飛行基本原理 的英文怎麼說

中文拼音 [fēihángjīběnyuánlǐ]
飛行基本原理 英文
aircraft general knowledge
  • 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...
  • 行 : 行Ⅰ名詞1 （行列） line; row 2 （排行） seniority among brothers and sisters:你行幾? 我行三。where...
  • 本 : i 名詞1 （草木的莖或根）stem or root of plants 2 （事物的根源）foundation; origin; basis 3 （本錢...
  • 原 : Ⅰ形容詞1 （最初的; 原來的） primary; original; former 2 （沒有加工的） unprocessed; raw Ⅱ動詞（原...
  • 理 : Ⅰ名詞1 （物質組織的條紋） texture; grain （in wood skin etc ） 2 （道理;事理） reason; logic; tru...
  • 飛行 : flight; flying; aviate; voyage; volitate; hop
  1. This paper introduced a flight information ground processing system. the basic operation principle of the system and the prob - lems and solving case that encountered in the designing are expatiated

    介紹了一種飛行信息地面處理系統。闡述了系統的基本工作原理以及在設計開發過程中遇到的難題和解決方案。
  2. Secondly, paper introduces the composition structure and the manufacture craft characteristic of airplanes, describes the structure and the main assembly process and the assembly characteristic of the n # fuel tank section, points out the assembly accuracy control of the n # fuel tank section. thirdly, paper analyses in detail problems which exist in the current riveted assembly of the n # fuel tank section, proposes the improve measures against the existent problems. finally, paper forecasts in theory the positive effect that the new plan will bring, introduces the practical result after approval test, analyses the differences of both

    具體做了以下幾方面工作:第一，詳細闡述了工作研究的基本原理;第二，介紹了飛機的組成結構、飛機製造工藝的特點、 n #油箱段的主要結構、 n #油箱段的主要裝配過程、 n #油箱段的裝配作業特點和n #油箱段的裝配準確度的控制方法;第三，具體分析了n #油箱段鉚接裝配生產線現行作業中存在的問題，針對存在的問題，提出了具體的改進建議，並形成了新的改進方案;第四，從理論上預測了新方案將會帶來的積極效果，介紹了新方案在現場試驗驗證的實際結果，並對兩者之間存在的差異進行了對比分析與研究。
  3. 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。
  4. It has been maked for immediate and statistical analysis that the calculation about the work order parameter of the base - bleed - rocket is calculated in the taguchi method, its influencing trend is bring out in the open, the theoretical base is settled for confirming the greatest combination about the work order parameter of the base - bleed - rocket. the multi - objectile optimal design model is established that the indexes have been taked into account first and synthetically, such as physical parameter range lethality power strength and flight stability and so on, the program is compiled and the example is calculated. the true worth of the theoretical work in this paper is validated by flight experimentation of 130mm hybrid base - bleed - rocket extended - range principium projectile

    本文進行了底排?火箭復合增程彈工作時序參數正交試驗設計的直觀分析與方差分析，揭示了每個參數對射程計算的影響趨勢，為進一步確定底排?火箭工作時序參數值的最佳匹配組合奠定了理論基礎；建立了底排?火箭復合增程彈多目標優化設計模型，該模型首次綜合考慮了底排?火箭復合增程彈的結構特徵參量、結構強度性能、飛行穩定性、威力性能和射程指標，編制了相應的分析程序，進行了算例計算；完成了130mm底排?火箭復合增程原理樣彈的結構設計與飛行試驗，其試驗結果驗證了本文理論研究工作的實際應用價值。
  5. 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。
  6. Now, it is worthwhile to conduct the research on the ground load of landing gear with multi - wheels and multi - struts according to the basic theories of the mechanics, the dynamics analysis model of the full - aircraft during its landing process is established in this paper

    本文首先以某多輪多支柱飛機的起落架作為研究對象，應用動力學基本原理，建立了全機的著陸動力學模型。然後，通過利用大型動力學模擬軟體adams對該飛機進行了對稱著陸模擬，並對模擬結果進行了對比分析。
  7. In the lectures, representatives from the hong kong radio control soaring society, the hong kong paragliding association and the hong kong observatory have introduced to the participants the basic principles and skills of radio - controlled gliding and paragliding and also the weather conditions that would help the glider pilots take off and stay longer in the sky

    在講座中，香港遙控滑翔飛行協會、香港滑翔傘協會和天文臺的代表向參與講座的人士介紹了遙控滑翔機和滑翔傘的基本飛行原理和技術，以及有利滑翔飛行員起飛及於空中逗留更長時間的相關天氣條件。
  8. On the basis of these, a simplified iced aerodynamics model is established, describes the effects of aircraft icing on aerodynamic parameters. main principle and implement method of iced aircraft envelope protection system are proposed. after ascertain iced aircraft envelope, for pilot and autopilot, open - loop and close - loop aircraft envelope protection control law respective designed, ensure the aircraft will efficiently follow the flight path specified by the pilot in the safe - flight envelope

