Open Access
 Issue JNWPU Volume 37, Number 5, October 2019 962 - 967 https://doi.org/10.1051/jnwpu/20193750962 14 January 2020

This is an Open Access article distributed under the terms of the Creative Commons Attribution License (http://creativecommons.org/licenses/by/4.0), which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.

## 1 导弹数学模型

### 1.1 运动模型

 图 1导弹气动外形

### 1.2 线性化模型

1) 采用系数冻结法，即取弹道上某一时刻t, 飞行速度V、高度H、推力P、质量m、转动惯量Jz均不变；

2) 攻角α为小量, 即sinαα, cosα≈1。

## 2 鸭舵/尾舵复合控制系统

 图 2鸭舵/尾舵复合控制系统结构

## 3 基于序列二次规划法的鸭舵/尾舵分配策略

1) 给定初值S0=(Kz1, Kz2);

2) 求解(10)式所描述的二次规划子问题, 确定搜索方向dk;

3) 令Sk+1=Sk+dk, 判断Sk+1是否满足收敛条件。若满足, 则取最优解为S*=Sk+1, 停止计算; 否则返回2)继续迭代。

## 4 仿真验证

 图 3高度变化曲线
 图 4攻角变化曲线
 图 5法向过载变化曲线
 图 6鸭舵/尾舵舵偏角变化曲线
 图 7尾舵分配系数变化曲线
 图 8阻力变化曲线

## References

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## All Figures

 图 1导弹气动外形 In the text
 图 2鸭舵/尾舵复合控制系统结构 In the text
 图 3高度变化曲线 In the text
 图 4攻角变化曲线 In the text
 图 5法向过载变化曲线 In the text
 图 6鸭舵/尾舵舵偏角变化曲线 In the text
 图 7尾舵分配系数变化曲线 In the text
 图 8阻力变化曲线 In the text

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