in-flight conditions 中文意思是什麼

in-flight conditions 解釋
飛行條件
  • in : adv 1 朝里，向內，在內。 A coat with a furry side in有皮裡子的外衣。 Come in please 請進來。 The ...
  • flight : n 1 飛行，飛翔；（鷹對獵物的）追趕。2 （候鳥等的）遷徙；飛行的一群。3 （光陰）飛逝。4 （思想等的...
  • conditions : （旅遊合同中）條件或服務項目
  1. In order to make the terminal airspace moderated and consisted, and acquire the biggest capacity of airport, we must consider the influencing factors as many as possible, it is our final target to plan the airspace in beijing terminal unify. with the conditions that the current operation modes of parallel runway, approach and departure procedures and terminal airspace in beijing international airport, this article has analyzed the reasons of airspace congestion. this article also applies the theory of instrument flight procedure and utilizes the current facilities in beijing international airport. the design of flight procedures combining rnav procedures with instrument approach procedures may be accepted on some routes. it make the approach and departure procedure more effective, and increase the capacity of the airport more or less ; secondly, this article contrast the capacities of parallel runway in different methods under radar control, and make the conclusion that the parallel runway in dependent operation modes has the biggest capacity

    本文從目前首都機場平行跑道的運行方式、進離場程序、終端區空域的現狀入手，剖析了造成空域緊張的原因，應用儀表飛行程序設計的思想和原則，利用首都機場終端區現有的設施，某些航線可採用區域導航（ rnav ）程序與儀表進近程序相結合的飛行程序設計，優化了目前首都機場的進離場程序，在一定程度上增加了機場容量；其次，研究了雷達管制條件下平行跑道不同運行方式的容量對比，得出平行跑道獨立運行的容量最大，然後以這種這種運行方式，為首都機場設計出了平行跑道獨立運行的飛行程序；最後，分析北京終端區各機場空域對首都機場飛行程序安全、有效運行的制約因素，研究設計出了北京終端區規劃方案及規劃后的飛行程序和飛行方法，以達到增大機場的容量，適應未來航班量增加的需求。
  2. Based on the mathematical model developed by the paper, the trim calculations are carried out in the conditions that the example aircraft converts from helicopter to airplane mode in level flight with zero longitudinal acceleration and angular rate

    本文依據所建立的樣例機縱向動力學模型，假定飛機在給定高度平飛，縱向加速度和角加速度均為零，完成過渡模式下的動力學配平。
  3. The battle of borodino was not fought on a carefully picked and fortified position, with forces only slightly weaker on the russian side. after the loss of the shevardino redoubt, the russians fought on an open, almost unfortified position, with forces half the strength of the french, that is, in conditions in which it was not merely senseless to fight for ten hours and gain a drawn battle, but incredibly difficult to keep the army for three hours together from absolute rout and flight

    波羅底諾戰役並不是在一個選定的，設了防的陣地上進行的，也不是俄軍的兵力僅僅稍弱於敵軍，實際上俄國人由於失掉舍瓦爾金諾多面堡，不得不在一個開闊的，幾乎沒有防禦工事的地帶，兵力比法軍少一半的情況下迎接波羅底諾戰役，也就是說，在這樣的條件下，不僅戰斗十小時和打一場不分輸贏的戰役不可思議，就是堅持三小時而不使軍隊完全崩潰和逃遁也是不可思議的。
  4. To study the influence of this damper configuration to aeromechanical stability, some work has been done in this thesis. first, dynamic equation of the rotor - hub system was modeled with the generalized hamilton principle, which can be used to analyze the stability problem in different conditions like on - ground, hovering and flight. when fastening the fuselage, the model can also be used to analyze the stability problem of isolated rotor system

    為了研究這種新型布置減擺器對直升機穩定性的影響，本文所作研究工作如下:首先，本文利用廣義的hamilton原理建立了適用於不同狀態（地面、懸停和前飛）的旋翼/機體耦合系統的動力學模型，該模型中將機體固定可以用來分析孤立旋翼的穩定性問題。
  5. In most flight conditions it is desired to maintain the sideslip angle equal to zero.

