Conclusions : with the horizontal alveolar loss , the rotation center moved toward the apex and the capacity of periodontal support decreased significantly 結論:隨著牙周支持組織高度的逐漸降低,牙的旋轉中心向根尖移動,牙周支持組織對牙的支持能力明顯減弱。
In succession , we should test whether the rotation center of the tri - eccentric butterfly vavle was right , brought forward a method to test the seal fit interference , designed the program about the seal fit interference and gave the corresponding results which the program was run 對于三偏心蝶閥回轉中心的選擇是否合適,本文提出了一個檢查密封副干涉的方法,設計了相關的程序并進行了驗證,給出了程序運行的部分結果。
The paper analyzed the struture of the tri - eccentric butterfly vavle at length , defined the tri - eccentric butterfly valve , educed the geometry function and its characteristic about the section of the butterfly disc . the results indicate : the parallel contour line across butterfly disc thickness is normal ellipse , thereby eslablished function relations between its geometry parameters ( long axis and short axis ) of three primary sections of the butterfly disc and the tri - eccentricity ; in order to avoid interference between the butterfly disc and the valve seat as well as the valve body , combining the torque , we obtained the feasible range about the rotation center of the tri - eccentric butterfly vavle 本文主要分析了三偏心蝶閥的結構,給出了三偏心的定義,推導出了蝶板截面的幾何方程及其性質,結果表明,沿蝶板厚度的平行截面輪廓線為標準的橢圓形,進而推導出了蝶板幾個主要截面的幾何參數(長軸、短軸)與三個偏心之間的函數關系;考慮到蝶板啟閉過程中避免與閥體及閥座發(fā)生干涉,結合蝶板的啟閉扭矩,確立了三偏心蝶閥回轉中心的適宜區(qū)域。
Because it is impossible to adjust the air bearing absolutely balance , the difference between mass center and rotation center must lead to a notable gravity disturbance torque . in the process of identification , modeling and identification of gravity disturbance torque is considered , and an extended kalman filter is educed for identifying air bearing inertia matrix and gravity disturbance torque , and then the algorithm is validated 由于氣浮臺平衡調試方法和手段的限制,實驗過程中氣浮臺質心與轉動中心有一定的位置偏差,必將導致較大的重力干擾力矩,在辨識算法的推導過程中,重點考慮了重力干擾力矩的建模和參數辨識問題,推導了氣浮臺的轉動慣量和重力干擾力矩辨識的擴展卡爾曼濾波算法,并對算法進行了數學仿真和全物理仿真驗證。
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(wèi)星在軌失重條件下的姿態(tài)運動,是衛(wèi)星姿態(tài)控制系統物理仿真的核心部件,其轉動慣量和質心偏移引起的重力干擾力矩等決定了基于氣浮臺的衛(wèi)星姿態(tài)物理仿真系統的性能,并且利用氣浮臺可以實現衛(wèi)星質量特性在線辨識算法的地面物理仿真驗證,因此本文對衛(wèi)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。