Integrated Guidance and Control of Interception Missiles Considering Rudder Deflection Saturation and Impact Angle Constraints

ZHOU Ming; CAO Lijia; GUO Chuandong; CHEN Yucen; LIU Yanju

doi:10.15892/j.cnki.djzdxb.2025.06.041

Journal of Projectiles, Rockets, Missiles and Guidance >

2025 , Vol. 45 >Issue 6: 1293 - 1302

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2025.06.041

Academic article

Integrated Guidance and Control of Interception Missiles Considering Rudder Deflection Saturation and Impact Angle Constraints

ZHOU Ming ^,¹ ,
CAO Lijia ¹^,²^,³ ,
GUO Chuandong ^,¹^,²^,³^,^* ,
CHEN Yucen ⁴ ,
LIU Yanju ¹^,²^,³

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¹ School of Automation and Information Engineering,Sichuan University of Science and Engineering,Yibin 644000,Sichuan,China
² Intelligent Perception and Control Key Laboratory of Sichuan Province,Yibin 644000,Sichuan,China
³ Key Laboratory of Higher Education of Sichuan Province for Enterprise Informationalization and Internet of Things,Sichuan University of Science and Engineering,Yibin 644000,Sichuan,China
⁴ Norinco Group Aviation Ammunition Institute,Harbin 150030,Heilongjiang,China

Received date: 2025-05-06

Online published: 2026-01-24

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Abstract

To achieve accurate interception performance while simultaneously satisfying actuator deflection saturation and impact angle constraints,this paper proposes a dynamic surface sliding mode integrated guidance and control method.The design draws inspiration from backstepping control and sliding mode control frameworks.Firstly,the longitudinal dynamics of the missile are modeled using a first-order low-pass filter to effectively describe the actuator saturation behavior.The unmodeled parts of the missile dynamics are regarded as external disturbances.A time-varying linear sliding surface is then constructed to address the constraint imposed on the impact angle.To avoid the common problem of derivative explosion caused by repeated differentiation in traditional backstepping design,a first-order filter is employed in the control law.Additionally,a nonlinear disturbance observer is designed to estimate and compensate for the external disturbances online.To tackle the actuator saturation,a Nussbaum-type function is integrated into the controller to deal with unknown input nonlinearities.The overall stability of the closed-loop system is rigorously proven based on Lyapunov stability theory.Simulation results validate the effectiveness of the proposed approach,demonstrating that it not only ensures terminal guidance accuracy but also successfully handles the impact angle and actuator saturation constraints,showing strong robustness and reliability under complex engagement conditions.

Key words： integrated guidance and control; impact angle constraint; rudder surface saturation; dynamic surface control; sliding mode control; nonlinear disturbance observer

Cite this article

ZHOU Ming , CAO Lijia , GUO Chuandong , CHEN Yucen , LIU Yanju . Integrated Guidance and Control of Interception Missiles Considering Rudder Deflection Saturation and Impact Angle Constraints[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2025 , 45(6) : 1293 -1302 . DOI: 10.15892/j.cnki.djzdxb.2025.06.041

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