    大多數飛行狀態都要求保持側滑角等於零。
  6. In chapter 5, the uh - 1 model rotor, the model rotor measured in the present work and the helicopter z - 8 rotor are taken as numerical examples, the calculations on rotor noise under different flight conditions are carried out for validation purposes

    應用該模型，分別以uh - 1模型旋翼、本文試驗的模型旋翼以及z - 8直升機旋翼為算例，對不同飛行條件下的旋翼氣動噪聲進行了計算，驗證了本文的計算方法。
  7. In chapter 5, a new dynamic wake model is developed by employing the rotor free - wake method in chapter 2, and is used to investigate the curve distortion during the conversion of tiltrotor aircraft between helicopter flight conditions and airplane flight conditions

    在第二章方法的基礎上，第五章建立一個傾轉旋翼動態尾跡模型，使用該模型對傾轉旋翼機傾轉過渡狀態的尾跡彎曲變形進行了研究，得出了一些結論。
  8. The aircraft load calculation implies determination of the loads acting on the aircraft structure for flight maneuvers, flight in turbulence, landing and ground handling conditions

    飛機的載荷計算就是確定飛機在機動飛行、突風飛行、著陸和地面操作過程中作用在飛機結構上的載荷。
  9. On the basis of this theory, the applications of the sdr structure of wideband and bandpass sampling in if ( intermediate frequency ) in flight test were offered : increase the sampling in if ( intermediate frequency ) in flight test were offered : increase the capacity of the transmitter and the terminal receiver channels without changing the apparatus of original system and on the conditions of obeying the standard remote sensing

    首先對軟體無線電的組成結構和飛行測試中實際使用的通道進行了闡述，在此基礎上提出了基於寬帶中頻帶通采樣軟體無線電結構在飛行遙測測試中的應用，在不改變原系統設備的情況下，在遵守遙測標準的前提下，提出增加機載發射機和接收機通道容量的設計方案。
  10. Simulation results demonstrate that iced aircraft envelope protection is capable of successfully avoiding incidents and accidents during flight in icing conditions, provide flying safety, operate definite action on the design of next generation civil airplane

    研究結果表明，結冰飛行包線保護系統將極大增強飛機容冰能力，保證飛機在各種結冰情況下的飛行安全，在下一代民機的研製中起到一定的作用。
  11. Reconfigurable flight control systems are control systems that are characterized by the ability to perform in the presence of drastic changes in the system dynamics due, for example, to abrupt system component failures or rapid changes in the operating conditions

    可重構飛行控制系統能夠根據預先設定的故障模式，自動地調節故障后系統的控制律。注重於使用無故障元件獲得更大效益、補償故障元件的功能，有利於保持系統的安全運行，最大限度地執行設定的控制指令。
  12. On the basis of collecting and processing many datum and materials. firstly. this paper analyzes main activities and cost constitutions of each stage of the life cycle of a fcs, and lay a foundation for later analysis and evaluation of system lcc. secondly, a basis method and usage range for estimating the system lcc are introduced. a multivariate linear regression model of pcs development cost and cost driven factor is built by use of the parametric method and supplies the base of cost estimation of newly - developed systems. thirdly, combine actual examples and make statistical analysis of lcc of a certain pcs developed by our institute, predict unhappened usage and service cost with grey prediction method, obtain proportion of each constitute to the lcc. forthly, according to actual conditions, use the fuzzy theory to overall evaluate efficacy of the fcs, fifthly, combimng our actual conditions, investigate specific measures of how to implement the life cycle cost management in our institute and put forward a new conception of developing web - based flight control system lcc management information system with pdm as the platform. at last, investigate important factors such as reliability and maintainability that may affect the life cycle cost of the fcs in detail, and put forward specific methods of lowering the life cycle cost of the fcs

    論文在收集和整理大量資料的基礎上，首先深入分析了飛控系統壽命周期各階段的主要活動以及各階段的費用構成，為以後系統壽命周期費用的分析和評價奠定了基礎；其次，介紹了壽命周期費用估算的基本方法和使用范圍，並利用參數法建立了飛控系統研製費用與費用驅動因子的多元線性回歸模型，為新研系統的費用估算提供了依據；第三，結合實例對我所研製的某型飛控系統的壽命周期費用進行統計分析，運用灰色預測方法對未發生的使用及維修費用進行預測，得出了該系統的壽命周期費用以及各組成部分所佔比例；第四，根據實際情況，首次運用模糊理論對飛控系統的系統效能進行了綜合評價，構造了飛控系統系統效能模糊綜合評價模型；第五，結合我所實際，探討了如何在本單位實施加強壽命周期費用管理的具體措施，提出以pdm為平臺，開發基於web的飛控系統lcc管理信息系統的新構思；最後，對影響飛控系統壽命周期費用的重要因素如可靠性和維修性等進行了詳細地研究，提出了降低飛控系統壽命周期費用的具體方法。
  13. Here, the aircraft is in extreme flight conditions that is high angles of attack and high angular rates. it can encounter severe nonlinear effects. detailed descriptions of the flight dynamic, aerodynamic models, inverse dynamic and the choice of the control variable are given

