姿態角速度 的英文怎麼說

中文拼音 [zītàijiǎosùdù]
姿態角速度 英文
attitude angular velocity
  • 姿 : 名詞1. （容貌） appearance; looks; mien; aspect 2. （姿勢） gesture; carriage; bearing
  • 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
  • 角 : 角Ⅰ名詞1 （牛、羊、 鹿等頭上長出的堅硬的東西） horn 2 （古時軍中吹的樂器） bugle; horn 3 （形狀像...
  • 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
  • 速度 : 1. [物理學] velocity; speed; blast; bat 2. [音樂] tempo3. （快慢的程度） speed; rate; pace; tempo
  1. Many factors were considered in the algorithm such as the helicopter nonlinear flight dynamic model, the time delay of rotor wake, the air compressibility at advancing blade, the stall of retreating blade, the unsteady flapping motion of rotor blades and the aerodynamic interaction among rotor, fuselage, tail rotor and empennage

    根據這一方法可以確定為完成直升機機動飛行所需的駕駛員操縱輸入及直升機的飛行速度、角速度和飛行姿態的變化歷程。
  2. Using coordinate transformation method, the formula of imv on every point of image plane was deduced, and it included almost all motorial factors : the flight velocity of aircraft, roll, pitch, yaw, camera ' s scan and so on. thus, it is a precise formula, and it is also applied to frame cameras and push _ room cameras with array ccd

    利用坐標系變換的方法可推出像面上各點的像移速度公式，該公式包含了幾乎所有的運動因素：飛機的前向飛行、飛機的姿態角變化、相機自身的擺掃運動等等，是精確的像移速度公式。本公式同樣適用於畫幅式航空相機和線陣ccd推掃型航空相機。
  3. Least squares solution of equation is used to calculate and adjustment transformation matrix at same time, transformation matrix is used to calculate the 3 - axis angle of star sensor. so is very fast and precise

    利用方程組的最小二乘解求取轉換矩陣，通過轉換矩陣計算星敏感器的三軸姿態角，使姿態計算和平差同時進行，具有較高的姿態計算精度和計算速度。
  4. 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。
  5. Abstract : this paper introduces the principles of doppler radar signal processing method in the modulation. it provides the processing method for projectile tracer time, the burst time, rocket engine working time, projectile spin and flight attitude from signal of doppler radar

    文摘:介紹了測速雷達調制域彈道信息處理方法的工作原理，詳細論述了從測速雷達信號中處理彈丸曳光時間、底排燃燒工作時間、火箭發動機工作時間、彈丸旋轉速度、飛行姿態角和擺動周期等彈道信息的方法。
  6. Error analysis on getting inertial angular position with linear accelerometers is improved

    改進了對線加速度計測量慣性姿態角的誤差分析。
  7. Theory of getting inertial angular position from linear accelerometer measurements with double integration algorithm is analyzed

    分析了使用線加速度計測量慣性角加速度，通過二次積分演算法得到慣性姿態角的原理。
  8. The results of simulation given in this paper indicate that the sins / dtu can effectively improve on the following navigation parameters : velocity, latitude and longitude, yawing and attitude angle, position of track - reckoning etc

    模擬結果表明，該組合導航系統可有效地減小速率、經度和緯度、航向角和姿態角及航跡推算下的位置等導航參數的累積誤差。
  9. When the signal of gps is lost for five minutes, the position error is about 1400 meters, its velocity error is about 15m / s and its attitude angle error is about 10 degree

    在gps信號丟失5分鐘時，位置誤差大約為1400米，速度誤差大約為15米/秒，姿態角誤差大約為10度。
  10. Using piezoresistive accelerometers and magnetoresistance sensors measure the dynamic acceleration and geomagnetic field and through avr mcu software to calculate the attitude angular and azimuth. the fact of affecting the module is discussed in detail in this report and put forward the resolving scheme of key technology of digital filter, linear compensation, temperature compensation and magnetic field adjustment. the digital module has advantages of small size, light weight, low conception, high accuracy, all solid state and high reliability

    本課題採用壓阻式加速度計和磁阻傳感器分別測量重力加速度和地磁場，通過avrmcu軟體解算出姿態角和方位角，課題詳細分析了影響模塊性能指標的因素，就數字濾波、線性補償、溫度補償、磁場修正等關鍵的技術問題提出了可行的解決方案，研製的數字化模塊具有體積小、重量輕、低功耗、精度高、全固態、高可靠等特點，所有性能指標均滿足設計要求，為姿態角測量提供了有效的手段。
  11. Traditional inertial mechanized - platform uses velocities to damp the system attitude to improve the precision of attitude, when the system acceleration is small. referring to the idea, this paper designeda damp kalman filter in strap - down attitude heading reference system ( ahrs ). the new method makes use of 3 - d accelerometer ' s measurements to estimate the system attitude, which is measured to compensate attitude errors. because the acceleration affected the precision of fiher directly, the fuzzy adaptive system was presented. the fuzzy logic inputs are three accelerations and the output is to control the measurement noise covariance matrix. simulations and experimental results prove that the damp algorithm can damp most of schuler oscillation and foucauh oscillation, so that to assure the filter convergence and efficiently improve the precision of strap - down ahrs

