Simulation and test of rocket initial disturbance 火箭彈起始擾動的仿真與試驗研究
Research of initial disturbance of rocket in lagrange 拉格朗日方法建模下的火箭彈起始擾動研究
A method to study random factor ' s effections on initial disturbance of projectile 隨機(jī)因素對彈丸起始擾動影響的分析方法
The primary work of this thesis is as follow : ship motion is an important factor which effected missile initial disturbance 作為影響艦載導(dǎo)彈發(fā)射初始擾動的重要因素,對艦艇運(yùn)動規(guī)律的研究非常重要。
One of the inequalities is that the initial disturbance amplitude is more than a critical value , and the other is that the frictional coefficient is more than another critical value 初始擾動振幅大于某一臨界值; ( 2 )摩擦系數(shù)大于某一臨界值,前者對后者有很強(qiáng)的約束。
The introduction of nonlinear advection into the model weakens the intensifying of maximum tangential wind with relative to the initial disturbance azimuthally wave numbers and intensity Ssbyt和臺風(fēng)強(qiáng)度影響的研究似二波分布擾動使tc強(qiáng)度的增幅并沒有實際二波擾動的增幅大。
The main conclusions show as following : 1 the effects of propagating vortex rossby waves on tc intensity change are relative closely to the position , the size and intensity of the initial disturbance 主要結(jié)果可歸納如下: 1渦旋rossby波傳播對熱帶氣旋強(qiáng)度變化的影響,與初始擾動相對渦旋中心的位置、初始擾動尺度大小及強(qiáng)度等關(guān)系密切。
Launch process of missile , especially initial disturbance , is an important direction of launch dynamics . with the development of compute simulation and launch dynamics , much technology and method has been researched in the area of launch process 導(dǎo)彈發(fā)射過程,特別是導(dǎo)彈的初始擾動是發(fā)射系統(tǒng)研究的一個重要課題,隨著計算機(jī)仿真和發(fā)射動力學(xué)的發(fā)展,對導(dǎo)彈發(fā)射過程的研究也有許多不同的途徑和技術(shù)。
The controlling force developed by the jets is working at the beginning of the initiative trajectory ( 0 . 385 - 3 . 385s ) to control the attitude of the projectile to keep its axis on the direction of launch - direction , so as to reduce the effect of initial disturbance 控制力由噴流作用力產(chǎn)生,在主動段的初始段( 0 . 385 3 . 385秒)控制彈體的姿態(tài),使彈軸維持在初始方向上,從而減少初始干擾,減小落點散布(飛行時間約170秒) ,提高精度。