    2 、應用經典的微分幾何方法研究了一般的飛行狀態下飛機飛行的控制律，指出不利用矢量推力的飛行系統的控制方程一般都是可以逐步通過動態狀態反饋，適當的坐標變換和正則靜態反饋等三個步驟得以線性化。
  14. Abstract : a method named multi - times optimization is presented to solve the multi - specification optimization problem, which is difficult to solve using the variational optimal theory. in the method several demands are reduced to some sub - tasks. in every subtask a demand that can not be transformed into bound condition is taken as performance specification for optimazation, and the other demands are taken as bound conditions. by means of the method, the arrival time, number of turn, turn angle of the aircraft in the terminal area are selected as performance specification separately, and the general character of optimal flight route in the terminal area is given

    文摘:為了給飛機提供一條能滿足多種指標要求的最優飛行軌跡，針對變分最優理論難以求解多指標優化問題，提出了命名為多次優化的方法，即將多要求的優化任務分成先後相繼的多次任務，每次任務中選取一種不能邊界轉化的要求作為最優性能指標，而其餘要求轉化為邊界條件.利用這一方法以時間、轉彎次數、轉彎角度為最優性能指標給出了終端區最優飛行軌跡的一般特徵
  15. In this paper, maccormack explicit time - split scheme, baldwin - lomax algebraic turbulent model and two - steps hydrogen - air nonequilibrium chemical kinetics model are employed to simulate the 2 - d flow fields in a fixed geometry scramjet combustor in different injecting way of fuel in different flight conditions. the results show, in the same entrance condition, the operating mode of scramjet combustor is influenced by the control of fuel

    本文採用maccormack顯式時間分裂法、 b - l代數渦粘性湍流模型及氫-空氣兩步非平衡化學動力學反應模型，模擬了在不同的飛行馬赫數條件下，固定幾何的雙模態燃燒室在不同供油規律下的二維燃燒流場。
  16. " for the soaring flight and the evocative imagery of his poetry which in a visionary fashion reflects the conditions of our time

    由於他高超的飛越與豐盈的想象，表達了一種關于目前這個時代之富於意象的沉思
  17. Scramjet combustor may realize the subsonic - combustion mode and supersonic - combustion mode respectively based on the control of fuel in variable flight conditions. isolator has great effect on mode transition and preventing unstart of inlet. inlet can be unstarted by raising the back pressure result from chemical energy release in the combustor

    計算研究表明，在相同的來流條件下，供油規律對燃燒室的工作模態有著重大的影響；在不同的來流條件下，可以通過調節供油規律使燃燒室分別實現亞燃模態和超燃模態；隔離段對防止燃燒引起的壓力升高對進氣道的干擾和燃燒室的模態轉換具有重要的作用。
  18. With increasing concern about the potential health risks of long flights in cramped conditions, the aim was to make a much more spacious cabin with room for passengers to move around during the flight

    由於外界越來越擔心處于狹窄空間中的長時間飛行可能給健康帶來風險，新航的這一設計旨在創造出更大的艙內空間，以方便乘客在飛行期間來回走動。
  19. A numerical simulation software is developed that can be used to simulate standing oblique detonation waves in hypervelocity flight conditions. reasonable parameters and advanced method are provided for the application of standing detonation propulsion technology. the main points are as follows : the mathematical model is developed that can be used to analyze the properties of planar standing oblique detonation waves

    通過對駐定斜爆轟波形念的理論分析和數值模擬，對高超音速條件下斜爆轟波的穩定性現象進行了系統研究，探討了產生駐定斜爆轟波的臨界條件，開發了平面和錐形駐定斜爆轟波流場數值模擬軟體，為駐定爆轟推進技術的應用提供合理的系統參數和先進手段。
  20. Hundreds of hours in flight and kilometers of cross country in various countries well known for xc potential : texas ， mongolia ， switzerland ， france ， austria and others well known for their difficult conditions : japan ， korea ， portugal

    在世界許多知名的場地做了成百小時的飛行和遠距離的越野，如：德克薩斯、蒙古、瑞士、法國、奧地利，以及日本、韓國、葡萄牙等地。
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