姿態主動控制 的英文怎麼說
中文拼音 [zītàizhǔdòngkòngzhì]
姿態主動控制
英文
active attitude control- 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
- 控 : 動詞1 (告發;控告) accuse; charge 2 (控制) control; dominate 3 (使容器口兒朝下 讓裏面的液體慢...
- 制 : Ⅰ動詞1 (製造) make; manufacture 2 (擬訂; 規定) draw up; establish 3 (用強力約束; 限定; 管束...
- 控制 : control; dominate; regulate; govern; manage; check; cybernate; manipulate; encraty; rule; rein; c...
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To ensure the security of gi inspection, no approving method has been developed by far to drive the capsule endoscope but utilizing the natural peristalsis of gi tract. the uncontrollability of the capsule endoscope brings on some limitations in its functional extension in inspection, medication and surgery, such as temperature and ph measuring, medicament spraying, sampling, on - line sample analyzing, laser incising and rf cauterizing
膠囊內窺鏡目前還沒有實用的主動驅動方法,只能利用消化道自然蠕動作為膠囊內窺鏡前進的動力。由於膠囊內窺鏡不可控,限制了它的功能擴展,比如壓縮空氣噴藥、吸取組織樣品、在線樣品分析、激光切割、射頻燒灼等。完善的膠囊內窺鏡系統需要在現有基礎上加入安全有效的驅動控制,可調整姿態、行進及定位,從而擴大膠囊內鏡檢查的適應癥、安全性與多功能性。It include dynamic system which used to describe the motion of orbit and attitude of the space station, gnc system that describe the control of orbit and attitude of the space station system ; power system, that provide the power supply for the space station
其中:動力學子系統描述空間站運行的軌道和姿態運動, gnc系統主要描述空間站的軌道、姿態控制,電力系統主要描述空間站的電力供應情況。The precision of hitting will be improved obviously if we can offer a set of simple guidance control systems in powered phase of the rocket projectile
如果能在火箭主動段加一套簡易的控制系統來控制火箭的姿態,則將大大提高火箭的命中精度。Direct side force control ( dsfc ) comes into being with the appearance of act ( active control technology ). through maneuvering the vertical canard to produce side force, people can control a aircraft easily. so the trajectory of a vehicle can be controlled precisely, and it ' s maneuverability is greatly improved
直接側力控制是隨著主動控制的提出而出現的,採用直接側力控制,可在不改變飛機姿態的條件下,直接通過控制面造成側力來操縱飛機機動,從而達到精確控制飛行軌跡和增強機動能力的目的。This paper was based on robocup legged - robot group which uses sony aibo robot as experimental object. with the platform of gt2004 published by germanteam in 2004, combining the image information taken by the robot ’ s own camera with recent self - localization approach, the paper implemented real - time localization process under the real dynamic environment and met the need of robocup new rules. on the condition of wireless network communication and accurate pose estimation, the dynamic role assignment and coordination among multi - agents became possible
本文基於robocup四腿機器人足球比賽,以比賽組委會指定的aibo機器狗為實驗對象,以國際robocup2004四腿機器人足球比賽冠軍德國隊公布的gt2004為研發平臺,為適應新的比賽場地和比賽規則,主要運用自主體本身所採集的圖像信息,結合最新的圖像處理手段和自主定位演算法,從而估算出自主體在動態特徵比賽環境下的實時位姿,並藉助無線網路通訊手段和自主定位的結果,實現多自主體的動態角色分配和協調控制過程。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。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。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。Based on chinese tracking and data relay satellite ( ctdrs ) in the future, the antenna pointing control and complex control theory of user satellite are studied deeply in this dissertation, which is funded by the improve item of dept. of astronautic engineering and mechanics ? “ the teaching demonstration of antenna pointing control system in tdrss ”. the main contents of this dissertation are consisted of the following parts : firstly, dynamics equation is derived using lagrange equation for user satellite, so as the kinetics equations of user satellite at the same time are expressed in the form with matrix differential equations that is suitable for attitude control system design and analysis
本學位論文結合航空宇航科學與技術學科研究生教學基地實驗室建設項目「中繼系統星間鏈路天線指向控制系統教學與演示實驗」 ,以我國跟蹤與數據中繼衛星系統為背景,對某型號用戶星星間鏈路天線指向跟蹤控制和復合控制理論進行深入的研究,研究內容主要包括以下幾個方面: 1 .利用lagrange方程建立了用戶星的動力學方程,同時推導了運動學方程,並將這組動力學方程以矩陣微分方程形式表示,使之適用於姿態控制系統的設計和分析。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These efforts will lay a foundation for landing man on the moon and establishing lunar base. for the unmanned lunar rover work safely in a long enough time in complex environment of lunar surface, a good navigation system is needed to supply position and pose message in real time to support automatic navigation and remote control
與其它類型的移動機器人一樣,無人月球車要在月球表面的復雜環境中長時間安全地運行,需要導航系統實時提供位置和姿態的信息作為控制月球車的自主導航或地面遙控的條件,以確保它在這一環境中工作的安全性。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。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。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。In addition, the principle of component synthesis vibration suppressing ( csvs ) method is also briefly introduced and summarized to several lemmas, which can suppress flexible vibration by utilizing the character of vibration system itself and has the characters of simple, multiform, easy to apply and so on
另外,為了將分力合成方法應用於撓性系統的振動抑制,簡要地介紹了分力合成方法的一些基本概念及原理。針對採用推力器作為執行機構的撓性航天器姿態機動的振動抑制問題,提出了將分力合成振動抑制( csvs )方法和基於分佈壓電元件( pzt )的主動振動抑制技術相結合的一種復合主動控制方法。分享友人