考虑导弹自动驾驶仪动态特性的新型制导律

张凯; 杨锁昌; 张宽桥; 张永伟; 陈鹏

doi:10.13700/j.bh.1001-5965.2016.0630

考虑导弹自动驾驶仪动态特性的新型制导律

doi: 10.13700/j.bh.1001-5965.2016.0630

张凯^{1, 2},
杨锁昌^1, ,,
张宽桥¹,
张永伟¹,
陈鹏^{1, 3}

1.
军械工程学院导弹工程系, 石家庄 050003
2.
中国华阴兵器试验中心制导武器试验鉴定仿真技术重点实验室, 华阴 714200
3.
军械技术研究院, 石家庄 050003

基金项目:

国家自然科学基金 61501493

国家自然科学基金 51177174

武器装备军内科研项目 ZS2015070132A12012

详细信息

作者简介:
张凯  男, 硕士研究生。主要研究方向:精确制导理论与技术

杨锁昌  男, 博士, 教授, 博士生导师。主要研究方向:精确制导理论与技术

张宽桥  男, 博士研究生。主要研究方向:精确制导理论与技术

张永伟  男, 博士研究生。主要研究方向:弹箭智能化与信息化技术

陈鹏  男, 博士, 工程师。主要研究方向:弹箭智能化与信息化技术

通讯作者:
杨锁昌, E-mail: yangsuochang_jx@sina.com

中图分类号: V448;TJ765
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- 被引次数: 0
出版历程
- 收稿日期: 2016-07-27
- 录用日期: 2016-11-08
- 网络出版日期: 2017-08-20

Novel guidance law accounting for dynamics of missile autopilot

1.
Department of Missile Engineering, Ordnance Engineering College, Shijiazhuang 050003, China
2.
Key Laboratory of Guided Weapons Test and Evaluation Simulation Technology, China Huayin Ordnance Test Center, Huayin 714200, China
3.
Ordnance Technology Research Institute, Shijiazhuang 050003, China

Funds:

National Natural Science Foundation of China 61501493

National Natural Science Foundation of China 51177174

Weapon and Equipment Military Science Projects ZS2015070132A12012

More Information

Corresponding author: YANG Suochang, E-mail: yangsuochang_jx@sina.com

摘要

摘要:
针对拦截空中飞行目标需要满足零脱靶量和攻击角约束提高导弹制导性能等问题，首先，利用考虑噪声干扰的扩张状态观测器对目标加速度进行估计，其次，改进一种非奇异终端滑模面，将自动驾驶仪视为理想环节，然后，基于终端滑模控制理论和有限时间收敛理论推导一种滑模制导律，最后，考虑自动驾驶仪二阶动态特性，将得到的滑模制导律结合动态面控制法提出一种新型制导律。分别以不同的攻击角对机动飞行和匀速飞行的目标进行拦截，大量仿真表明，所提制导律具有良好的制导性能，能够保证导弹在零脱靶量击中目标的同时达到期望攻击角。
- 自动驾驶仪 /
- 攻击角约束 /
- 制导律 /
- 动态面控制 /
- 非奇异终端滑模控制
Abstract:
Interception of air targets requires zero miss-distance and impact angle constraint to improve the missile guidance performance. First, the acceleration of the target was estimated by extended disturbance observer which also considered the noise interference. Second, a nonsingular terminal sliding mode surface was improved, which considered autopilot ideally. Third, a sliding-mode guidance law was designed based on the terminal sliding mode control theory and the theory of finite time convergence. Finally, considering the second-order dynamic characteristics of autopilot, the novel guidance law was developed combining both sliding-mode guidance law and dynamic surface control method. In simulation experiments, both maneuvering targets and constant velocity targets were intercepted with different impact angle. A large number of simulation results demonstrate that the proposed guidance law canguarantee that the missile hits the target and at the same time achieves a desired angle of impact, which performs well.
- autopilot /
- impact angle constraint /
- guidance law /
- dynamic surface control /
- nonsingular terminal sliding mode control

HTML全文

图 1 弹目相对运动示意图

Figure 1. Schematic diagram of relative motion of missile and target

下载: 全尺寸图片幻灯片

图 2 场景1仿真实验结果

Figure 2. Simulation experimental results of Situation 1

下载: 全尺寸图片幻灯片

图 3 场景2仿真实验结果

Figure 3. Simulation experimental results of Situation 2

下载: 全尺寸图片幻灯片

表 1 不同视线角拦截机动目标仿真实验结果

Table 1. Simulation experimental results of maneuvering target interception at different angles of LOS

q_d/(°)	制导律	制导时间/s	脱靶量/ m	视线角偏差/(°)
30	BPNG	12.12	2.298 3	2.3
	DSCG	11.69	0.247 8	0.5
	SMG	11.68	1.256 4	1.1
	VSG	11.67	1.426 8	1.3
60	BPNG	12.08	2.278 5	1.8
	DSCG	11.62	0.239 8	0.3
	SMG	11.62	1.087 2	0.9
	VSG	11.61	1.413 9	1.2
75	BPNG	12.16	2.301 2	2.5
	DSCG	11.67	0.257 6	0.4
	SMG	11.66	1.156 8	1.3
	VSG	11.64	1.507 3	1.4

下载: 导出CSV

表 2 不同视线角拦截匀速目标仿真实验结果

Table 2. Simulation experimental results of uniform-velocity target interception at different angles of LOS

q_d/(°)	制导律	制导时间/s	脱靶量/ m	视线角偏差/(°)
30	BPNG	11.63	3.568 5	2.2
	DSCG	11.54	0.354 2	0.3
	SMG	11.49	1.532 7	1.3
	VSG	11.52	1.453 6	1.3
60	BPNG	11.55	3.550 7	2.1
	DSCG	11.51	0.336 9	0.2
	SMG	11.48	1.513 8	1.2
	VSG	11.48	1.483 2	1.1
75	BPNG	11.58	3.760 4	2.4
	DSCG	11.52	0.326 9	0.3
	SMG	11.50	1.502 3	1.2
	VSG	11.49	1.496 3	1.3

下载: 导出CSV

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