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Control of Quick Turning of Missile with Lateral Thrust and Aerodynamics Based on Neural Network
- Acta Armamentarii Vol. 45, Issue 10, Pages: 3564-3576(2024)
- 作者机构：
北京理工大学 宇航学院, 北京 100081
- 作者简介：
- 基金信息：
DOI：10.12382/bgxb.2023.0901
CLC：Received：11 September 2023，
Published Online：30 October 2024，
Published：31 October 2024
- 稿件说明：
移动端阅览
Xinyue PEI, Yong YU, Zheng LI, et al. Control of Quick Turning of Missile with Lateral Thrust and Aerodynamics Based on Neural Network[J]. Acta Armamentarii, 2024, 45(10): 3564-3576.
Xinyue PEI, Yong YU, Zheng LI, et al. Control of Quick Turning of Missile with Lateral Thrust and Aerodynamics Based on Neural Network[J]. Acta Armamentarii, 2024, 45(10): 3564-3576. DOI： 10.12382/bgxb.2023.0901.
摘要
空空导弹迅捷转弯控制是在保证导弹稳定飞行的前提下
在尽可能短的时间内完成整个机动过程。为实现上述战术指标
考虑到导弹迅捷转弯的快时变性、强非线性和大干扰性
设计基于滑模变结构控制和模糊逻辑的直/气复合控制器。针对实际飞行中可能出现的初值不确定和外界干扰过大等现象
引入固定时间收敛理论和扩张状态观测器
有效避免干扰带来的控制输入抖振并保证导弹姿态角能在固定时间内快速稳定收敛。利用神经网络对滑模变结构控制的设计参数进行优化
在保证导弹迅捷转弯的同时减轻导弹侧向发动机的质量。通过仿真验证新提出的控制和分配方案的有效性。研究结果表明
所设计的控制器在存在模型不确定性和外部干扰等复杂情况下具一定的鲁棒性、稳定平滑的控制效果、较强的抗干扰能力以及优异的姿态跟踪性能
同时参数优化后的控制算法跟踪效果更优
在降低了原收敛时间的12.6%的同时
降低了原最大控制力的9.6%。
Abstract
The control of the quick turning of air-to-air missile is to complete the entire maneuvering process in the shortest possible time under the premise of ensuring the stable flight of the missile. In order to achieve the above tactical indicators
a lateral thrust/aerodynamics composite controller based on sliding mode variable structure control and fuzzy logic is designed considering the fast time denaturation
strong nonlinearity and large interference of the missile quick turning. In view of the uncertain initial value and excessive external interference that may occur in actual flight
the fixed-time convergence theory and the extended state observer are introduced to effectively avoid the control input jitter caused by interference and ensure that the attitude angle of missile can converge quickly and stably within a fixed time. The neural network is used to optimize the design parameters of sliding mode variable structure control
which not only ensures the quick turning of missile
but also reduces the mass of missile's lateral engine. The effectiveness of the proposed control and distribution scheme is verified by simulation. The designed controller has certain robustness
stable and smooth control effect
strong anti-interference ability and excellent attitude tracking performance in complex situations such as model uncertainty and external interference
and the tracking effect of the control algorithm after parameter optimization is better
which reduces the original convergence time by 12.6% and the original maximum control force by 9.6%.
关键词
Keywords
references
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