姿態擾動 的英文怎麼說

中文拼音 [zītàirǎodòng]
姿態擾動 英文
attitude disturbance
  • 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
  • 擾 : Ⅰ動詞1 （擾亂; 攪擾） harass; trouble 2 （客套話 因受人款待而表示客氣） trespass on sb s hospital...
  • 擾動 : excitation; turbulent motion; turbulence; destabilization; [物理學] perturbation motion; [地質學]...
  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. So, researching the manned spacecraft attitude disturbances induced by the astronaut ’ s intravehicular activities is of great theoretical and practical significance

    因此，研究航天員艙內活動對載人飛船姿態的擾動影響具有重要的理論與實踐意義。
  3. The aerodynamic parameters are calculated under dynamic condition. according to the position and the posture of the bomb, the parameters are calculated every short interval until it leaves the interfere area

    本文採用了在動態條件下求解航彈氣動力的方法，每隔很短的一個時間間隔就根據彈體的位置和姿態重新計算其氣動力參數，直至航彈脫離機翼、機身的干擾區。
  4. Secondly, at the premise of the basic hypothesizes, establish the “ astronaut - spaceship ” system dynamics equations based on the principle of momentum conservation, and simulate the disturbance influence of the spaceship attitude induced by five kinds astronaut ’ s motion include stand - up act, landing act, right arm single - pendulum motion, left arm double - pendulum motion, right arm operating panel motion

    其次，在基本假設的前提下，基於動量矩守恆原理建立了「航天員?飛船」系統動力學方程，並模擬分析了起立動作、停靠動作、右臂單擺運動、左臂雙擺運動和右臂操作儀錶板五類航天員運動對飛船的姿態的擾動影響。
  5. Firstly, under the assumption that the output driving torque generated by the stepper motor of the mirror is constant, such influence analysis is conducted. secondly, a mathematic model of the stepper motor is given. under the assumtion that the input impulse frequence is constant, the rotational motion of the stepper motor of the mirror with the mutual exertions of damping torque, friction torque and disturbance torque generated by satellite platform ' s attitude motion is simulated and analyzed

    對衛星平臺姿態振動對紅外相機掃描機構轉動的影響進行了系統深入的模擬分析:首先在步進電機驅動力矩一定條件下，模擬分析了星體姿態運動干擾力矩對紅外相機掃描鏡轉動的影響;接著建立了步進電機的數學模型，在步進電機輸入脈沖頻率一定條件下，模擬分析了步進電機在阻尼力矩、干摩擦力矩、平臺干擾力矩等負載轉矩的共同作用下的轉動情況。
  6. Nevertheless, some manned flight mission requires the spacecraft has high pointing and stabilizing precision. so, it needs us to quantitatively analyze the astronautic disturbances, so as to evaluate flight mission and guide or improve spacecraft system design especially the attitude control system design

    有的載人飛行任務需要航天器具有很高的指向精度和穩定度，這就需要對航天員的擾動進行定量分析，以便對飛行任務進行評估並能指導或改進航天器系統設計特別是姿態控制系統的設計。
  7. The aim of this article is to shorten the gesture capture time and to improve control precision. author from both theoretical and applied researches the using of a nonlinear active disturbance rejection control technologies in small satellite gesture capture system

    本文以縮短主動磁控小衛星姿態捕獲時間，提高控制精度為目標，從理論和應用兩個方面深入研究了非線性自抗擾控制新技術及其在主動磁控小衛星姿態控制系統中的應用。
  8. In one aspect, the influence of various disturbances upon satellite ' s attitude motion is studyed by simualtion

    模擬分析了各種干擾作用下星體的姿態運動情況。
  9. Through it the author made a deep study of the satellite attitude control subsystem, verified several sorts of disturbance torques and realized satellite three - axis attitude stabilization control and attitude maneuver under different conditions

    本文在simulink下對衛星姿控系統作了比較深入的研究，對各種干擾力矩進行了驗證，同時在不同的模擬條件下實現了衛星三軸穩定控制、姿態機動和飛輪的磁卸載。
  10. This paper studies on the attitude ontrol system of three - axis stabilized satellite systematically, and makes deep study on the design of attitude control system. the main work of this paper is as follows : first, found whole mathematical model about attitude control system of satellite. it contains kinematics model, dynamic model, actuator model and torque model. analyse the conmmen characteristic of actuator of satellite ’ s attitude control system

