姿態確定 的英文怎麼說

中文拼音 [zītàiquèdìng]
姿態確定 英文
attitude determination
  • 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
  • 確 : 形容詞1. （符合事實; 真實） true; reliable; authentic 2. （堅固; 堅定） firm
  • 定 : Ⅰ形容詞1 （平靜; 穩定） calm; stable 2 （已經確定的; 不改變的） fixed; settled; established Ⅱ動詞...
  • 確定 : 1. （明確地定下） define; fix; determine; ascertain 2. （明確而肯定） definite; certain; for sure
  1. In the base of rigid body kinematics, the equations of attitude computation was developed via the imu sensor ’ s output, and a new method of the integrated attitude determination using gyroscope ’ s dynamic output and accelerometer ’ s static output was presented

    基於剛體運動學，本文給出了由慣性測量單元的輸出所確定的氣浮臺姿態解算方程，並提出了利用陀螺儀的動態輸出與加速度計的靜態輸出進行組合的姿態確定方法。
  2. This thesis has researched the design and control of a new triaxial air - bearing experimental system. in this thesis, the attitude determination and the attitude dynamics and control of the system was focused on

    本文對新型的三軸氣浮轉臺進行了設計與控制研究，重點研究了系統的姿態確定及動力學與控制問題。
  3. The high precision flight attitude of spacecraft has been mainly received through star sensor. the priciple is that at first the star acts as reference and the stars image has been captured by star sensor, then stars image identification and attitude estimation have been done, at last the flight attitude of spacecraft has been received

    航天器的高精度姿態確定主要是通過星敏感器來完成的，首先是以恆星為參照物，利用星敏感器得到星圖，然後進行星圖圖像處理、星圖識別和姿態估算等一系列計算，達到確定出航天器的飛行姿態的目的，而星圖處理是星敏感器處理的基礎。
  4. The result shows that the solar radiation pressure moments play a mainly part. based on kalman filtering, three kinds of attitude determination algorithms were studied using the attitude sensor now available on the explorer : the first based on digital solar sensor ( dss ) and gyroscope when the star sensor is not available ; another based on dss, high - gain antenna ( hga ) and gyroscope when the explorer is in the earth - safe mode ; the third based on star sensor combined with gyroscope when the explorer is in the normal mode

    針對配置了典型測量敏感器的深空探測器，基於擴展kalman濾波給出了其姿態確定的方法:針對星敏感器不可用情形，給出了使用太陽敏感器和速率陀螺定姿的濾波器演算法;針對安全模式下的對地穩定定向情形，給出了太陽敏感器和高增益天線融合速率陀螺信息的定姿演算法;針對正常巡航模式給出星敏感器和速率陀螺聯合定姿演算法。
  5. Chapter studies attitude determination problem by multi - antenna. the coordinate system and ad - algorithm is introduced firstly

    第三章研究衛星導航系統中多天線姿態確定問題。
  6. In the attitude determination experiment, star sensor hardware is introduced into the control loop to correct the gyro bias. in the attitude control experiment, firstly using reaction thrusters to perform large - angle slew and then

    姿態確定實驗中引入星敏感器實物到控制迴路中對陀螺數學模型中的漂移進行修正;姿態控制實驗中先進行噴氣大角度控制後用飛輪進行穩定控制。
  7. 3. carry out the simulation of the kalman filter based on the gps / magnetometer attitude determination system and the ins / cns / infrared earth sensors attitude determination system. the results show that it can improve attitude determination accuracy by fusion theory

    3 .利用聯邦kalman濾波演算法分別對採用gps 、磁強計和採用慣性陀螺、紅外地平儀、星敏感器的兩種衛星姿態確定方案進行了建模和模擬。
  8. In order to test the performance of the attitude determination and control methods presented in this thesis, the whole simulation loop of the small astronomical satellite ' s adcs was constructed

    3 ）為了充分驗證本文提出的姿態確定和控制方法的效果，本文的最後建立了svom衛星姿控系統大迴路模型，並編寫了相應程序，進行了數學模擬。
  9. Secondly, the static aeroelastic problems and jig - shape design, as a kind of multi - disciplinary design optimization ( mdo ), are investigated for sweep wing and super - critical wing. numerical results are in good agreement with other reference data. the method and the program presented in this paper are verified

