飛行速度計 的英文怎麼說

中文拼音 [fēihángsùdùjì]
飛行速度計 英文
airspeedometer
  • 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...
  • 速 : Ⅰ形容詞（迅速; 快） fast; rapid; quick; speedy Ⅱ名詞1 （速度） speed; velocity 2 （姓氏） a surna...
  • 度 : 度動詞[書面語] （推測; 估計） surmise; estimate
  • 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...
  • 飛行 : flight; flying; aviate; voyage; volitate; hop
  • 速度 : 1. [物理學] velocity; speed; blast; bat 2. [音樂] tempo3. （快慢的程度） speed; rate; pace; tempo
  1. Less benefit is achieved on this vehicle by use of the accelerometer.

    在這個飛行器上使用加速度計帶來的好處不大。
  2. The outputs of these accelerometers are the three coordinates of the inertial velocity of the vehicle with the exception of gravity effects.

    這些加速度計的輸出是三個沒有重力影響的飛行器慣性速度座標。
  3. I spun up my inertial to a get ground speed indication to kind of give me a rough guess

    我操縱慣性讀數系統得到地速顯示，多少估計出飛行速度。
  4. He was alone when he set out last week on what was to be a three - hour flight, looking for a large flat area where he could try to set a new land speed record on the ground

    他上個星期又一次單獨起飛，他當時的計劃是要飛行3個小時，尋找一片平地，沖擊最快著陸速度的世界記錄。
  5. The method of wing shape optimization of space shutlle has been developed with penalty function approach in which the objective function is the mass of the wing and the constraints are the hypersonic re - entry flight cross range, lift / drag ratio, and subsonic flight lift / drag ratio, the margin of the longitudial static stability and the magnitude of the horizontal landing speed etc

    摘要介紹了在滿足高超音速再入橫向機動航程，高超音速再入飛行時的升阻比，亞音速進場飛行時的升阻比，縱向靜穩定性裕度和水平著陸速度等飛行性能設計要求下，用罰函數法尋求使航天飛機機翼質量為最小的外形優化方法並給出了算例。
  6. Although aircraft designers and engineers continued to employ wing - warping techniques for years afterward ( especially on early monoplanes such as the bleriot xi ), ever faster flight speeds eventually led them to beef up wing structures to resist the resulting stresses

    雖然其後許多年間，飛機設計師和工程師仍繼續採用翹曲機翼設計（尤其是布雷修xi型等早期單翼機） ，但由於飛行速度不斷提升，終于迫使他們加強機翼結構，以承擔所增加的應力。
  7. In this paper, firstly the macro parameter of the series connection app was comprehensively analyzed, among which the trajectory location of the bullet emission and the terminal velocity of the bullet were mainly analyzed, and the feasibility of the series connection app to cope with explosive reactive armor was demonstrated. and then the macro design about the head of the series connection app was made, among which a particular analyse about the bullet " s launching process was made, from which we concluded the relation between the thickness of the airproof loop and the velocity of the bullet detached from the carrier and the relation between the length of the bullet and the velocity of the bullet detached from the carrier and the relation between the length of the bullet and the burning rate of the powder and the relation between the length of the bullet and the maximum pressure of the emission hole and the relation between the length of the bullet and the emitting time of the bullet, and the reasonable str ucture of the head of the carrier and bullet were designed, then the intensity of the head of the carrier was checked out using of the software of ansys

    本文首先對子母式穿甲彈總體參量作了全面的計算分析，其中主要分析了子彈射出的彈道位置和必要的子彈著靶速度，論證了子母式穿甲彈對付爆炸式反應裝甲的可行性，然後對子母式穿甲彈彈頭部進行了總體設計，其中主要對子彈的發射過程進行了詳細的分析，得出了母彈彈頭部發射孔內閉鎖環厚度與子彈飛離母彈速度的關系、子彈長度與子彈飛離母彈速度的關系、子彈長度與火藥燃燒率的關系、子彈長度與母彈彈頭部發射孔內最大壓力的關系以及子彈的長度與子彈發射所需時間的關系，設計出了合理的母彈彈頭部結構和子彈的結構，並利用ansys有限元分析軟體對母彈彈頭部的強度進行了校核。
  8. One ornithologist had devised a formula to compute the ratio of domestic to pure - strain wild turkey in an individual bird by comparing the angle of flight at takeoff and the rate of acceleration

    有個鳥類學家設計了一種計算公式，對家養火雞和純種野火雞進行起飛角度和加速度的比較。
  9. Second, by computing the trajectory of the missile and the method of analyzing cep, influences that the fighter ' s height, speed, pitch angle, the deflection angle between fighter and target, and the target moving characters make on the times of fighter attack and missile launch are deeply developed. third, by relating the motion of the missile and the fighter, the influences that fighter ' s dive angle and the deflection angle between fighter and target make on the attack field of the fighter are discussed in this paper when the fighter perform vertical and horizontal attack. criterion of attack effect is proposed focusing on attack time of the fighter, trajectory of the missile and destruction probability to the target

    本文主要完成了以下幾個方面的工作：對導彈可發射區和飛機可攻擊區進行建模，通過對導彈彈道的模擬計算，並運用典型的圓概率偏差精度分析方法，詳細討論了飛機實施攻擊時，飛機的飛行高度h 、速度v 、俯仰角、與目標的偏離角_ x及目標運動特性等對飛機攻擊時機和導彈發射時機的影響；因此，將飛機和導彈結合起來，詳細研究了飛機在垂直平面和水平平面內實施攻擊時，飛機俯沖角和與目標的偏離角_ x對飛機的攻擊范圍的影響；以飛機實施攻擊的時間t 、彈道特性和對目標的殺傷概率p來評判對地攻擊的效果；最後給出典型算例，通過對空地攻擊過程的模擬實現，對飛機飛行過載提出要求。
  10. In addition, a series of reasonable time histories of helicopter velocity, angular velocity and flight attitude were shown during the given dolphin maneuver flight

