飛行狀態 的英文怎麼說

中文拼音 [fēihángzhuàngtài]
飛行狀態 英文
attitude of fight
  • 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...
  • 狀 : Ⅰ名詞1 （形狀） form; shape 2 （情況） state; condition; situation; circumstances 3 （陳述事件或...
  • 態 : 名詞1. （形狀; 狀態） form; condition; appearance 2. [物理學] （物質結構的狀態或階段） state 3. [語言學] （一種語法范疇） voice
  • 飛行 : flight; flying; aviate; voyage; volitate; hop
  • 狀態 : status; state; condition; state of affairs: （病的）危險狀態 critical condition; 戰爭狀態 state o...
  1. Either to be a platform for originating an attack to the enemy or to be a vehicle for landing force, the wig vehicle must fly with low altitude in martial action. it is also a valuable topic that how to take advantage of the good interaction and avoid the potential dangers as flying at lower altitude in demotic application

    在軍事上，地效翼船無論是作為實施襲擊的平臺還是登陸作戰的工具，保持低空飛行狀態都是必須的；在民用上，如何在充分利用低空飛行的有利因素的同時規避低空飛行時潛在的風險也是一個值得研究的問題。
  2. 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。
  3. This display system can show the real time flying status parameter, the flight simulation curves, and the flight attitude using the three dimensional animation

    實時顯示飛行狀態參數，飛行模擬曲線，並採用三維動畫實時顯示飛機狀態。
  4. 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。
  5. 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
  6. As the air - breathing engine, the performance of solid rocket ramjet is determined not only by structure of engine and the performance of propellant, but also by flight condition

    作為吸氣式發動機，其性能不僅取決于發動機本身結構和推進劑性能，與飛行狀態也有密切的聯系。
  7. For studying the performance of solid rocket ramjet under the influence of different flight conditions, it ' s significant to simulate the integrated flow field of inlet and combustor

    因此，開展超聲速進氣道/補燃室流場一體化數值模擬研究對于考查飛行狀態對於火箭沖壓發動機性能的直接影響具有重要的現實意義。
  8. In order to determination the thrust, the thrust definition and many control parameters are analyzed discussed, which mass flow rate and flight altitude are involved. it is difficult to measure the flight thrust of solid rocket ramjet directly

    通過討論高空飛行推力與地面可測試參數的關系，得到了固體火箭沖壓發動機高空飛行狀態下推力折算方法，並開發相應的計算程序。
  9. Compared with non - slung - load flight, additional aerodynamic load, gravity load should be considered in the slung - load system. so the moment to the gravity center, flight mode and the natural frequency will change

    直升機吊掛飛行，與直升機非吊掛飛行狀態相比，增加了新的氣動載荷、重力載荷，和因此產生的對直升機重心的力矩，其飛行運動模式、低頻振蕩固有頻率均發生改變。
  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. Virtual instruments technology was applied to build the measurement and control system and develop the software for the experiment, which improve the efficiency of the study. finally the velocity control experiment of sapc at several flight states was accomplished which has a good effect. the study has certain significances on developing electronic - electric cpcs

    構建基於虛擬儀器技術的測控平臺，採用labview軟體開發測控軟體，利用實驗室的現有條件，結合某型電子/氣動式壓調器的實驗，完成了飛機在各種飛行狀態下所需的大氣壓力模擬艙內的壓力控制，取得了較好的效果。
  12. Based on the prior knowledge of flight navigation control, a combined navigation system is achieved by integration of dgps, magnetometer and atmosphere data computer

    基於飛行導航控制的先驗知識，對dgps 、磁航向計、大氣數據計算機等飛行導航傳感器獲取的飛行狀態信息進行綜合處理，實現了組合導航控制。
  13. The echolocating calls in the state of fly were compared with those in the state of hang in two kinds of bats, r. yunanensis and h. pratti, and the doppler compensation effect was described. the analyzing result indicated that the frequency in hang was higher that that in fly, the duration and interpulse duration in hang were longer than those in fly, and the fm bandwidth in hang was narrower than that in fly

    比較了雲南菊頭蝠和普氏蹄蝠飛行狀態和懸掛狀態下的回聲定位聲波，描述這2種蝙蝠的多普勒補償效應，懸掛狀態聲波頻率顯著高於飛行狀態，聲脈沖時間和間隔時間顯著長于飛行狀態， fm帶寬窄于飛行狀態。
  14. Some technique issues concerned to the scene simulation system of the launch vehicle was discussed and developed in this thesis. in this scene simulation system, the established 3 - dimension ( 3d ) model of the objects are imported to scene simulation environment by programming to create a vivid virtual scene. scene simulation technique can objectively describe the simulation process, realize the flight simulation as well as real time roam of launch vehicle, etc.

    其中，視景模擬系統是整個系統最有顯示度的部分，它採用視景模擬技術，根據模擬的目的，構造模擬對象的三維模型和場景驅動，達到客觀、實時的再現模擬過程，實現火箭飛行狀態的可視化模擬和火箭測試狀態的實時漫遊等功能。
  15. " the cnsatm has immense benefits in enabling aircraft to operate more frequently within their most optimum flight envelop, while minimising airspace constraints, and reducing traffic congestion. it also commensurates with achieving a marked increase in flight safety

    該系統不但能容讓航機在最佳的飛行狀態范圍增加飛行次數，把空域限制減至最少，紓緩航空交通擠塞，而且更可顯著提高飛行安全。
  16. This paper studies optimal helicopter flight operations in the event one - engine failure. a three - dimensional point mass with a yawing motion of uh - 60a has been used to study rto and cto from an elevated heliport or from a heliport, a first order dynamic of the oei contingency power is considered. flight after engine failure are formulated as nonlinear optimal control problems

    雙發及多發直升機單發失效后，直升機飛行所需要的功率由剩餘發動機提供，而在某些需要大功率的飛行狀態時，如起飛狀態、著陸狀態等，剩餘發動機提供的功率可能滿足不了，這就需要對剩餘發動機的可用功率進行合理利用。
  17. 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。
  18. Helicopter aerodynamic parameter identification in vertical flight

    直升機垂直飛行狀態氣動參數辨識方法研究
  19. Study on slider steady flying attitude in high density magnetic storage system

    高密度磁記錄系統中磁頭穩定飛行狀態研究
  20. It is a novel way ( problem ) to measurement dynamically the recoil in the flight

    在飛行狀態下進行後座力動態測量是一種新的測試課題。
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