The thesis tracks the research about the intercept technology oversea . the rolling missile model with attitude - control - system is established by referring to the figuration dimension of pac - 3 本文跟踪国外研究，以“爱国者? 3 ”导弹外形尺寸为参考建立了具有姿态控制系统的滚转导弹模型。
I the latter part of this paper , some re - entry warhead rudders is designed by using the mrd and a new method is proposed to calculate the probability of re - entry vehicle roll abnormity 应用本文的方法对小型再入弹头尾舵进行稳健设计，并提出一种提高再入弹头滚转异常概率计算效率的方法。
And still signal being sheltered model and deflection separation model when the missile is controlled non - rolling are built , separation process are digitally simulated to check the stability during it 提出信号传输遮挡模型,建立受控无滚转时的偏差分离模型,实现导弹分离过程数值仿真和稳定性分析。
2 . considering the difference of the rolling missile and the non - rolling missile , the mechanism of rolling missile control force and the control theory of rolling missile was analyzed rigorously 考虑到滚转导弹与非滚转导弹的不同，本文仔细分析了滚转导弹控制力的产生机理和滚转导弹的控制原理。
That globe is massaged into greater roundness between heavy plates and honed to exact sphericity and smoothness by rolling through grindstones hundreds , if not thousands , of times [ see main illustration , right ] 将小球放在重盘之间滚压得更圆，同时在砂轮间滚转数百次到数千次，打磨得更圆更光滑（见右图） 。
3 . the combined trajectory control system is designed . the direct force is acting on the pitch channel and the yaw channel , and the roll channel is stabilized by the fin surface deflection 设计的轨控直接力作用于俯仰和偏航通道，而滚转通道没有直接力系统的作用，依靠气动舵面的偏转对滚转角进行稳定。
The flying stability of the unguided projectile with wrap around fins could be influenced by the self - induced rolling characteristics and the cross coupling effects of the waf badly . it is necessary to study further on this special aerodynamic problems 卷弧翼存在自诱导滚转特性、较严重的交叉耦合效应等特殊气动问题,对于无控的卷弧尾翼弹而言,这很大程度上影响飞行稳定性。
This article discusses the differential tail design , which will be proved to improve the roll ability for the aircraft and it will be possible for reconfiguration of the flight control processing in the design when the aircraft has a wrong 本文就某型飞机采用差动平尾的方案进行分析，从而证明采用差动平尾操纵方式可使得飞机滚转性能大大的提高；当飞机发生故障时，使得相应通道的控制重构成为可能。
The aerodynamic characteristics of a projectile with wrap around fins are studied systematically in this paper , as follows : 1 . the lift coefficients 、 drag force coefficients 、 pitch moment coefficients 、 pitch damping moment derivatives and roll damping moment derivatives are obtained from engineering calculation through looking wrap around fins as flat fins of the same projection aera 本文对某卷弧尾翼弹气动特性进行了系统研究,主要内容与结论为: 1 .将卷弧翼按照相同投影面积的平板翼进行工程估算,得到升力系数、阻力系数、俯仰力矩系数、俯仰阻尼导数、滚转阻尼导数曲线。
Then , we do some modeling for some architecture of some indoors , outdoors and a city scene with the aid of some special modeling software such as 3d studio . we put these models into the opengl walkthrough program and add different walkthrough controls to them . we still do much progress in the optimization of the rendering 其次，关于第二种虚拟漫游技术，本文将由3dsstudio专用建模软件设计的、比较复杂的室内外和城市建筑模型，导入到opengl的交互程序中，实现了贯穿漫游、环视、俯视、仰视、滚转等复杂的漫游控制。
