advanced propulsion system of future single - stage - to - orbit reusable spacecraft and hipper - sonic missile. it has been broadly investigated in foreign countries and has been progressed into small and full - scale flying stage

    火箭基組合動力循環（ rbcc ， rocketbasedcombinedcycle ）將傳統的火箭發動機和吸氣式發動機的優點集中組合到一個具有多種工作模態（包括引射、亞燃、超燃及火箭模態）的發動機里，在不同的飛行階段啟用不同的工作模態，因此具有大幅提高航天推進系統經濟性與高效性的潛在優勢，並可能發展成為下一代單級可重復使用航天器以及高超聲速導彈武器的動力系統。
  10. A couple statements i want to make before we open it up is, one, contrary to some releases, this aircraft was straight and steady, holding altitude, heading away from hainan island on auto - pilot when the accident occurred

    在我們接受提問之前我想作兩點聲明，一，與一些報導所說的相反，在事故發生的時候，這架飛機是在直線平穩飛行，高度固定，處于自動駕駛飛行狀態，向背離海南島的方向飛行。
  11. Compared with general aircrafts and ships, the wing - in - ground air vehicle features high aerodynamic efficiency, safety, high speed, comprehensive use and potential development toward huge vehicle of thousands tons

    地效飛行器與一般的飛機和船舶相比，具有氣動效率高、安全性好、速度快、可用作多方面的執行任務的交通工具，能向幾千噸位的大型化發展等優勢特點。
  12. This dissertation presents how to use the ultrasonic motor as an actuator to suppress the flutter of a two - dimensional airfoil section with a control surface. the ultrasonic motor, which features simple structure, high torque at low speed, small size, low weight and no electromagnetic contamination, is a promising actuator for the flutter suppression of small aircraft

    超聲電機以其結構簡單緊湊、轉矩/質量比大、低速大扭矩、直接驅動，動態響應快、斷電自鎖和不產生磁場且不受外界磁場干擾等優點，有望成為一種非常有前途的作動器，用於小型飛機的機翼顫振主動抑制。
  13. Upon above advantage, we can realise that the airboat is very suitalbe for every advertising company and enterprises, low cost, high efficiency, it brings the commercial advertising from the groung to the sky, from the static to moving, from silence to soundable, the shape of streamline is adopted to have very good ability of anti winding, stable flying and agility, it can take off vertically, forwarding or backwarding, presenting a fully new carrier to advertising circles, becoming a focus of people in the world

    綜合以上的優點不難看出，遙控飛艇非常的適用於各廣告公司，各種企業購買使用，成本低，見效快，它將商業廣告從地面發展到空中，由靜態變為動態，由無聲變有聲，遙控飛艇採用流線外型，氣動性能好，抗風能力強，飛行平穩，機動靈活，可垂直起落，俯沖爬升，前進後退，空中懸停，拋撒資料，施放彩色煙霧，空中攝影攝像等，向廣告界展示了一個新穎的廣告載體。
  14. Furthermore, because rotors are mounted on the tips of the wing, the rotor / pylon / wing aerodynamic interactions are also included in the model. such factors reflect the unsteady and nonlinear characteristics in the model

    此外，傾轉旋翼飛機的旋翼安裝在翼尖，旋翼/發動機短艙/機翼之間的氣動干擾是建模的一個難點。
  15. Abstract : approximate methods for calculating aerodynamic heating rates on space shuttles are discussed. various methods are given for predicting the heating rate at axisymmetric stagnation points, general three dimensional stagnationpoints and the leading edge stagnation point of wings. numerous laminar and turbulent heating techniques for flat plates and cones are analyzed and compared. a brief review of some methods is presented to predict heating rate for winward centerline and lateral direction off the symmetry plane. the results show that the methods are simpler and can guarantee enought precision for predicting aerodynamic heating environment of space shuttles

    文摘:介紹了國內外預測航天飛機氣動加熱的工程計算方法.給出了軸對稱、非軸對稱和機翼前緣等各種外形駐點熱流密度的計算，分析和比較了平板、錐體的層流和湍流熱流密度計算的各種方法，概述了航天飛機迎風面中心線和離開中心線橫向熱流密度的計算.計算結果表明，本文方法用在航天飛機氣動熱環境初步設計中比較簡單並且有足夠精度
  16. This thesis combines artificial neural networks ( nn ) with adaptive inverse control ( nnai ) on the basis of analyzing their principle and characteristics, and applies them in the control of nonlinear system. an application in the design of automatic landing is shown

    本文在深入分析了神經網路和自適應逆方法的原理與特點的基礎上，將神經網路與自適應逆方法相結合，著重研究了將這種方法應用於非線性系統的控制問題，最後，用飛機自動著陸的過程，驗證了神經網路自適應逆方法的效果。
  17. Based on the mechanism of slipstream interaction, described in this thesis is firstly the interaction of the propeller slipstream with the wing 、 fuselage and horizontal tail. subsequently, the changes in lift 、 drag and pitching moment are derived, giving an engineering model for the prediction of the increments in the aerodynamic characteristics caused by the interference between the propeller slipstream and the other parts of aircraft. this method offers a powerful means to the calculation of the aerodynamic interaction between the propeller and the aircraft, providing reliable data for the design of and aerodynamic calculation on propeller - powered aircraft

    本文以滑流干擾的機理為出發點，研究了螺旋槳滑流與飛機機翼、機身、平尾組合體之間的相互影響，推導出滑流引起的飛機升力、阻力和俯仰力矩的變化，給出了滑流干擾對機體氣動特性影響的工程估算方法，為研究螺旋槳與飛機部件之間的相互干擾提供了有力的工具，為以螺旋槳發動機為動力的飛機的設計和氣動計算提供可靠的依據。
  18. Practice for octane rating naturally aspirated spark ignition aircraft engines

    測定自燃吸氣火花點火式飛機發動機燃料辛烷值的操作規程
  19. Standard practice for octane rating naturally aspirated spark ignition aircraft engines

    測定自然吸氣火花點火式飛機發動機燃料辛烷值的標準實施規范
  20. Standard practice for ground - based octane rating procedures for turbocharged supercharged spark ignition aircraft engines

    渦輪增壓增壓火花點火式飛機發動機的地面辛烷值測定的標準實施規程
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