attitude controller 中文意思是什麼

attitude controller 解釋
姿態控制器
  • 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。
  • controller : n 1 管理人，主管人。2 （會計的）主計人，檢查員；〈英國〉（特指宮廷、海軍等的）出納官〈常作 comptr...
  1. 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。
  2. In this paper, we for the first time present an adaptive robust attitude controller which is robust to the disturbances and / or uncertaities in both the inertial matrix and the control matrix

    本文首次針對控制矩陣中的不確定性，採用自適應控制方法，得到了一種對上述兩種不確定性都具有魯棒性的自適應魯棒控制器。
  3. Answer : when the job permits a person to explain a safety precaution to working controller, every explain a measure, working license person should ask clear job chief and collectivity to whether the staff member already was clear about, clear, if work, the safety precaution that person of license of chief class job explains already listened clear, look clear, answer to permit a person to demonstrate an attitude to the job instantly, both sides affirms without by accident hind, the job permits a person to answer to draw " of of a " on this measure of working ticket, make a mark, leak in order to prevent

    答：工作許可人向工作負責人交待安全措施時，每交待完一項措施，工作許可人應問清工作負責人和全體工作人員是否已清楚、明白，如工作負責人班工作許可人交待的安全措施都已聽清，看明白，應立即向工作許可人表明態度，雙方確認無誤后，工作許可人應在工作票的該項措施上畫一個" " ，做一個記號，以防止漏項。
  4. To solve the problems caused by the varieties of the missile dynamics with the difference of flight height, velocity and attitude angle in modeling the missile, in this thesis, the theory of variable structure model reference adaptive control is used to design a pitch channel autopilot based on a longitudinal missile model, the status equation using the measurable parameters of load and angular rate is established, and the methodology to choosing the reference model is discussed also, and the performance of the controller is analyzed by means of simulation

    為了解決攔截彈氣動參數隨飛行高度、速度、姿態的不同，變化范圍大，控制系統難以準確建模的困難，基於縱向平面攔截彈模型，採用模型參考變結構控制理論設計了俯仰通道姿控復合控制系統，以可測量變量過載和角速度作為狀態量建立了系統的狀態方程，討論了參考模型的選擇方法，並對系統的性能作了模擬分析。
  5. A multiloop antenna pointing controller has been designed while three feedforward schemes are used in this control design. the simulation results show that the antenna pointing control system can improve the precision of the attitude angle and the attitude angle rate, and the antenna can slew to the neighborhood of tdrs fast, search and then track tdrs

    在設計好的天線跟蹤指向控制系統基礎上，採用前饋+反饋的復合控制策略設計了復合控制器，模擬結果表明設計的天線指向控制系統能夠較好的提高星體的姿態穩定度和控制精度，天線能夠快速回掃至中繼衛星附近並進行跟蹤，天線指向精度滿足設計要求，表明了所設計的天線指向控制系統的合理性和有效性。
  6. Deduce the mathematical model of satellite attitude control system and position / attitude control system respectively, then design tracking controller. the credibility and availability of the proposed control strategy is shown by theory and simulation

    分別推導了人造衛星姿態控制系統的數學模型和人造衛星位姿控制系統的數學模型，並進行指數穩定跟蹤控制設計，理論和模擬實驗證明了所提供的設計方法是行之有效的。
  7. 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。
  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. In the task space, the attitude space of the robot end - effector is parameterized by rodrigues parameters, and an output feedback controller without the generalized velocity is designed for controlling the position and attitude of the end - effector of a rigid robot

    利用機器人控制系統固有的無源性，在作業空間中，採用rodrigues參數描述末端執行器的姿態，設計了用於機器人末端執行器位姿控制的輸出反饋控制律，消除了控制器中的廣義速度。
  10. The small astronomical satellite has demands on both pointing accuracy and attitude maneuverability, so this thesis modeled the attitude control subsystem based on reaction wheels. under the fine precision pointing mode, a pd control law and a variable structure ( vs ) control law were studied respectively, and the simulation validated that vs control is more effective under fine precision pointing mode. furthermore, the vs controller for rapid large - angle maneuver was also designed

    2 ） svom衛星同時對指向精度和姿態機動性有著很高的要求，因此本文建立了基於反作用飛輪的svom衛星姿態控制系統模型，在高精度慣性定向三軸穩定模式下分別設計了pd控制律和變結構控制律，通過模擬驗證了變結構控制對于svom衛星的有效性，並基於變結構控制研究了svom衛星快速大角度機動的方法。
  11. The proposed control system includes the attitude controller acting on the rigid hub, designed by using pulse - width pulse - frequency ( pwpf ) modulation integrated with command shaping technique based on csvs method, and the piezoelectric material elements as sensors / actuators bonded on the surface of the beam appendages, designed by the optimal positive position feedback ( oppf ) control technique, in which the selection of ppf gains is determined via introducing a cost function to be minimized by feedback gains which are subject to the stability criterion at the

