In this paper, an analysis of coupled vibration for the flexible spin rocket launch system with a supersonic exhaust jet is presented. Dynamic equations of the system are established, and the flow field structure inside the launch tube is described by a numerical simulation method. Transient responses of the launch system are given and the effect of exhaust jet on the rocket attitude is discussed. This work provides a more reliable and efficient approach to simulate the dynamics environment of the flexible...

            對(duì)于柔性旋轉(zhuǎn)火箭發(fā)射系統(tǒng)，考慮高速燃?xì)鈬娏髯饔孟碌南到y(tǒng)耦合振動(dòng)．建立發(fā)射系統(tǒng)動(dòng)力學(xué)模型，數(shù)值計(jì)算發(fā)射管流場(chǎng)結(jié)構(gòu)，確定系統(tǒng)瞬態(tài)響應(yīng)和燃?xì)饬鳑_擊對(duì)火箭發(fā)射姿態(tài)的影響，更加真實(shí)地模擬柔性旋轉(zhuǎn)火箭的發(fā)射動(dòng)力學(xué)環(huán)境．

         This paper discusses the problem of dynamics control for rocket launching systems.The traditional method for dynamics control,Driver Constraint Method,is introduced,and its controlling thoughts are narrated in detail.A set of governing differential equations for multibody model of rocket gun systems is established via employing the Driver Constraint Method.Based on these equations,a software is developed.And an example,the dynamics control of a rocket gun system,is given to demonstrate the control procedure...

            該文探討了火箭發(fā)射系統(tǒng)的動(dòng)力學(xué)控制問(wèn)題。傳統(tǒng)的動(dòng)力學(xué)控制方法被引入文中 ,其控制思路得到詳細(xì)敘述。運(yùn)用此方法建立了火箭發(fā)射系統(tǒng)的動(dòng)力學(xué)控制方程 ,并編制了相應(yīng)的控制軟件。文末給出了一個(gè)控制實(shí)例以演示整個(gè)控制過(guò)程和控制效果 ,結(jié)果表明 ,對(duì)火箭炮系統(tǒng)實(shí)施恰當(dāng)?shù)膭?dòng)力學(xué)控制 ,有助于抑制發(fā)射系統(tǒng)的振動(dòng)和減小火箭彈的起始擾動(dòng)

         Carrying out launching attitude control is to increase the high concentration of rocket.During the launching,ships have two types of vibration stimulated by wave and the force of exhaust gas,so the precision will be closely related to the ship motion and the feature of dynamic structure of launching system.By studying the launching attitude of ship and the launching characteristics of rocket weapon under different attitudes,the optimum attitude of ship for launching is selected.An effective way of controlli...

            實(shí)施艦載多管火箭武器系統(tǒng)發(fā)射姿態(tài)控制的目的 ,是提高火箭發(fā)射的精度。火箭發(fā)射過(guò)程中 ,載體存在 2種形式的振動(dòng) :隨波振動(dòng)和燃?xì)饬髟斐傻臎_擊振動(dòng)。因此系統(tǒng)的發(fā)射精度同時(shí)與船體的運(yùn)動(dòng)及發(fā)射系統(tǒng)的動(dòng)力學(xué)結(jié)構(gòu)特征等兩方面因素密切相關(guān)。該文通過(guò)研究船體在火箭發(fā)射時(shí)的姿態(tài)及各姿態(tài)下火箭武器的發(fā)射特性 ,對(duì)發(fā)射時(shí)船體姿態(tài)求優(yōu) ,獲得了對(duì)系統(tǒng)發(fā)射姿態(tài)實(shí)施控制的有效途徑

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