simulated aircraft 中文意思是什麼

simulated aircraft 解釋
模擬飛機
  1. For the convenience of the design and experiment of cpcs, a sapc ( simulated atmospheric pressure cabin ) that can simulate the atmospheric situation when aircraft are at different flight states was necessary

    座艙壓力控制系統的研製和檢驗過程中,需要大氣壓力模擬艙,其主要功能是模擬飛行器各種飛行狀態下所處大氣壓力環境。
  2. Several icing parameters were imported to calculate the change of drag coefficient and typical derivatives between clean aircraft and iced aircraft, and the aircraft flight envelope change of iced and un - iced situation was computed, and the small disturbance flight dynamics model was modified to study the effect of the ice accretion on the aircraft dynamics by importing the ice parameter to it, and the longitudinal and lateral stability and the elevator, aileron and rudder step response were also studied and simulated

    根據這些參數計算了飛機結冰后阻力系數以及典型氣動導數的變化,並計算了結冰前後飛機的飛行包線;同時對結冰前後飛機的縱向、橫側動穩定性以及升降舵、副翼和方向舵階躍操縱響應進行模擬計算。
  3. The flight ' s atmospheric dynamic characteristics is considered, the aircraft is modeled as a combination of objects. most compositions, such as scene system, flight system, flight ' s sound and control surface are all simulated

    )等建模軟體建立了相應的三維表現模型;模擬了飛機的主要系統:飛行系統、視景系統、儀表系統和音響系統。
  4. " it will be activated in the evening of december 2, simulating an aircraft in distress about 130 kilometers south of hong kong. search aircraft, helicopters and ships will be dispatched to the area the following morning to search and locate the simulated targets in the south china sea, " he said

    演習由十二月二日傍晚開始,模擬飛機于香港以南一百三十公里之南中國海失事,翌日早上,各參與單位將派出搜索飛機,直升機及搜救船找尋及搜索目標。
  5. Characteristics of eye movement and cognition during simulated landing of aircraft

    模擬飛機降落過程中的眼動和認知研究
  6. Using this model, not only the normal static and dynamic characters of aircraft epgs but also the fault state system can be simulated. it is useful to analyse and design aircraft epgs

    利用本文開發的模型,不僅能模擬電源系統及其部件正常工作時的穩態和動態特性,而且能模擬其故障狀態,有助於對飛機電源系統進行分析和設計。
  7. Then the steady and unsteady subsonic, transonic and supersonic viscous flows around airfoil and some aircraft are numerically simulated. the 3 - dimensional unsteady navier - stokes equations are solved using the implicit lu - nnd algorithm, with baldwin - lomax turbulent model. on the basis of simulating unsteady viscous flow, coupling the structure dynamics equations, the problems of static aeroelasticity and flutter are investigated for wings and elevator

    在模擬非定常粘性繞流的基礎上,與顫振運動方程相耦合,分別對機翼和全機流固耦合現象中顫振問題進行了研究,準確求解跨音速顫振臨界速度,分析機翼和全機的從亞音速到超音速范圍的顫振規律,並研究分析了機翼飛行迎角變化對顫振速度的影響。
  8. Machining deformation of aircraft monolithic component is simulated by finite element method ( fem ) and validated by experiment. the initial residual stress in pre - stretched plate is generated by simulating quenching and stretching processes. with a single tool - tooth milling process fem, the machining loads in monolithic component material removing is obtained. restart - calculation is put forward to complete the whole simulation of machining process. to verify the fem result, an experiment is carried out. the deformation distribution of the monolithic component resulting from fem shows a good agreement with the experiment result, which indicates that the key technologies presented in the paper are practicable and can be used to simulate the milling process of monolithic component to predict its deformation. lengthy and expensive trial and error experiment process can be avoided

    在模擬淬火、拉伸過程獲得含有初始殘余應力的預拉伸板材以及模擬單齒切削過程獲得切削載荷的基礎上,提出並採用接力演算法,對一航空整體結構件的材料銑削過程進行有限元模擬,同時進行了試驗研究.結果表明,有限元模擬的整體結構件的變形與試驗具有一致性,從而證明提出的整體結構件加工模擬關鍵技術的可行性,避免了為研究加工變形而進行的繁瑣的試錯法
  9. The electro - hydraulic proportional control law is given. the laws of tracking control of displacement and speed of aircraft as well as tracking control of angle and angular speed of belt wheel are designed by means of state feedback linearization and quadratic performance index linear optimal control method. the robustness of the designed systems is analyzed, and arresting processes are simulated