    在系統機動性不強的情況下，傳統的平臺內阻尼演算法將系統本身的速度信息通過阻尼網路加到系統中，達到提高姿態角精度的目的.將這種平臺內阻尼的思想引入到捷聯慣性航姿系統中，在系統加速度較小的情況下，利用加速度計的輸出估計系統姿態角，通過卡爾曼濾波的形式補償系統姿態誤差.由於加速度的大小直接影響濾波器精度，本文設計了模糊自適應卡爾曼濾波演算法，根據三軸加速度計的輸出調整內阻尼量測誤差方差陣，從而避免了濾波器的發散.模擬和實驗驗證，內阻尼演算法可明顯抑制舒勒周期振蕩和傅科周期振蕩，避免了系統姿態漂移，有效提高了捷聯慣性航姿系統的精度
  12. The results indicate that : with sa, the position precision of the integrated system, whose gyro drifting is 50 degree / hour and whose accelerator offset is 0. 001g, is 60 meters, its velocity precision is about 1. 75m / s out and its attitude angle precision is about 0. 25 degree. without sa, the position precision is about 20 meters, its velocity precision is about 0. 5m / s and its attitude angle precision is about 0. 1 degree. when the signal of gps is lost, the growing rate of the integrated system error is much lower than that of sins system

    模擬結果表明：對于陀螺漂移為50度/小時、加速度計零偏為0 . 001g的組合系統，在有sa的情況下，位置精度大約為60米，速度精度大約為1 . 75米/秒，姿態角精度大約為0 . 25度；在無sa的情況下，位置精度大約為20米，速度精度大約為0 . 5米/秒，姿態角精度大約為0 . 1度；在gps信號丟失時，系統誤差的增長速度比純sins系統明顯減緩。
  13. Finally, the motion stability of the flexible deployable truss mentioned before was analyzed. according to the definition of motion stability, the simulation results under the conditions of different initial attitude angle velocities and pulse torque function indicate that the deployment motion of flexible truss under these initial distortions was steady. the drive angle velocity of deployment

    根據無擾運動的穩定性定義，通過對衛星在不同初始姿態角速度下及受到力矩脈沖作用下展開時衛星的姿態角速度的影響的比較，說明在這兩種初始擾動下桁架的展開運動的穩定性情況;對不同驅動角速度下桁架展開的模擬結果比較得到該桁架的失穩條件。
  14. The rigid and flexible trusses were simulated respectively. the dependences of the attitude angle degree and angle velocity of the spacecraft on the rigid and flexible situation in the deployment process and drive velocities loaded on the joints were derived. the frequency - amplitude characteristic curves were gained from the attitude angle velocity curves of the deployment of the flexible truss and locked flexible truss after deployment through the fast fourier transition ( fft ) method

    文中給出了展開前後的動力學固有特性;對展開過程中分別為剛性桁架和柔性桁架兩種情況進行了模擬計算，對比了兩種情況的桁架展開過程中衛星姿態角及姿態角速度的變化;比較了柔性桁架不同展開速度對衛星姿態角及姿態角速度的影響;分析了柔性桁架展開過程對衛星非展開方向的姿態角度及角速度的影響及原因;對柔性桁架展開過程中及展開鎖定后的衛星姿態角速度的變化曲線進行快速傅立葉變換，得到柔性桁架展開過程即展開鎖定后衛星姿態角速度的頻幅特性曲線。
  15. By comparing the ideal joint and clearance joint for the deployment process of a spatial deployable truss structure in multibody dynamics, it is found that the existence of the joint clearance makes the movement discontinuous, and also found the attitude angle degree and angle velocity of the spacecraft are affected in the deployment for the joint clearance

    通過對有無鉸接間隙的剛性空間展開桁架模型的計算結果比較，說明鉸接間隙的存在對于桁架展開過程的影響及這一過程對衛星的姿態角速度的影響，同時比較了有無鉸接間隙時鉸接處在展開過程中接觸力的變化。
  16. The table is a important device in the hardware - in - the - loop simulation system, and it simulates the flight of unmanned aerial vehicle so as to achieve flying parameters from those sensors. the signals of sensors in the table are transmitted by many cables previously, thus it confines the movement range of the three - axis frameworks. as the perfomance of uav become complicated, the signals cables are replaced by wire rings in some tables, but it brings many difficulties and unreliable factors for the simulation table ’ s design also. bluetooth, as a new short - range wireless communication technology, is a reasonable and feasible scheme in this condition

    三軸模擬轉臺是無人機地面半實物模擬系統中的重要設備，用來模擬飛機在空中的姿態和角運動，以驅動傳感器產生飛行姿態、角速度及角加速度信號。早期轉臺上傳感器信號通過穿在框架中的電纜進行傳輸，這就限制了框架的運動范圍。隨著無人機任務的復雜程度不斷提高，出現了採用導電滑環傳遞信號的模擬轉臺，但這也給轉臺設計帶來了困難，且存在不可靠因素。
  17. Secondly, for satellite controlled by reaction wheels, an algorithm or strategy is presented. and then reaction wheels are used to generate a known disturbance torque, using thrusters as controller and gyro as the attitude sensor, a thruster parameters calibration for thruster levels and alignments on - line is achieved

    其次，針對反作用飛輪控制的衛星，提出了一種衛星質量特性在線辨識策略和辨識演算法，並利用反作用飛輪產生擾動力矩，推力器作為控制執行機構，使用陀螺測量衛星姿態角速度，實現推力器推力大小和方向等參數的在線辨識。
  18. In one methods, the attitude dynamics is used only to propagate the attitude rate

    其中一種方法是採用姿態動力學模型進行姿態角速度的遞推。
  19. Asymptotical stabilization of anglular velosity of a rigid spacecraft with two - dimensional complete configuration

    二維完整配置下剛性航天器姿態角速度的漸近鎮定
  20. Two extended kalman filters for star sensor based attitude and attitude rate determination are derived

    研究了兩種基於星敏感器的姿態和姿態角速度確定的擴展卡爾曼濾波演算法。
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