模擬飛行計劃 的英文怎麼說

中文拼音 [mónǐfēihángjìhuà]
模擬飛行計劃 英文
simulated flight plan
  • 模 : 模名詞1. （模子） mould; pattern; matrix 2. （姓氏） a surname
  • 擬 : 動詞1. （設計; 起草） draw up; draft 2. （打算; 想要） intend; plan 3. （模仿） imitate
  • 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...
  • 計 : Ⅰ動詞1 （計算） count; compute; calculate; number 2 （設想; 打算） plan; plot Ⅱ名詞1 （測量或計算...
  • 劃 : 劃動詞1 （撥水前進） paddle; row 2 （合算） be to one s profit; pay 3 （用尖銳的東西在別的東西上...
  • 模擬 : imitate; simulate; analog; analogy; imitation; simulation模擬艙 boilerplate; 模擬電路 [電學] circ...
  • 飛行 : flight; flying; aviate; voyage; volitate; hop
  • 計劃 : 1 （工作、行動以前預先擬定的內容和步驟） plan; project; programme; device; devisal; design 2 （做...
  1. Afterwards, combining mathematical model with simulation model, the moving air traffic flow in airport was further analyzed ; the algorithms of random flight generation, departure waiting list and taxiing flow optimization was proposed to construct the airport practical evaluation model

    然後，結合數學規劃模型和模擬模型，進一步分析了機場空側系統空中交通流的運動情況，提出了隨機飛機流增減演算法、跑道頭離場等待隊列和滑行飛機流優化演算法，構建以實際飛行計劃為依據的機場實際容量評估模型。
  2. In this dissertation the control loop of attitude angle and collective piston loop are separately. the controller is designed at two scales. and the simulation shows the uncoupling of three attitudes angle loop is achieved with dynamic inversion scheme

    在姿態角通道的設計中，採用了動態逆思想，按照時標分離的原則將直升機飛控系統劃分為快慢迴路，並採用動態逆方法對飛行控制系統進行設計和模擬，模擬結果表明動態逆在通道解耦方面非常有效。
  3. As n1 less than 85 %, it gives the open - loop control law of fuel and staff, and when n1 more than 85 %, it adopts close - loop to fuel. the paper designed pi controller and adopted reasonable portion for envelopment. 3. the paper studies transition control process of the engine and gets the main fuel control law of accelerating and decelerating which has been simulated

    第二，對其穩態控制過程進行了分析研究，當n1小於85的自始轉速時，給出了供油量與油門桿之間的開環控制規律：當n1大於85的自始轉速時，採用分塊的pi控制方法對燃油進行閉環控制，且對飛行包線進行了合理的劃分，用優化方法設計出了pi控制器並用matlab進行了模擬。
  4. In this thesis, a system planning of assembly sequence planning module in virtual assembly system is proposed which is based on analyzing the characteristic of airfoil assembly and assembly design. the core techniques of assembly sequence planning which based on genetic algorithm and fuzzy set theory are investigated in detail. main research work and achievements are as follows : 1

    本文在分析飛機機翼裝配特點的基礎上，完成了虛擬裝配系統中裝配順序規劃模塊的設計與實現，並對基於遺傳演算法及模糊集理論的裝配序列規劃技術進行了深入研究，主要研究內容包括： 1
  5. The control loop of attitude angle is designed with dynamic inversion method, and is divided into fast loop and slow loop at two time scales. in the end, the result of simulation showed that the three channels of attitude angle are discoupled by dynamic inversion method

    在姿態角通道的設計中，採用動態逆思想，按照時標分離的原則將直升機飛控系統劃分為快慢迴路，並分別採用動態逆的方法進行設計，最後通過模擬得以證明直升機的三個姿態角通道得到有效的解耦。
  6. According to the study above, we bring forward combined rbf - rbf neural network to target assignment and attack sequence decision, which is proved to be feasible by matlab simulation. thirdly, we build mathematics model of super - maneuver fighter and part the aircraft states to two loops based on principle of time delay. then nonlinear dynamic inverse theory is applied to design the flight control law

    接下來本文建立了超機動飛機的數學模型，並根據時標分離的原則，將飛機狀態劃分為快迴路和慢迴路，然後應用非線性動態逆理論分別構造兩個迴路的控制律，同時利用設計的飛控系統對赫布斯特機動進行了模擬。
  7. The results show that the wind effects are relatively severe and therefore control system design should take this fully into account. this paper gives significant references for uav conceptual design, flight mission planning and trajectory controlling system design

    本文的數值建模方法與實際模擬軟體對無人機的總體設計、飛行任務規劃及控制器設計等都有實際的參考意義。
  8. Firstly, total system could be divided into four parts including simulation algorithmic library, simulation knowledge library, flight test database, simulation test database, according to characters of resources and functional differences of flight simulation, and then these parts are designed and accomplished respectively

    首先，根據飛行模擬資源的特點和功能上的區別，可以將整個系統從總體上劃分為模擬演算法庫、模擬知識庫、飛行試驗數據庫和模擬試驗數據庫等四個部分，然後分別進行設計和實現。
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