氣動力矩 的英文怎麼說

中文拼音 [qìdònglìjǔ]
氣動力矩 英文
aerodynamic moment
  • 氣 : Ⅰ名詞1 （氣體） gas 2 （空氣） air 3 （氣息） breath 4 （自然界冷熱陰晴等現象） weather 5 （氣味...
  • 力 : Ⅰ名1 （力量; 能力） power; strength; ability; capacity 2 [物理學] （改變物體運動狀態的作用） forc...
  • 矩 : 名詞1. （畫直角或正方形、矩形用的曲尺） carpenter's square; square2. （法度; 規則） rules; regulations 3. [物理學] moment
  1. Aerodynamic forces and moments are strictly speaking functionals of the state variables.

    嚴格說來，氣動力和力矩是狀態變量的泛涵。
  2. The aerodynamic forces on any control surface produce a moment about the hinge.

    在任何操縱面上的空氣動力均產生圍繞其鉸鏈軸的力矩。
  3. It is an important half hardware - in - loop simulation equipment, which is often used to simulate the aerodynamic torque load on the missile rudder or elevon actuators in the flight

    它是地面半實物模擬系統中的一種重要專用設備，用來模擬飛行器舵機在飛行過程中所承受空氣動力力矩載荷。
  4. This paper adopts linear interpolation to deal with data of wind tunnel experiment for sample uav and realizes modeling and simulation of the sample uav with c language in common aerodynamics and moment coefficient

    本文採用線性插值處理樣例無人機風洞試驗數據，採用正常情況下的氣動力及力矩系數數學模型，並用c語言實現樣例無人機建模與模擬。
  5. Method study of normal force engineering calculation of missile with rectangular cross - sectional shape

    矩形截面彈體法向氣動力計算方法
  6. Of all the aerodynamic parameters required in stability and control analysis, the hinge-moment coefficients are most difficult to determine with precision.

    進行穩定性和操縱性分析所需要的全部空氣動力參數中，鉸鏈力矩系數最難準確地確定。
  7. The complicated aerodynamics characteristic of spinning projectile with lateral jets and with attack angle is studied detailedly. the formation and changes are analyzed including magnus force, normal force, yawing moment, pitching moment and pressure center

    系統分析了旋轉側噴彈丸復雜的空氣動力學特性，分析了馬格努斯力系數、法向力系數、偏航力矩系數、俯仰力矩系數和壓力中心等參數的產生機理和變化規律。
  8. First, a great deal of aerodynamics and moment parameters are processed by look - up table, and then the flight simulation model of normal aircraft and fault aircraft are established

    首先，利用look - uptable對大量的氣動力參數及氣動力矩參數數據進行了插值處理，並在此基礎上建立了正常和故障飛機飛行的模擬模型。
  9. Electro - hydraulic servo loading system ( ehsls ) simulates the aerodynamic torque acting on the rudders while flying. ehsls can be used to create various types of loading on the rudders in the lab condition to analyze its performance

    電液伺服加載系統是模擬飛行器在飛行過程中舵面所受空氣動力矩的加載裝置，其功能是在實驗室條件下復現飛行器舵面所承受的各種氣動載荷。
  10. It is difficult to replicate hinge moment accurately and rapidly because surplus torque affect dynamic performances of load simulator system badly with large intensity and continuous variation derived from variable velocity of rudder system

    這種干擾作用具有強度大、隨舵機速度不同連續變化的特點，它的存在嚴重影響了負載模擬器的動態性能，使得加載系統難以準確、快速地復現空氣動力鉸鏈力矩。
  11. The structural vibrational equations for the former are also depicted. the disturbance torques imparted by space environment are analyzed, which include gravity gradient torque, solar pressure torque, aerodynamic torque and magnetic torque

    對作用在衛星上的各種空間環境力矩進行了分析，包括重力梯度力矩、太陽光壓力矩、氣動力矩、剩磁力矩等。
  12. In the modeling of dynamics of the vehicle, the forces and moments arise from both aerodynamic and propulsive sources, which are for these configurations hard to separate