    在此基礎上，建立了簡化的飛機結冰氣動模型，以描述結冰對氣動參數的影響;給出了結冰飛行包線保護系統的基本原理及實現方法，在計算確定結冰飛行包線后，對於人工駕駛、自動駕駛飛行兩種情況，分別設計了開環、閉環飛行包線保護控制律，保證飛機在安全飛行包線內沿著預定的航線飛行。
  9. But the variation of its aerodynamic forces will induce flapping motion and produce the cyclic pitch on the main rotor blades by the bell mixing mechanism. in order to study the effect of bell - hiller stabilizer bar on helicopter stability and control, this paper first analyze the function and the principles, give the flapping equation and a flight dynamic model with bell - hiller stabilizer bar. and then works over the stability and control of uav r - 50 in hover and cruise condition, and analyzed the influence from parameters of the bar to it

    為了深入研究希勒伺服旋翼對直升機穩定性和操縱性的影響，本文首先分析了希勒伺服旋翼的功能和工作原理，推導了伺服旋翼的揮舞運動方程，建立了帶有希勒伺服旋翼直升機的飛行動力學模型，然後以yamahar - 50無人直升機為例，分析該直升機在懸停和前飛時的平衡、穩定性和操縱性，在此基礎上進一步研究希勒伺服旋翼設計參數變化對直升機穩定性和操縱性的影響。
  10. In paper, reaching the aim, firstly, we have researched thorough about symbol recognition and theory understanding relative theory and technology, and basing on those theory and technology, we adopt the based global characteristic symbol recognition and engineering drawing understanding algorithm which can automatic convert the vectorgraph which doesn ’ t include the relative physical information into the vectorgraph which includes the relative physical information. secondly, researching about the 2d computer animation technology and combine the cbt system, we have presented the new path animation model which include the union path description, animation pattern and time - velocity and time ? distance parts

    為達到上述目標，本文首先對目前圖形符號識別技術進行系統的、較深入的分析，結合民航飛機原理圖特點採用基於全局特徵的符號識別演算法對原理圖進行符號處理，並以此為基礎改進了基於圖的方法和全局知識的語義分析方法相結合的原理圖理解演算法，可將無序的矢量圖轉化成高層的知識表示，為動畫製作提供素材，為后續的電路完整性檢測及動畫自動播放提供相應的知識支持。
  11. That is to say, the test system can be connected easily with other systems and be installded with the setup softwares by using socket communication. what is more, the scheme that the thesis mentioned just uses adapted ieee1588 to synchronize the collection machines ? network nodes, because there is no need to implement the whole ieee1588 in the simple enviroment, and an extend manner to implement the whole protocol is discussed in the master / slave communication

    本文對飛機測試系統外總線進行綜合分析后，並在理解了ieee1588的時鐘同步原理的基礎上，對ieee1588進行了裁減，並將裁減后的ieee1588協議應用到各數據採集器的同步策略中，使各採集器之間能達到精確的時間同步，進一步提出了在主/從方式的測試系統中實現完整ieee1588的擴充同步方案。
  12. With above principles, take domestic and abroad research works as foundation, this paper try to improve the degree of integration and automatization of aircraft based on currently available technology and equipment. the study focus on how to realize auto - flight and auto - attack through the integration of flight control, fire control and propulsion control system, a satisfied result wold be feasible system integration schemas that could improve the mission performance and enhance the aircraft combat automation

    基於以上考慮，本文參考國內外已經完成的工作，致力於在現有技術基礎上提高飛機綜合化、自動化程度，研究通過飛行、推進、火控等系統的綜合實現自動飛行、自動攻擊的原理、演算法，提供可以工程應用的系統綜合方案。
  13. Finally, this dissertation reviews the federation security and the next works need to do. in practice, this dissertation has creatively finished the following works : to derive and expand the theory and method for simulation development based on hla ; to develop the object model developing tool kd - omdt that is complied with dmso hla omt specification and will be updated to comply with ieee 1516. 2 soon ; to design and guide to implement the object model library ( oml ) shared by internet net ; to modify a large scale flight analysis and training system with hla ; to use the case tool rational rose to develop hla simulation system ; to design and guide to implement a automatic tool used to develop hla simulation with matlab / simulink

    特別地，本文在實踐中創新性地完成了以下工作：系統地提煉、擴展了基於hla進行模擬應用開發的原理與方法；開發了具有自主版權、符合dmsohlaomtv1 . 3規范的對象模型開發工具kdomdt ，向ieee1516 . 2的移植工作正在進行當中；設計並指導實現了基於internet網共享的hla對象模型庫（ oml ） ；成功地採用hla對某大型飛行分析訓練系統進行了改造；成功地將case工具rationalrose軟體應用於hla模擬系統的開發；設計並指導實現了基於matlab simulink開發hla模擬應用的自動化工具。
  14. We have finished the semi - phsical simulation on the single axis turfing platform, which included on board prototype computer, optic fiber gyro and reocaon wheel which saturation chamaeristic has been taken into account

