active attitude control 中文意思是什麼
active attitude control
解釋
主動姿態控制-
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。 -
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。 -
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。 -
Active vibration control of flexible spacecraft during attitude maneuver
撓性航天器姿態機動的主動振動控制 -
In order to study small satellite attitude control system, the author first establishes the small satellite dynamics, kinematic models, and gives the theories of the quarternion, then study in - depth of the principles of the active magnetic control
為研究主動磁控小衛星姿態控制系統，首先建立了主動磁控小衛星動力學、運動學模型，並給出了姿態四元數的相關理論。從地磁場模型出發，深入研究了主動磁控的原理。 -
Based on the requirements of high precision pointing / targeting of advanced spacecraft, dynamic modeling of spacecraft with flexible appendages bonded with piezoelectric sensors / actuators, attitude control and active vibration suppression theory are studied deeply in this dissertation, which is funded by the research fund for the doctoral program of higher education of china item ? “ large flexible multi - bodies structure spacecraft active vibration control technology ” ( 20050213010 ). the main contents of this dissertation are as the follows : an approximate analytical dynamic model of a flexible spacecraft with surface bonded piezoelectric sensors and actuators is derived using hamilton ’ s principle with discretization by the assumed mode method. the model is then converted to state - space form for the purpose of control design
本學位論文結合高等學校博士學科點專項科研基金「撓性多體結構衛星主動振動控制技術研究」 （ 20050213010 ）課題，從理論上對粘貼有壓電智能元件的撓性航天器的建模、姿態控制和主動振動控制理論等展開了深入的研究，其研究內容主要包括以下幾個方面:利用hamilton原理推導了撓性航天器的動力學模型、壓電元件的作動方程及檢測方程，並採用模態分析方法，進一步將撓性航天器的耦合方程規范化，使之適應于姿態控制系統的分析和設計。 -
Active vibration control technique is the key technology of designing of attitude control system for large flexible spacecraft to fulfill mission requirements such as precision pointing and integrity of structures
航天器撓性結構的主動振動控制技術是大型航天器姿態控制系統設計的關鍵技術。
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