| 引用本文: | 吴放,常思江.攻击时间和攻击角度控制的非奇异终端滑模制导律[J].哈尔滨工业大学学报,2021,53(6):94.DOI:10.11918/201910210 |
| WU Fang,CHANG Sijiang.Nonsingular terminal sliding mode guidance law of impact time and impact angle control[J].Journal of Harbin Institute of Technology,2021,53(6):94.DOI:10.11918/201910210 |
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| 摘要: |
| 为提高导弹的突防能力并增强毁伤效果,对导弹攻击时间和攻击角度控制问题进行了研究,以导弹和目标相对运动模型为基础,提出了一种非奇异滑模导引律.利用成型理论设计了以时间多项式描述的、同时满足攻击时间和攻击角度约束的导弹视线角表达式.采用优化方法确定表达式系数.由于非奇异终端滑模理论具有使滑模面能够在有限时间内快速收敛的特点,故利用该理论构造关于视线角误差的滑模面,设计了一种无奇点的攻击时间和攻击角度控制制导律.该制导律可使导弹的实际视线角按照设计的理想视线角变化,使导弹满足攻击时间和攻击角度的双重约束.通过理论分析,证明了该制导律满足Lyapunov稳定性条件,能够实现攻击时间和攻击角度控制且不存在奇点.在多种情形下对所设计制导律进行了数值仿真. 仿真结果表明,采用该制导律可在不同条件下有效实现导弹的攻击时间与攻击角度控制,与现有文献相比具有一定优势,当存在一定程度的外界干扰时仍能完成攻击时间和攻击角度控制. |
| 关键词: 导弹 制导律 攻击时间控制 攻击角度控制 非奇异终端滑模 |
| DOI：10.11918/201910210 |
| 分类号:TJ765.3 |
| 文献标识码:A |
| 基金项目:国家自然科学基金(11402117) |
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| Nonsingular terminal sliding mode guidance law of impact time and impact angle control |
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WU Fang,CHANG Sijiang
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(School of Energy and Power Engineering, Nanjing University of Science and Technology, Nanjing 210094, China)
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| Abstract: |
| To improve the penetration ability of missiles and enhance the damage effect, the problems of impact time and impact angle control of missiles were studied. A nonsingular sliding mode guidance law was proposed based on the relative dynamics of missile and target. According to the shaping theory, a line-of-sight (LOS) polynomial satisfying impact time and impact angle constraints simultaneously was designed. The coefficient was determined using an optimization method. Since the nonsingular terminal sliding mode theory has the characteristic of fast convergence of sliding surface in finite time, a sliding surface was constructed via the error of the LOS, and a nonsingular impact time and impact angle control guidance law was designed. The proposed guidance law could change the actual LOS according to the designed LOS to satisfy the constraints of impact time and impact angle. Through theoretical analysis, it was proved that the proposed guidance law satisfied the Lyapunov stability criterion and could realize the control of the impact time and impact angle without singularities. The proposed guidance law was numerically simulated in different situations. Numerical simulation results show that the proposed guidance law could control impact time and impact angle effectively under various conditions and had certain advantages compared with existing literature. Even with a certain degree of external interference, the impact time and impact angle control could still be completed. |
| Key words: missile guidance law impact time control impact angle control nonsingular terminal sliding mode |