    給出了電液比例控制規律;利用狀態反饋線性化及二次型性能指標線性最優控制方法分別設計了系統跟蹤控制飛機位移與速度以及跟蹤控制帶輪轉角與角速度的非線性控制規律;對所設計的攔阻系統進行了魯棒性分析及攔阻過程模擬,模擬結果表明,通過選取適當比例系數或控制權系數,兩種控制系統的控制效果及魯棒特性均優于新型飛機攔阻系統。
  10. 3. wth application of large - scale computational software anasys - dyna, the case of elastic impact to each other of two recta - ngular cross - section rods has been implemented and also compared with theoretical results, which maks good agreement and draws very helpful practical experiences to use some techncal parameters in the program. eventually, the a real - world aircraft windshield shell structure impacted by a flying bird has been simulated through fem numerical computation, and meanime, an engineering predical experimeni of bird sttiking to the windshield in some type of aircraft has been performed

    3 、應用大型科學計算程序anasys - dyna ,對彈性體碰撞進行了數值計算驗證並與理論結果對比,獲得了計算參數應用的實踐經驗;在此基礎上,進行了鳥體撞擊飛機風擋結構動力學響應的實際數值計算,與此同時安排了工程鳥體撞擊試驗,並就兩者計算結果給予了細致分析對比,獲得了良好的一致性結論。
  11. Fourth, according to the actual aircraft frame part, the scale component is machined, and the quenching process of the scale component is simulated, which obtain temperature field and residual stress field in the frame scale component

    4 、建立了某軍用飛機隔框零件比例件三維淬火過程有限元模型,模擬得到其三維瞬態溫度場與應力場。
  12. To shorten aircraft r & d time and reduce cost, simulation is necessary, aircraft is an airborne one and environmental actions on aircraft are simulated by the loading system

    在模擬系統中,飛行控制系統採用實物,而飛行器在飛行過程中所受的外界作用力則由電液伺服加載系統來提供。
  13. Players see the window shall be a simulated aircraft cockpit perspective, the mobile mouse can be controlled on the screen star. click on the menu fire

    玩家看到的窗口即為一個飛機駕駛艙的模擬視角,移動鼠標可以控制畫面上的準星,點擊左鍵開火。
  14. Players see the window shall be a simulated aircraft cockpit perspective, the mobile enter the name of the game

    玩家看到的窗口即為一個飛機駕駛艙的模擬視角,移動鼠標可以控制畫面上的準星,點擊左鍵開火。
  15. This algorithm successfully estimated sonobuoy position for simulated aircraft data. the effect of aircraft - to - sonobuoy range, the frequency of measurement, and changes in altitude are also analyzed

    模擬表明,對于給定的飛行模式和飛機參數,該演算法可以成功地估計浮標的位置,並且分析了飛機與浮標的距離、測量頻率和飛行高度對定位的影響。
  16. The controller for longitudinal short period model of aircraft has been designed and simulated by using those schemes. simulation results are demonstrated to show that the scheme is not only simpleness and easy accomplish, but also enhance the performance of flight and the effectiveness and applicability of the proposed method

    模擬結果表明,用此方法,不但使設計過程簡單且易於實現,而且用該方法設計出控制器可以有效地改進飛機的飛行性能,提高失速迎角,加快起恢復速度,閉環跟蹤效果也令人滿意。
  17. Form the practical engineering point of view, the longitudinal natural stability of anti - submarine helicopter is analyzed, the stabilized loop of the pitch angle is systematically studied. this paper is mainly on the design and simulation of the stabilized loop of pitch angle with classic control method and fuzzy control method and many useful results are achieved. the main work of this paper can briefly described as follows : after the mathematical models of aircraft was build with relevant date, the stabilized loop of pitch angel was designed and simulated

    本文從工程應用的角度出發,分析了國產直九c反潛直升機的縱向自然穩定性,分別應用古典控制和模糊控制的方法,系統地研究了國產直九c直升機的縱向姿態角穩定迴路、速度迴路、高度迴路、自動過渡等,對縱向姿態角穩定、速度、高度、自動過渡迴路進行了控制律的設計與模擬,取得了良好的控制效果。
  18. Finally, system is simulated, and the results can satisfy the requests value of the aircraft landing system and it represents a strong robustness of aircraft landing control system

    然後設計了自動著陸控制系統控制律,並進行了模擬,模擬結果滿足飛機自動著陸各項指標要求,表明所設計的自動著陸控制系統具有較強的魯棒性。
  19. In the end, an aircraft system is simulated by software matlab, and the data of 3 subsystems are obtained

    最後本文對一飛行器系統進行建模模擬,得到三個子系統的模擬數據。
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