【摘要】：在機(jī)械、航空、航天、兵器、機(jī)器人等領(lǐng)域中存在著大量的變結(jié)構(gòu)動(dòng)力學(xué)問題,變結(jié)構(gòu)多體系統(tǒng)動(dòng)力學(xué)日益成為當(dāng)今力學(xué)領(lǐng)域的研究難點(diǎn)與熱點(diǎn)之一。變結(jié)構(gòu)多體系統(tǒng)動(dòng)力學(xué)問題最主要的特征就是系統(tǒng)在運(yùn)動(dòng)過程中結(jié)構(gòu)會(huì)發(fā)生突變,即拓?fù)浣Y(jié)構(gòu)與自由度會(huì)發(fā)生突變。結(jié)構(gòu)的突變使得傳統(tǒng)的多體系統(tǒng)動(dòng)力學(xué)仿真軟件在處理這類問題時(shí)存在著一定的局限性,無法實(shí)現(xiàn)拓?fù)浣Y(jié)構(gòu)的自動(dòng)切換。本文針對(duì)多體系統(tǒng)變結(jié)構(gòu)問題的特點(diǎn),將"分路"思想引入到變結(jié)構(gòu)動(dòng)力學(xué)問題中,采用"自由度最大化"法實(shí)現(xiàn)了系統(tǒng)結(jié)構(gòu)的"虛擬穩(wěn)定",進(jìn)而實(shí)現(xiàn)了仿真過程中拓?fù)浣Y(jié)構(gòu)的自動(dòng)切換功能,極大地提高了仿真軟件的計(jì)算效率與連續(xù)性。從而使得仿真軟件能夠?qū)崿F(xiàn)變結(jié)構(gòu)多體系統(tǒng)動(dòng)力學(xué)的全局仿真。本文主要以變結(jié)構(gòu)火箭發(fā)射系統(tǒng)為研究背景,詳細(xì)描述了火箭發(fā)射系統(tǒng)中所遇到的幾類變結(jié)構(gòu)問題,建立了變結(jié)構(gòu)火箭發(fā)射系統(tǒng)的動(dòng)力學(xué)方程。最后,以某型號(hào)火箭發(fā)射系統(tǒng)為例進(jìn)行了動(dòng)力學(xué)仿真。以下幾個(gè)方面是本論文主要的研究內(nèi)容:1.研究了變結(jié)構(gòu)多體系統(tǒng)動(dòng)力學(xué)的建模理論。討論了多體系統(tǒng)中所遇到的變結(jié)構(gòu)問題,通過引入"自由度最大化"和"分路"方法來解決變結(jié)構(gòu)問題。2.以火箭發(fā)射系統(tǒng)為主要研究對(duì)象,詳細(xì)闡述了火箭發(fā)射系統(tǒng)的發(fā)射過程中的不同階段以及拓?fù)浣Y(jié)構(gòu),對(duì)火箭發(fā)射系統(tǒng)中所遇到的幾類變結(jié)構(gòu)問題進(jìn)行了描述,并建立了變結(jié)構(gòu)火箭發(fā)射系統(tǒng)的動(dòng)力學(xué)方程。3.綜合上述的理論知識(shí),編制了變結(jié)構(gòu)多體系統(tǒng)動(dòng)力學(xué)仿真軟件,以某型號(hào)火箭發(fā)射系統(tǒng)為研究對(duì)象,對(duì)發(fā)射過程進(jìn)行了動(dòng)力學(xué)仿真,驗(yàn)證了仿真軟件的可靠性和穩(wěn)定性。
[Abstract]:There are a lot of variable structure dynamics problems in the fields of machinery, aviation, aerospace, weapon, robot and so on. The dynamics of variable structure multi-body system has become one of the difficulties and hotspots in the field of mechanics. The main characteristic of the dynamic problem of variable-structure multi-body system is that the structure of the system will change in the course of motion, that is, the topological structure and the degree of freedom will mutate. Because of the sudden change of structure, the traditional multi-body system dynamics simulation software has some limitations in dealing with this kind of problems, and it is unable to realize the automatic switching of topology structure. In this paper, according to the characteristics of variable structure problem of multi-body system, the idea of "shunt" is introduced into the problem of variable structure dynamics. The "degree of freedom maximization" method is used to realize the "virtual stability" of the system structure, and the automatic switching function of the topology structure in the simulation process is realized, which greatly improves the computational efficiency and continuity of the simulation software. Therefore, the simulation software can realize the global simulation of variable structure multi-body system dynamics. In this paper, based on the research background of variable structure rocket launch system, several kinds of variable structure problems encountered in rocket launch system are described in detail, and the dynamic equations of variable structure rocket launch system are established. Finally, the dynamic simulation of a rocket launch system is carried out. The following are the main contents of this thesis: 1. The modeling theory of variable structure multi-body system dynamics is studied. In this paper, the variable structure problem in multibody system is discussed, and the variable structure problem is solved by introducing the method of "maximization of degrees of freedom" and "shunt". Taking the rocket launch system as the main research object, the different stages and topological structure of the rocket launch system are described in detail, and several kinds of variable structure problems encountered in the rocket launch system are described. The dynamic equation of variable structure rocket launching system is established. Based on the above theoretical knowledge, the dynamic simulation software of variable-structure multi-body system is developed. Taking a certain type of rocket launch system as the research object, the dynamic simulation of the launching process is carried out, and the reliability and stability of the simulation software are verified.
【學(xué)位授予單位】：南京理工大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2017
【分類號(hào)】：O313.7

【參考文獻(xiàn)】

相關(guān)期刊論文 前10條

1 杜超凡;章定國;;基于無網(wǎng)格點(diǎn)插值法的旋轉(zhuǎn)懸臂梁的動(dòng)力學(xué)分析[J];物理學(xué)報(bào);2015年03期

2 杜超凡;章定國;洪嘉振;;徑向基點(diǎn)插值法在旋轉(zhuǎn)柔性梁動(dòng)力學(xué)中的應(yīng)用[J];力學(xué)學(xué)報(bào);2015年02期

3 范紀(jì)華;章定國;;旋轉(zhuǎn)柔性懸臂梁動(dòng)力學(xué)的Bezier插值離散方法研究[J];物理學(xué)報(bào);2014年15期

4 金光;謝曉光;谷松;張鏑;;衛(wèi)星太陽帆板展開的動(dòng)力學(xué)仿真分析與應(yīng)用[J];光學(xué)精密工程;2014年03期

5 段sコ，

本文編號(hào)：2199201