摘要
脉冲发动机凭借其响应迅速快、结构简单及成本低廉等优势,近年来在战术导弹垂直发射转弯阶段的控制中受到广泛关注。本文针对垂直冷发射条件下脉冲动力转弯过程中的导弹滚转角抑制难题,通过引入独立的滚转控制自由度,提出了一种基于滚转冲量对消的滚转−俯仰转弯控制技术,并在典型极限工况下开展了实验验证。结果表明,该技术不仅能够有效抑制滚转运动,将滚转角稳定在较小范围内,还实现了滚转与俯仰通道的控制解耦,从而支持任意方位与俯仰角的同步对准,简化了控制系统设计。在控制策略中,综合考虑了气动阻力矩对扰动的补偿效应,并引入角度误差预测机制,进一步提升了转弯过程的控制精度。该方法具有良好的控制效果,转弯角误差小于2°,验证了其在极端条件下的可行性与鲁棒性。
The pulse motor has garnered widespread attention in recent years for the control of tactical missiles during the vertical launch and turning phase,owing to its advantages such as rapid response,structural simplicity and low cost.To address the challenge of roll angle suppression for missiles during pulse-powered turning under vertical cold launch conditions,a roll-pitch turning control technique was proposed based on roll impulse cancellation by introducing an independent roll control degree of freedom,with experimental verification conducted under typical extreme operating conditions.The results demonstrate that the technique not only effectively suppresses roll motion and stabilizes the roll angle within a narrow range but also achieves control decoupling between the roll and pitch channels.This enables simultaneous alignment of arbitrary azimuth and elevation angles while simplifying the control system design.In the control strategy,the compensation effect of aerodynamic disturbance torque is comprehensively considered,and an angle error prediction mechanism is incorporated to further enhance the control accuracy during the turning process.The proposed method exhibits excellent control performance,with a turning angle error of less than 2°,verifying its feasibility and robustness under extreme conditions.
作者
刘朝琪
文立华
熊广昌
LIU Chaoqi;WEN Lihua;XIONG Guangchang(School of Astronautics,Northwestern Polytechnical University,Xi'an 710072,China)
出处
《固体火箭技术》
北大核心
2025年第6期954-960,共7页
Journal of Solid Rocket Technology
关键词
脉冲发动机
战术导弹
垂直发射
转弯控制
pulse motor
tactical missile
vertical launch
turning control