    模型建立中，由於由推進系統以及空氣動力產生的力與力矩很難分離，因此本文只是提出一個設計初級階段考慮飛行器特性的解析表達式。
  13. On the basis of looking up a lot of referenced works, the phenomenon that lateral jet injected into the external air stream surrounding an intercepting missile is analyzed. the effects of jet interaction on forces and moments are described by interaction amplification factor, and the algorithm to calculate the interaction amplification factor is presented, then the motion model and the dynamics model of interceptor are established according to the previous analysis

    根據大量參考文獻的結論，分析了側向噴流射入攔截彈外流的流場特徵，以干擾放大因子來描述干擾效應對力和力矩的影響，給出了放大因子的計算方法，進一步建立了噴流側向力和空氣動力作用下的導彈運動學和動力學模型。
  14. For the flexible shaft model, a computer program frame for dynamic model is set up in the matlab. the dynamic processes of hawt which support several aerodynamic moments are simulated and the simulation results are analyzed and compared

    並結合傳動機構的柔性軸模型，在matlab中建立了動態模型的系統框圖，模擬了水平軸風力機在幾種氣動轉矩作用下的動力學過程，並對模擬結果進行了分析和比較。
  15. The aerodynamic terms in the force and moment equations have all been replaced by the state variables of which they are functions and control forces and moments.

    力和力矩方程中的空氣動力項已經全部用為其函數的狀態變量及操縱力和力矩所代替。
  16. Through the analysis of attitude dynamic equation, how to realize three axis passivity stabilization of the mircrosatellite by just using environmental torque is presented. three sorts conformations of three axis passivity stabilization of the mircrosatellite by using environmental torque are put forward, one is to realize the passive attitude control of microsatellite by using the aerodynamic moment and the gravity gradient, the other two by making use of the gravity gradient and the geomagnetic moment, the attitude dynamics of microsatellite of the three sorts are analysed in detail

    通過對衛星姿態動力學方程分析，給出如何利用環境力矩實現微小衛星三軸姿態被動穩定，並提出三種利用環境力矩實現微小衛星三軸姿態被動穩定方案，即一種利用氣動力矩和重力梯度實現微小衛星三軸姿態被動穩定方案和兩種利用重力梯度和地磁力矩實現微小衛星三軸姿態被動穩定方案，對採用這三種方案的衛星的姿態運動進行詳細分國防科技大學研究生院學位論文析。
  17. An experimental study on the aerodynamic characteristics of new concept car is conducted by model wind tunnel test, covering the pressure coefficient and wake vortices on longitudinal symmetry plane, as well as aerodynamic forces and moments under different yaw angles

    摘要用模型風洞對新概念車在不同橫擺角下縱對稱面上壓力系數、整車氣動力和氣動力矩的變化以及縱對稱面尾部流態分佈進行了試驗研究。
  18. According to the theory of boundary layer control and aerodynamics of delta wing at medium attack angle, the generation mechanisms of rolling, pitching, yawing moments, which are produced by coupling between the microactuator array and boundary layer near the leading edge, have been discussed

    首先，結合空氣動力學的邊界層控制原理以及三角翼在中等攻角條件下的氣動特徵，詳細討論了微致動器陣列通過與前緣邊界層的耦合產生三角翼翻滾、俯仰和偏航等力矩的機理。
  19. This paper refers the figures and dates of some missiles in domestic and foreign, builds the aerodynamic date, engineer and rudders mathematic model, analyses the phenomenon of side jet interaction with external flow, builds a side jet model with append factor which conforms to the actual situation, and founds nonlinear mathematic model of this missile

    本文參考了國內外各型導彈的形狀和數據，建立了導彈空氣動力和力矩模型、發動機模型和作動器模型，並且研究了在側噴直接力控制時，側噴與外流場的干擾效應，建立了更加符合實際情況的帶有附加增益的側噴模型。
  20. Load - simulator is a device developed to test the performance of rudder control system in the lab by simulating and applying air moment the rudder suffering. high performance load - simulator is in urgent need for the examination of newly developed aircrafts and control techniques

    負載模擬器是模擬飛行器等在飛行過程中舵面所受空氣動力矩的加載裝置，其功能是在實驗室條件下復現飛行器的舵面在空中所受的各種載荷，從而檢測其舵機驅動系統的技術性能指標。
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