部分约束下空中目标拦截制导控制一体化方法

doi:10.12305/j.issn.1001-506X.2023.04.22

摘要/Abstract

摘要：

针对拦截空中目标的场景, 提出一种考虑攻击角度的制导控制一体化(integrated guidance and control, IGC)方法, 同时考虑输入饱和以及攻角的约束问题。首先, 在俯仰平面下对包含不确定性的系统进行了建模。基于反演法和指令滤波器, 处理了攻击角度约束问题和执行器机械限制的输入饱和问题, 设计了含误差积分反馈的补偿项以处理跟踪误差, 引入了障碍Lyapunov函数将攻角约束在预设区间。基于Lyapunov理论证明了闭环系统的稳定性和变量的有界性, 以及各约束条件的成立性。仿真实验表明, 方法能够以预设角度有效拦截目标, 过程满足对输入以及攻角的约束条件, 同时具备较强的鲁棒性。

关键词: 制导控制一体化, 攻击角度, 输入饱和, 状态约束, 指令滤波器

Abstract:

An integrated guidance and control (IGC) method with impact angle is proposed to intercept aerial target, constraints including input saturation and angle of attack are considered as well. Firstly, system with lumped uncertainties is modeled in pitch plane. Based on backstepping and command filter, constraints of impact angle and input saturation due to mechanical limitation of actuator are solved, signals with integration of error are constructed to handle with tracking errors. To guarantee the angle of attack within a predefined interval, barrier Lyapunov function is introduced. Based on Lyapunov theorem, stability of closed system, boundness of signals, and required constraints are proved. Numerical simulations exhibit effectiveness of interception with predefined impact angle for aerial target, constraints satisfied including input saturation and angle of attack, strong robustness also possessed of the method.

Key words: integrated guidance and control (IGC), impact angle, input saturation, state constraint, command filter

中图分类号:

V448.13

梁乐成, 赵斌, 周军, 赵万利. 部分约束下空中目标拦截制导控制一体化方法[J]. 系统工程与电子技术, 2023, 45(4): 1134-1143.

Lecheng LIANG, Bin ZHAO, Jun ZHOU, Wanli ZHAO. Integrated guidance and control method against aerial target with partial constraints[J]. Systems Engineering and Electronics, 2023, 45(4): 1134-1143.

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导弹参数	数值	导弹参数	数值
θ_M(0)/(°)	10	V_M/(m·s^-1)	500
θ_T(0)/(°)	180	V_T/(m·s^-1)	200
x(0)/m	8 000	y(0)/m	6 000

参数	数值	参数	数值	观测器参数	数值
k₁	0.2	k₃	25	b₁, b₃, b₅	300
k₂	10	β₁	1.2	b₂, b₄, b₆	600
τ₂	0.06	β₃	20

仿真条件	脱靶量/m	飞行时间/s
λ_d=30°	0.066 7	15.003
λ_d=60°	0.071 3	15.166
λ_d=90°	0.091 6	16.042

来源	参数	拉偏量/%
结构参数	m, S, L, J_z	±20
气动参数	c_y^α, c_y^z^δ, m_z^α, m_z^z^δ, m_z^ω_z	±20

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