滑翔角

First, right coordinate system is chosen to analyse force and torque in the bomb flying course , particle ballistics model of vertical attack face is built ,after that, ballistics plan composed of four phases ,namely slide 、transition、dive and attacking angle backing to zero , is designed which can achieve demands for both cannon-shot and precision.

首先选取合适的坐标系分析了制导炸弹在飞行过程中所受的力和力矩，建立了纵向攻击面的质点弹道模型。在此基础上，按既要满足一定射程又要满足一定精度的技战术要求设计、优化出包含滑翔、过渡、俯冲和攻角回零四段的方案弹道。

The design method of fractional Controller for angle stability loop and mass center control loop of GREP was studied.The fractional PI~λD~μController and integral PID Controller were designed respectively for some type GREP.The simulation results show that the fractional PI~λD~μController designed by this method has its own features compared with PID Controller.

研究了滑翔增程炮弹角稳定回路和高度控制回路的分数阶控制器设计方法，并对某滑翔增程炮弹算例分别进行了分数阶控制器和整数阶PID控制器设计，仿真结果表明该设计方法设计的分数阶控制器较PID控制器有其自身的特点。

A method was proposed for approaching the glide trajectories based on nsegment constant gliding angle.

提出用包含地球旋转效应的n个常滑翔角飞行段近似实际滑翔飞行轨迹的方法。

Flight ; Approximate solution ; Constant gliding angle ; Longitudinal ; Long-range ; Long-time

飞行；近似解；常滑翔角；纵向；远程；长航时

The approach to calculating the gliding angle and flight time of each segment was given.The procedure for approaching the whole glide trajectory was described.Two examples show that the differences in the gliding range and flight time between the approximate solution and the...

文中算例结果表明，该近似求解方法计算得到的滑翔航程和滑翔时间与实际值相差很小，航程误差率约为0.7%，时间误差率约为0.6%，因此该方法在近似小初始滑翔角的长航时远程纵向滑翔飞行时是有效的、可行的，尤其针对航程在地球半圈以上的滑翔飞行轨迹。

Three calculation example are used in this thesis, they are 122mm-missile bullet,250kg aviation bomb and a glide bullet with I,II two models.

通过对比两种型号的滑翔增程弹计算结果，分析了来流马赫数、攻角和弹翼对滑翔增程弹气动特性影响。

The split between the two groups can hardly be papered over.

这两个团体间的分歧难以掩饰。

This approach not only encourages a greater number of responses, but minimizes the likelihood of stale groupthink.

这种做法不仅鼓励了更多的反应，而且减少跟风的可能性。