attitude disturbance 中文意思是什麼

attitude disturbance 解釋
姿態擾動
  • attitude : n. 1. 姿勢，身段。2. 態度，看法。3. 【軍事】飛行姿態。4. 芭蕾舞的一個姿勢。
  • disturbance : n. 1. 動亂，變亂，騷亂。2. 煩悶；（心情）紛亂；（身心）失調。3. 【無線電】干擾；【氣象學】擾動；【地質學；地理學】（地殼的）局部運動。4. 【法律】侵犯（權利），妨害（治安）。
  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. To overcome this problem, the author researching from the core of active disturbance rejection control theory " fal function ", having the advantage of : small errors, large gains ; big error, the small gains character, designs a nonlinear pid gesture controller. simulation results showed that the design of nonlinear pid controller shortening the small satellite gesture catch time and improving the attitude control precision

    為了克服這個問題，本文從自抗擾控制理論中的核心「 fal函數」出發，基於fal （ e ， ， ）函數具有:小誤差，大增益;大誤差，小增益的特性，設計了一種非線性pid姿態控制器，比較好的縮短了小衛星姿態捕獲時間，一定程度上提高了姿態控制的精度。
  3. 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。
  4. 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。
  5. 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。
  6. The main work done in the paper is as follows : 1. satellite attitude dynamics modeling study : for the earth - oriented three - axis stabilized satellite, a precise attitude dynamics model is established, considering the influence of the environmental disturbance, such as the gravity, the sun radiation, the earth magnetic field and the atmospheric resistance

    本文的主要研究工作如下： （ 1 ）衛星姿態動力學建模研究：針對對地定向三軸穩定衛星，考慮了重力梯度、太陽輻射、大氣阻力、地球磁場等環境因素對衛星的影響，建立了較精確的衛星姿態動力學模型，同時又建立了四元素描述的姿態運動學方程。
  7. 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。
  8. 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。
  9. Algorithm research of the early - warning satellite attitude control under the payload disturbance is a critical technology of ballistic missile early - warning system

    預警衛星在其有效載荷干擾作用下的姿態控制演算法研究是彈道導彈預警系統的一項關鍵技術。
  10. In the article, a self - learning stochastic method based on the statistical pattern recognition is presented for attitude control under the disturbance of blind mixed gaussian white noises

    摘要本文提出一種基於統計模式識別，針對盲混合高斯白噪聲干擾下衛星姿態控制的方法。
  11. The nonlinear h and h2 / h control theories are applied to solve the problem of robust h control and the problem of disturbance almost decoupling of the rigid body attitude systems and the robot systems to verify the rationality and the validity of the results proposed in this dissertation

    應用非線性h _和h _ 2 h _控制理論解決了剛體姿態系統和機器人系統的h _控制問題、干擾近似解耦問題等，驗證了論文有關結論的合理性和有效性。
  12. The satellite attitude backstepping controller is designed. in order to compensate the disturbance of infrared camera, a compounding feedforward controller is proposed basing the momentum conservation

    基於動量守恆定理，設計了用於補償紅外相機干擾作用的前饋控制器，從而提出預警衛星姿態的反饋-前饋復合控制方法。
  13. Simulation result indicated that predictive filter of the dynamics model may be followed the attitude movement, if disturbance moment is time variable and large relative to gradient moment of gravity, and predictive filter based kinematics is suitable if there is no information about dynamics

    在有較大時變干擾力矩情況下基於動力學模型的預測濾波演算法能夠很好地跟蹤姿態變化，而在對系統模型一無所知，系統動態不高的條件下利用基於運動學的預測濾波演算法可以得到較好的姿態估計。
  14. 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。
  15. Using quaternion as attitude representation, the attitude kinematics function is established. 2. several kinds of disturbance torques affecting the satellite attitude are directly computed through the models described in the paper, forming a closed loop stabilization system dumped by magnetic torques and provided with initial torques through flywheels, but other simulations only estimate it by experience

    （ 2 ）很多模擬是根據經驗估算衛星所受的干擾力矩，本文以某對地觀測小衛星為背景，利用所建力學模型對衛星所受數種干擾力矩進行計算，形成了一個以飛輪作為主動力矩、通過磁力矩卸載的閉環而且穩定的姿態控制系統。
  16. 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。
  17. 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。
  18. The system based on pid control theory has characteristics of fast response speed and higher peak overshoot, and it also has a good performance of tracking, but it is lack of ability of disturbance rejection. because smvs control method is insensitive to the variations of the model parameters, nonlinear and exterior noises, the attitude stabilization system designed based on smvs has fast response speed, higher ability of disturbance rejection and has no peak overshoot, namely, the system is robust

    模擬結果表明，基於pid控制規律設計的系統具有響應速度快但超調大的特點，系統的跟蹤性能較好，但抗干擾能力較差；滑模變結構控制方法因為其對模型參數的變化、非線性和外擾噪聲的不敏感性，設計的聲納基陣姿態穩定系統無超調，響應速度快而且抗干擾能力強，具有很好的魯棒性。
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