    設計的控制器僅利用輸出信息，從而避免設計撓性模態狀態觀測器以及引入狀態觀測器誤差;在此基礎上，採用分力合成方法設計命令成形控制器來抑制撓性附件的振動，設計的優化命令成形控制信號在理論上可以對系統的各階撓性模態完全抑制。但考慮到模型不確定性和外部擾動，在內迴路又設計了最優正位置反饋（ oppf ）補償器以增加撓性結構的阻尼，使撓性結構的振動能夠很快衰減。
  12. At the end of the dissertation, the fuzzy pd track tail controller is designed. the pd controller and controller of attitude angle are made up of flight control system of helicopter

    最後，本文設計了直升機模糊pd軌跡跟蹤控制器，與姿態角控制器相結合，完成了對整個飛行控制系統的設計。
  13. Finally, the trajectory tracking controller based on cm ac and pid parallel control is designed, which is combined with attitude angle controller and complete whole flight controller system

    本文最後設計了基於小腦模型神經網路（ cmac ）和pid并行控制的軌跡跟蹤控制器，與姿態角控制器相結合，完成直升機整個飛行控制系統的設計。
  14. In view of reasonable price, high productivity as well as compatible with round can production line, irregular - can forming machine is currently being pursued by many manufacturing companies, which indicates vast potential markets. attitude control and fuzzy controller adjustment are two key factors directly affecting the running stability and controlling precision of the irregular - can forming machine

    異形罐成形機由於造價適中、生產率高，並且能夠與圓罐生產線兼容等諸多優點，受到了國內許多生產廠家的一致看好，具有廣闊的應用前景。姿態控制與調整模糊控制器設計的好壞直接影響到異形罐成形機運行的穩定性和控制精度。
  15. In order to provide a basic and effective practical engineering tool for handling quality planning, analysing and evaluating, which is needed hi helicopter prototype development, this research work is launched on the fundation of comprehending the new aeronautical standard of united states army - ads - 33, and has obtained the achievements as following : ( 1 ) performance definition of pcs according to the criteria requirements for an explicit helicopter, beginning at analysis of its missions. ( 2 ) establishment of a helicopter attitude controller, which can meet the criteria requirements, by using the technology of adaptive neural network model - inverse control ; implementation of two response types ( rts ) and two control modes ; evaluation of quantitative parameters according to the ads - 33. ( 3 ) establishment of a helicopter trajectory contoller based on the attitude controller ; simulations of mission task elements ( mtes ) and evaluation of handling quality

    為了給型號研製中飛行品質的規劃、分析和評價提供基本的、有效的工程實用工具，本課題在充分消化理解美軍新航標ads - 33的基礎上，作了以下工作： （ 1 ）針對具體直升機，從任務分析入手，根據規范要求確定對飛控系統的要求； （ 2 ）應用自適應神經網路模型逆控制技術，構造了能夠滿足飛行品質要求的直升機姿態控制器，實現了兩種響應型式、兩種控制模式，並根據ads - 33進行了定量指標評估； （ 3 ）在姿態控制器的基礎上，構造了軌跡跟蹤器，進行了任務科目基元模擬和飛行品質評估。
  16. 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。
  17. The real - time accurate parameters are then transferred to the stochastic optimal controller by the self - learning system to control the attitude of satellites

    學習系統將干擾白噪聲參數的精確估計值傳送至隨機最優控制器以獲得精度優良的控制效果，通過模擬研究表明了方法的有效性。
  18. This thesis contains six chapters. the first chapter is introduction ; the second chapter is the proposal and resolution of attitude control ; the third chapter deals with the design method of attitude control system ; chapter four discusses matlab simulation and laboratory simulation ; chapter five involves self - tuning parameters for controller and its procedure ; the last chapter is conclusion

    第一章是緒論；第二章是姿態控制的提出與實現方案；第三章是模糊控制用於姿態控制系統的設計；第四章是matlab模擬與實驗室模擬；第五章是參數自整定模糊控制器及其實現；第六章是結論。
  19. 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。
  20. The sliding mode variable - structure controller basing attitude error quaternion and the sliding mode variable - structure controller basing adaptive learning on rbf neural network, three learning arithmetics of rbf neural network is emphasized

    針對衛星平臺分別設計了基於姿態誤差四元數的滑模變結構控制器和基於rbf神經網路上界自適應學習的滑模控制器。
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