    分別以某后掠機翼和超臨界機翼為算例，對機翼的靜氣動彈性問題以及基於靜氣動彈性的型架外形優化設計和飛行姿態確定進行研究，計算結果和有關文獻的結果進行了比較，吻合很好。
  10. The algorithm is tested by static and dynamic experiment. theory of attitude determination by gps is addressed in detial. error of attitude determination by gps is analyzed

    深入分析了gps姿態確定的原理，定性分析了gps姿態確定的各種誤差，在此基礎上提出了一種基於矩陣元素的卡爾曼濾波演算法。
  11. In this dissertation, the nonlinear filter methods are deeply studied on theory and application for the attitude estimation from vector observations of the three - axis stabilized satellite attitude measurement system. furthermore, for the shortages in extended kalman filter, several improved schemes are presented

    本文針對基於矢量觀測的三軸穩定對地定向衛星的姿態確定問題，從理論和應用兩個方面對衛星姿態確定的非線性濾波技術作了深入和細致的研究。
  12. This thesis took a small astronomical satellite as an example, deeply studied the attitude determination and control method for small astronomical satellites from both the theoretical and the engineering aspects

    本文以正在研製的一顆小型天文衛星? ? svom衛星的姿態確定與控制方案設計為背景，從理論和工程兩方面較為全面地研究了小型天文衛星的高精度姿態確定與控制方法。
  13. This dissertation takes system demonstration and validation of small satellites formation flying as the background, the theory and algorithms of relative attitude determination based on the gps like sensors are investigated ; the relative attitude coordinated control law, multi - agent based formation flying architecture and the coordination strategy are designed

    本文以「微小衛星編隊飛行演示驗證方案論證」為研究背景，深入研究了基於類gps相對測量的星間相對姿態確定方案和演算法，設計了編隊飛行衛星multi - agent體系結構與協同工作流程和策略及相對姿態協同控制演算法。
  14. Finally, image based asteroid lading navigation system structure is designed and numerical simulation is performed. the framework of the image navigation system is designed and functions of every subsystem are introduced. the simulation results suggest the navigation system proposed in this paper is feasible

    模擬結果表明基於圖像序列的自主導航系統的有效性和可行性，利用基於圖像序列的自主導航系統能夠有效地完成對導航相機的軌道和姿態確定任務，本文給出的系統設計是可行的。
  15. Case 1 : when there is no relative measurement, each satellite uses its own on - board attitude sensors to determine its attitude, and exchange the information through the communication link between formation satellites, and then the relative attitude is determined through simple mathematical operation. case 2 : based on the range measurements of gps like sensors, using two - point measurement of the relative orbit state to establish relative orbit and attitude kinematics and measuring equations. and state estimation is achieved through the extended kalman filter technology and unscented kalman filter technology, respectively

    方案一，在星間無相對測量時，由衛星自身攜帶的姿態敏感器實現單星高精度姿態確定，利用星間通信鏈路進行信息交互，通過簡單的數學計算獲得星間相對姿態;方案二，利用類gps相對測量，建立了編隊衛星相對軌道運動和相對姿態運動模型及相對距離測量方程，推導了兩點相對軌道運動模型，設計了擴展卡爾曼濾波器及uscented卡爾曼濾波器，對相對位置、速度和姿態進行估計。
  16. Satellite attitude determination with modified rodrigues parameters without gyro

    里格參數的星體姿態確定
  17. A micro - satellite attitude determination algorithm based on unscented kalman filter

    基於平淡卡爾曼濾波器的微小衛星姿態確定演算法
  18. A test platform for three dimensions attitude and relative attitude determination is established. the algorithms and the test platform is tested

    建立了gps三維姿態確定和編隊衛星相對姿態確定實驗系統，編制了姿態確定、相對姿態確定軟體。
  19. The research on fault diagnosis and system rebuild technology in satellite attitude control system : the intelligent and independent algorithms about fault diagnosis and system rebuild technology in satellite attitude control system are put forward

    衛星控制系統故障診斷與系統重構技術研究：提出了基於聯邦濾波結構的衛星姿態確定系統智能自主故障診斷與系統重構方案和演算法。
  20. The simulation results showed the methods represented in this thesis were effective and feasible

    模擬結果證明了本文提出的svom衛星姿態確定和控制方法的有效性和可行性。
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