    本文較為系統地研究了三軸穩定衛星的姿態控制系統，並在姿態控制規律的設計方面進行了較為深入的研究。論文主要工作如下:首先，建立了完整的衛星姿態控制系統的數學模型。其中包括星體運動學模型、星體動力學模型、執行機構模型及環境干擾力矩模型。
  11. On the base of active disturbance rejection control, author use active disturbance rejection control in small satellite attitude control system and designs a two - loop active disturbance rejection attitude control system

    在深入研究了自抗擾控制理論的基礎上，將自抗擾控制新技術應用於主動磁控小衛星姿態控制系統中。
  12. The new adrc technique was concluded from the related references in recent years, and the adrc theory was systemically introduced, which included tracking - differentiator ( td ), extended state observer ( eso ), nonlinear pid, nonlinear feedback ( nf ) and active disturbance rejection controller ( adrc ), and etc. the author first designs a pd attitude control system, indicating : using pd attitude control, the time of small satellite gesture capture is long and the precision of control is low

    從近幾年有關文獻中總結了自抗擾控制新技術，系統介紹了自抗擾控制理論，其中包括跟蹤微分器（ td ） 、擴張狀態觀測器（ eso ） 、非線性pid 、非線性反饋（ nf ）和自抗擾控制器（ adrc ）等。設計了主動磁控小衛星pd姿態控制系統。指出採用pd姿態控制，微小衛星姿態捕獲時間較長，姿態控制精度較低。
  13. 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。
  14. Through the approximate handling of geomagnetic intensity and differential riccati equation, the magnetic attitude h control law of the microsatellite in a circle orbit which has external disturb and the structural perturbation is presented

    通過對衛星地磁場和微分riccati方程進行近似處理，給出有外界擾動和結構化攝動圓軌道衛星系統的h _磁姿態控制規律。
  15. This paper provides a powerful method for the compatibility design of aircraft with external store, a missile, by calculating fast, conveniently and effectively the relative trajectory and relative attitude of the store with respect to aircraft during the separation process

    此外，為了有效擊中目標，需要掌握投放初始階段外掛物姿態和運動軌跡數據。因此，研究機載發射過程中的彈機氣動干擾力，考慮其對導彈發射后的彈道模擬初始參數的影響十分必要。
  16. 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。
  17. Both results show that the inertial coupling of the platform to infrared camera scanning mirror, to evaluate mirror motion, is negligible and so the mirror can perform scans of the earth at the specified angular rate

    兩方面的模擬分析表明:星體姿態運動干擾力矩對紅外相機掃描鏡轉動影響很小，紅外相機掃描鏡能夠按設計轉速正常運行。
  18. The air bearing is the most important part of an attitude control system simulator for simulating a satellite moving in the weightless circumstance. performance of a satellite attitude simulation system based on air bearing is decided by the inertia matrix and gravity disturbance torque arising from a difference between mass center and rotation center, and air bearing can be used to simulate the algorithm of on - line mass - property parameters identification on the ground. so the problem of mass - property and gravity disturbance torque identification for satellite and air bearing is studied in this thesis

    氣浮臺能夠模擬衛星在軌失重條件下的姿態運動，是衛星姿態控制系統物理模擬的核心部件，其轉動慣量和質心偏移引起的重力干擾力矩等決定了基於氣浮臺的衛星姿態物理模擬系統的性能，並且利用氣浮臺可以實現衛星質量特性在線辨識演算法的地面物理模擬驗證，因此本文對衛星和氣浮臺的質量特性及干擾力矩在線辨識問題進行深入研究。
  19. Lastly, establish the rigid - body spaceship attitude kinematics and dynamics equations, and primarily design the spaceship attitude law including limit loop parameters and two kind switch curves. analyze the astronaut ’ s disturbance moments. put the disturbance moments of typical astronaut ’ s push - off act as the input datas of the control system simulation, and analyze the response of the attitude control system after disturbed

    最後，建立剛體飛船姿態運動學及動力學方程，並對飛船姿態控制律進行了初步的設計，包括極限環參數的設計和兩類典型的開關曲線的設計;對航天員擾動力矩進行了分析;以典型的航天員推離動作對飛船的擾動力矩作為控制系統模擬的輸入參數，分析姿態控制系統受到擾動后的響應。
  20. The dissertation demonstrates the maneuvering target imaging model with acceleration and rotating motion and its signal processing to solve attitude perturbation of the targets

    針對機動目標存在的姿態擾動，研究了具有加速度和旋轉運動的機動目標成像模型及其信號處理過程。
分享友人
分享到 Line

分享到臉書