带角度和时间约束的抗饱和非解耦俯冲攻击制导律  

Anti-Saturation and Undecoupled Diving Attack Guidance Law for Impact Angle and Time Constraints

作　　者：葛颂 夏文杰 闫循良[1] Ge Song;Xia Wenjie;Yan Xunliang(School of Astronautics,Northwestern Polytechnical University,Xi’an 710072,China;China Airborne Missile Academy,Luoyang 471009,China)

机构地区：[1]西北工业大学航天学院,西安710072 [2]中国空空导弹研究院,河南洛阳471009

出　　处：《航空兵器》2023年第5期25-32,共8页Aero Weaponry

基　　金：国家自然科学基金项目(11602296)。

摘　　要：针对高超声速飞行器俯冲攻击段运动模型强非线性、通道间强耦合、受多种复杂约束限制和极限情况下过载易饱和等特点,设计了一种带角度和时间约束的抗饱和非解耦俯冲攻击制导律。首先,基于速度前置角相对运动模型和滑模控制理论,设计了一种带时间约束的非解耦滑模基础制导律;随后,对基于几何旋量的三维非解耦多角度约束最优制导律进行分析并分离出角度约束对应的指令项,进而将其作为偏置项引入带时间约束的滑模基础制导律中,构造了一种综合考虑终端落角、方位角和时间约束的制导律;最后,通过设计新的趋近律对制导律基准项进行改进以抑制制导指令饱和,得到了一种考虑终端角度和时间约束的抗饱和制导律,并通过数值仿真验证了所提方法的适用性和鲁棒性。Aiming at the characteristics of the motion model of the dive attack segment of hypersonic vehicle,such as strong nonlinearity,strong coupling between channels,complex constraints and easy overload saturation under the limit condition,a kind of anti-saturation non-decoupled dive attack guidance law with angle and time constraints is designed.Firstly,based on the velocity front angular relative motion model and sliding mode control theory,a time-constrained non-decoupled sliding mode basic guidance law is designed.Subsequently,the three-dimensional undecoupled multi-angle constraint optimal guidance law based on geometric spinor is analyzed and the instruction item corresponding to the angle constraint is separated.Then,the instruction item is introduced into the sliding mode guidance law with time constraint as the bias item.A guidance law considering the terminal fall angle,azimuth angle and time constraint is constructed.Finally,a new approach law is designed to improve the guidance law reference term to suppress the saturation of guidance instructions,and an anti-saturation guidance law considering terminal angle and time constraints is obtained.The applicability and robustness of the proposed method are verified by numerical simulation.

关 键 词：高超声速飞行器 俯冲攻击制导 非解耦 多角度约束 飞行时间约束 抗饱和 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程] V249[航空宇航科学与技术—飞行器设计]