    本文採用瞬時歐拉軸控制演算法，在星載計算機原理樣機的基礎上，考慮反作用飛輪的飽和特性，根據所選擇的反作用飛輪和光纖陀螺，在單軸氣浮轉臺上進行半實物模擬驗證。
  15. Abstract : a type of pilotless target aircraft flight control system is introduced. the function and basic compose and autopilot control regular and engine control principle and recovery control scheme of the flight control system are discussed

    文摘:介紹了無人駕駛靶機的飛行控制系統，詳細討論了系統的功能、基本組成、自動駕駛儀控制規律、發動機控制原理、回收控制方案及系統軟體設計等。
  16. The result shows that this kind of adaptive control method has robust performance to a great extent because of the special dynamic compensation for external disturbance in these two systems. lastly, this dissertation introduces the main development techniques used for exploring distributed 3d flight platform which can validate advanced flight control laws in theory and method. based on windows 2000 / xp os ( operation system ), it synthetically applies real - time simulation arithmetic of control system, oop ( object oriented program ) development technique, tcp / ip protocol - based net - communication technique and api development technique of 3d virtual reality opengl to exploring the distributed simulation platform with friendly a

    本文對于驗證先進飛行控制理論的分散式三維飛行模擬平臺主要開發技術進行了原理和方法上的介紹，文中在基於windows2000 xp操作系統下，綜合運用了控制系統實時模擬演算法、面向對象的軟體oop開發技術、基於tcp ip協議的網路通訊技術及三維虛擬現實opengl的api開發技術，在vc + +應用程序框架的范圍內，開發了具有友好互動式三維界面的分散式模擬平臺，該平臺除了用於先進飛行控制理論的實南京航空航天大學博士學位論文時程序驗證之外，也可以用於航空院校的飛行控制系統教學實踐和飛行訓練的課程，由於開發這一平臺並不需要大量的資金投入，因此具有非常廣泛的應用前景。
  17. On the base of the soft about the deformation of aerodynamic configuration of mav, the advanced controlling technique of the deformation o f aerodynamic configuration about the prototype mav will be explored. based on the characteristic of micro air vehicle, this paper abstracted the aerodynamic evaluation mathematics models, developed a aerodynamic engineering estimation program, all kinds of aerodynamic configuration was compared and analyzed, found the perfect configuration and got the prototype of mav. abstracted the model about the deformation of aerodynamic configuration on base of the method of vortex lattice, developed the program for researching the performance of the deformation of aerodynamic configuration

    本文針對mav的具體特點，抽象出mav的氣動工程計算數學模型，建立起氣動工程估算環境，對各種氣動布局進行了氣動特性比較分析與綜合，尋求出理想的mav氣動布局方案並提出mav原型機，抽象出基於渦格法的氣動外形形變的數學模型，建立起氣動外形形變性能研究環境，探討新型的飛行控制方法和氣動力控制策略，在得出氣動外形形變模型的初始方案后，對其進行進一步的優化，最後得出理想的氣動外形形變執行機構組合陣列。
  18. Firstly, i present a new structure of torque measurement ? rating torque sensor. secondly, introduce the fundamental principle of the dynamic torque. and then bring forward new methods of measuring flywheel moment and acceleration, which has been proved not only by theory, but also by experiment

    本文首先提出了轉矩測量的一種新結構? ?光柵靜態（平均）轉矩測量傳感器；然後闡述了動態轉矩測量的基本原理；接著提出了新的飛輪矩與加速度測量方法，並對其進行了理論推導及實驗證明；最後對提出的通用轉矩測量系統進行了硬體、軟體上的設計。
  19. Differential gps has become the prime and essential positioning system for many applications. this paper introduces the principles of the differential global position systems. clarifies the arithmetic of the pseudo - range dgps. by the high - class differential reference station receiver called javad receiver which being used in our laboratory now, some necessary work has been done : data digging from javad receiver ; data decoding, data encoding, and data transmission through the net and pc serial port ; further more, the gps receiver interface language has been analyzed to control differential reference station receiver

    因此，差分gps技術（ dgps ）應運而生，並得到飛速發展，其市場前景看好。 dgps在許多定位應用中已經成為重要的定位系統，本文論述了差分gps的原理，闡明了偽距差分的基本原理與演算法：在實踐上針對實驗室現有的比較先進的javad差分參考臺進行了偽距差分修正量數據的提取、數據解碼、數據編碼、數據的網上傳輸。
  20. Detailed analyses the algorithm of weight parameter. introduced the different algorithms of digital beam forming ( dbf ) and direction of arrival ( doa ). based on multi - aircraft tracking telemetry and command system, detailed introduce gradient algorithm pattern which follows the lms error norm

    介紹了數字波束形成的基本原理，詳細介紹了波束形成的權值演算法，研究了數字波束形成以及波達方向確定的各種演算法，結合多飛行器測控系統詳細介紹了在最小均方誤差準則下的梯度演算法模型。
分享友人
分享到 Line

分享到臉書