姿態角 的英文怎麼說

中文拼音 [zītàijiǎo]
姿態角 英文
attitude angle
  • 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...
  1. Since the varies of gun attitude angle and the vertical vector of the homograph plane are one - to - one, all the elements of modulation gun can be transformed into the calculation of the vertical vector angle, which avoids the calculation accuracy loss of the traditional approach under the condition of the tiny attitude angle disturbance

    由於火炮姿態角變化與相應平面的法向量是一一對應的，從而可將調炮諸元轉化為法向量夾角來計算，這樣可避免傳統方案在微小姿態角擾動情形下導致的計算精度可能的損失。
  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. This method can save the space of memory and reduce the computation time. because only the parameters of scattering centers are stored and genetic algorithm is used to search for aspect angle, the method is very suitable for the employment in real - time and restrictive environment. in chapter 3, the architecture of mmw seeker is studied

    該方法以目標多散射中心理論為基礎，只需要存貯目標的三維散射模型參數，需要的存貯量較少；與常規的全姿態角匹配識別方法比較，基於目標散射模型的匹配識別方法，由於利用了遺傳演算法的全局尋優能力，計算量較小。
  4. 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。
  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 identification and compensation of the lever - arm effect in the shipboard inertial system are analyzed by which accurate measuring of roll and pitch angle is achieved

    4 、分析了艦載晃動基座條件下，桿臂效應的辨識補償與動態水平姿態角測量問題。
  9. 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。
  10. 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。
  11. 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。
  12. As for the 3d modeling, the respondent modeling method is anglicized according to the characteristics of various sceneries. the simplicity of drawing method is proposed by combine the method of displaying list, terrain segmentation and vertex removing, which fulfilled the real - time display of a great scale terrain. as to the second problem, the quantitative relationship of view body and visual angle is deducted based on the theory of mathematics, which resolves the problem of aircraft pose display with better visual effect in simulation. these display the author ' s creative works

    在前者中，針對于各種景物的特點提煉出了相應的建模方法，並提出了將顯示列表、地形分割和頂點刪除法相結合的地形簡化繪制方法，實現了較大規模地形的實時顯示；在後者中，作者從數學角度推導出了視景體和飛行姿態角的定量對應關系，解決了飛行姿態顯示的問題，通過模擬，獲得了較好的視覺效果。
  13. The procedure can not only resist the influence of outlying kinematic model errors, but also control the effects of measurement outliers. 9. the precise velocity can be determined respectively with precise positioning results, receiver raw doppler measurements and carri

    討論了gps姿態測量中模糊度解算、姿態角解算等問題，並基於非專業姿態測量接收機，給出了gps姿態測量的初步結果。
  14. Attitude angular sensor ( electronic compass ) is widely used in fields of aviation. space flight and navigation etc for navigational orientation and especially in the field of military, so the foreign countries are limited to export the high performance of digital module of attitude angular sensor to our country. the aim of research object is to manufacture the all solid state digital module of attitude angular to meet the requirements of multifields

    姿態角傳感器（電子羅盤）可廣泛應用於航空、航天、航海等需要導航定位的眾多領域，尤其在軍事領域得到廣泛應用，因此國外一直限制高性能姿態角數字模塊對我的出口，本課題研製的主要目的就是研製出全固態的姿態角數字化模塊以滿足我國多領域的需要。
  15. 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。
  16. The work of this paper include : 1. the 3 - d solid entities of the external store, a missile, and the aircraft are modeled with a commercial cad software

    在投放發射分離過程中，外掛物處于載機的近流場中，狀態和姿態角的變化可能很大。
  17. The mathematical model of attitude solving algorithm on high dynamic aircraft was established, and the method which used rotation vector algorithm to solve attitude angle was discussed, and the method was compared with quaternion

    摘要建立了高動態飛行器姿態解算的數學模型，探討了利用等效旋轉矢量法解算姿態角的方法，並與四元數法進行了比較。
  18. The method can eliminate the conventional fuzzy control system ' s steady - state errors and flutters. considering wind disturbance, the stabilized loop of pitch angle was designed and simulated with this method

    9採用帶優化修正函數無量化的模糊控制方法設計國產直九c海豚直升機的縱向姿態角穩定迴路系統。
  19. The kalman filter theory is introduced and the dynamic error vector equation of the initial alignment is derived at the first. using velocity error as exterior value of observation, maneuverable characteristic that is influenced with system ' s observability and its degree is studied at length by do amount of simulations and experiences. choosing output error of accelerometers and angle error of attitude as observation respectively and system observation model is derived, which is based on analyzing kalman filter theory

    首先介紹了卡爾曼濾波理論及相關技術，建立了系統卡爾曼濾波的狀態方程和觀測方程；首先採用速度誤差作為觀測值，詳盡的研究了系統機動特性對可觀測性和可觀測度的影響，並做了大量模擬實驗：通過對濾波原理的分析研究了影響的原因；分別選用加速度計輸出誤差和轉臺輸出姿態角誤差作為外部觀測值，推導建立它們的觀測模型，並通過模擬證明了分析結論的正確性。
  20. 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
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