    最後以黑鷹直升機為例計算了魚躍越障機動飛行時駕駛員操縱輸入及直升機速度、角速度和飛行姿態的變化規律。
  11. On the basis of these results, the relations of total - pressure recovery coefficient or flow coefficient and flight mach number, angle of attack and the second movable wedge angle of the inlet have been founded by hypersurface fitting, then the mathematical model of the inlet is established

    根據流場計算結果並利用超曲面擬合方法建立了進氣道總壓恢復系數、流量系數與飛行馬赫數、進氣道攻角及二級可調斜板角度之間的關系，由此得到了二元混壓式超聲速進氣道數學模型。
  12. This paper presents a wider research field - risk analysis. through the study of the effects that threat factors and error factors impact on the flight risk and adjusting performance rules, the horizontal safe corridor, threat avoidance, vertical altitude real - time modification and the fastest trajectory programming are progressed

    總結前人在該方面的研究成果，提出一個更加廣義的研究角度? ?風險分析。通過對威脅因素、誤差因素對飛行風險的作用，調整性能準則而進行了水平安全走廊設計、威脅迴避、垂直離地高度實時修正以及最快速航跡規劃。
  13. Using flyer velocity gained from energy characterizing method, definite parameters of flyer and explosive, deterministic parameters of initiation system critical initiation energy to flyer of explosive can be theoretically calculated. associating with critical initiation voltage of explosive experiment measuring comparisons and evaluations can be conducted for flyer sensitivity of explosive

    利用能量損失法求出的飛片速度以及已知的飛片參數、炸藥參數、起爆系統中的既定參數，可以對炸藥的飛片臨界起爆能量進行理論上的計算，結合實驗測量的炸藥臨界起爆電壓值，可以對炸藥的飛片感度進行比較和評價。
  14. The control laws of longitudinal and lateral - directional autopilot modes are designed based on root locus theory. the control laws of altitude holding mode, heading holding mode, auto - throttle control and air speed holding mode are designed as well

    研究了無人機的飛行控制技術，利用根軌跡法設計了無人機的縱向與側向姿態保持控制律，設計了高度保持、航向保持、自動油門及速度保持控制律。
  15. The main research work of the thesis is summarized as follows : 1. the improved fuzzy logic control method the phenomenon of steady - state errors and flutter exists in the traditional fuzzy controller. an improved fuzzy controller without quantilizing is presented

    地形跟隨飛行控制律設計針對某型飛機應用控制航跡角法和控製法向加速度法對不同的反饋信號分別設計了pi控制器和模糊控制器，並做了模擬比較與魯棒性驗證。
  16. To solve the problems caused by the varieties of the missile dynamics with the difference of flight height, velocity and attitude angle in modeling the missile, in this thesis, the theory of variable structure model reference adaptive control is used to design a pitch channel autopilot based on a longitudinal missile model, the status equation using the measurable parameters of load and angular rate is established, and the methodology to choosing the reference model is discussed also, and the performance of the controller is analyzed by means of simulation

    為了解決攔截彈氣動參數隨飛行高度、速度、姿態的不同，變化范圍大，控制系統難以準確建模的困難，基於縱向平面攔截彈模型，採用模型參考變結構控制理論設計了俯仰通道姿控復合控制系統，以可測量變量過載和角速度作為狀態量建立了系統的狀態方程，討論了參考模型的選擇方法，並對系統的性能作了模擬分析。
  17. Finally, one trajectory meeting the height and the speed of towing flight is designed

    最終設計出一條滿足牽引飛行高度和速度的軌道。
  18. Based on this main idea, first the thesis discusses the mathematics model of gyro and accelemeter, the initial alignment of north - pointed strapdown inertial navigation system, the method of calculation navigation, the method of generating flight orbit data, the method of ins / gps integrated navigation in detail. then the thesis develops the system generating flight orbit data and the system of real - time simulating strapdown inertial navigation with vc + + 6. 0

    論文以此為核心展開：首先詳細討論了陀螺和加速度計的數學模型、指北式捷聯慣性導航系統初始對準和導航解算的演算法、飛行軌跡數據生成演算法、 ins gps組合導航演算法；然後利用visualc + + 6 . 0開發出飛行軌跡數據生成系統、捷聯慣性導航實時模擬系統。
  19. Specific executions of the fly - shear angle calculation, skin - pass mill control, line speed and tension control designed in the typical control design have been deliberately described, which is valuable for the domestic industry applications

    在典型控制方案論述中對飛剪角度計算和控制、平整機控制及機組速度、張力控制等給出了具體的實施過程，在國內同行業具有較好的應用價值。
  20. The fdps processes the flight plan data from aeronautical messages and prints out flight progress strips automatically for use by air traffic controllers to updatemonitor the aircraft flight profile, such as flight route, estimated time of departurearrival, flight level, expected times at reporting points, cruising speed, etc

    飛行數據處理系統可作航機飛行計劃的數據處理，和即時印出飛行進度紙條，供航空交通管制員用以更新和監察航機的飛行狀況，例如航道、預計著陸起飛時間、飛行高度、位置報告的預計時間、飛行速度等。
分享友人
分享到 Line

分享到臉書