姿態坐標系 的英文怎麼說

中文拼音 [zītàizuòbiāoxì]
姿態坐標系 英文
attitude frame of reference
  • 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
  • 標 : Ⅰ名詞1 [書面語] （樹梢） treetop; the tip of a tree2 （枝節或表面） symptom; outside appearance; ...
  • 系 : 系動詞（打結; 扣） tie; fasten; do up; button up
  1. 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。
  2. The coordinate systems and time systems are described in detail at first, then the paper presents the whole algorithm containing line of sight generation and projection attitude data combination scan mirror calibration, find corresponding grid cell, resample. at the same time, scan gaps and detector delays are analyzed in detail

    論文首先對校正過程中用到的時間系統和坐標系統作了介紹，然後給出了完整的校正演算法，包括視線產生和投影、姿態合成、掃描鏡校正、尋找校正圖像空間像素到未校正圖像空間的對應像素位置、重采樣這幾個部分，並在相鄰掃描行間隙的插值上採用了簡潔的方法。
  3. On the condition of selecting east - north - up coordinate as navigation coordinate and supposing the updating periods for attitude, velocity and position all the same, the digital algorithms for sins are deduced in details

    以東北天坐標系為導航坐標系，假定姿態、速度和位置更新周期相同時，詳細推導了捷聯慣導的數字迭代演算法。
  4. According to flight dynamics, a particle model and an attitude model in launching coordinate system and in quasi missile body coordinate system are established, the influence imposed by constant wind, thrust bias of the motor and connection bias are analyzed

    應用飛行動力學理論，建立了發射坐標系與準彈體系下助推段和分離過程質點運動和姿態動力學模型，分析常風干擾、發動機推力偏差和裝配誤差影響等。
  5. Firstly, this paper presents the coordinates and time system for discribing satellite motion, and then gives the models of orbit and attitude and satellite relative motion, considered the j2 perturbation

    本文首先給出描述衛星運行所需的時間系統和坐標系，然後建立衛星軌道、姿態動力學模型和基於軌道根數的衛星編隊飛行相對運動方程，並考慮j2項攝動的影響。
  6. The main innovations done in the thesis are as follows : 1. the rotation effect of navigation coordinate is well compensated in sins attitude algorithms. scrolling error compensation can directly be used in the position matrix update algorithms

    在捷聯慣導數字迭代演算法中，姿態演算法有效處理了導航坐標系旋轉的影響，利用位置矩陣求解位置的方法很容易地解決了渦卷誤差的補償問題。
  7. Fiber optic gyro ( fog ) inertial system provides angular velocity and acceleration measurement of measurement body along three axes, based on the attitude matrix refreshed by outputs angular velocity to transform the acceleration from the body frame to the earth frame, finally through acceleration integral we can get the position of the measurement body in the space. fog is popular in the navigation field for many advantages, such as wide dynamic range, high resolution and all solid components

    該測量方法利用捷聯式光纖陀螺輸出的角速度和加速度信息，測出運載體沿三個方向的加速度分量；再利用光纖陀螺輸出的角速率信號，不斷更新測量體的姿態轉換矩陣，將加速度分量用轉換矩陣更換到地理坐標系；最後經過計算機對轉換后的加速度信號積分運算分別可得到運載體在三維空間中的位置。
  8. Then the system can use automatic constraint violation stabilization method for differential / algebraic equations to get state, displacement, velocity, acceleration of multibody system in different time points under external force

    該系統採用絕對坐標方法自動建立多體系統動力學方程，其形式為微分代數混合方程，即euler - lagrange方程。利用約束違約自動穩定方法求得多體系統在外力的作用下姿態、位移、速度、加速度。
  9. At last the relatively attitude can be measured by the transformation between vehicle body coordinate system and the world coordinate system of n light points. the algorithm can be confirmed by the result of simulation

    最後利用n個光點在車體坐標系和世界坐標系下的坐標轉換，解出月球車的相對姿態，並給出了模擬結果。
  10. The landing site coordinate system is first defined from the image coordinates of three feature points obtained using an optical navigation camera and the distances from the spacecraft to each fp measured using a laser range finder

    首先利用特徵點的圖像坐標和探測器到三個特徵點的距離信息構建了著陸點坐標系，確定了探測器相對著陸點坐標系的位置和姿態。
  11. The third chapter involves some problems on attitude determination and integrity ambiguity resolving. using three formation flying satellites for an earth observation as an example, the forth chapter contains some problems about determination of inter - satellite position, attitude and time, by using high precise pseudo - ranging observation onboard pseudolites. the problems are the selecting of coordinate system and independent state parameters, the setting of observation equations, and the conversion of constellation ' s states

    第四章以三星編隊星座為例，討論利用擴展的高精度星間偽距觀測進行星間相對位置、姿態和時間參數確定的一些問題，包括：坐標系、獨立參數的選取、觀測方程的建立和星座狀態的轉換等。
  12. Study on strapdown inertial navigation system ( sins ) the concept, process and the already done work of initial alignment of sins arc introduced briefly. for selecting coordinate and deriving the error model, presenting some kinds of coordinate in the inertial navigation system ( ins ) ; the initial alignment of sins theory is introduced in detail ; the linear error model of moving base initial alignment of sins is derived, including analysis in characteristic and influence of system error of inertial apparatus.

    捷聯慣導系統的研究：首先概要介紹了慣導系統的相關知識，闡述了捷聯慣導系統的優點；分析了初始對準姿態確定的幾種坐標系，為建模定義了坐標系選擇和姿態矩陣；詳細研究了捷聯慣導系統的初始對準原理，推導並給出了捷聯慣導系統動基座初始對準的誤差方程，並分析了誤差特性以及慣性儀表誤差對系統誤差的影響；
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