Numerical State-Dependent Riccati Equation Approach for Missile Integrated Guidance Control

Zhang

Advances in Mechanical Engineering

et al. 2017

This article focuses on the missile integrated guidance and autopilot design in the end-game phase with control input saturation. First, the nonlinear integrated guidance and autopilot model is developed with third actuator dynamics, where the control surface deflection has magnitude constraint. Second, three nonlinear extended state observers are used to estimate the aerodynamics coefficients' uncertainties and unmatched time-varying disturbances. Third, a command filtered controller is designed step by step with linear and nonlinear sliding surfaces to improve the terminal performance. In the process, different command filters are implemented to avoid the influences of disturbances and repetitive derivation and solve the problem of unknown control direction. The stability of closed-loop system is proved by Lyapunov theory, and the principles abided by the controller parameters are concluded through the proof. Finally, 6-degree-of-freedom numerical simulations are presented to show the feasibility and validity of the proposed controller.

Section: Introductionmentioning

confidence: 99%

Command filtered back-stepping missile integrated guidance and autopilot based on extended state observer

Zhang

Advances in Mechanical Engineering

et al. 2017

IEEE Trans. Contr. Syst. Technol.

“…In [8]- [10], second-order and high-order sliding mode controls were used to improve the robustness of IGC to target maneuvers and model uncertainties. Based on the feedback linearization, IGC was transformed into the trajectory optimization of finite-time linear quadratic form [11], [12], with the numerical solution of Riccati equation developed in [13]. In [1], [14], and [15], a robust partial IGC (PIGC) design was proposed.…”

Section: Introductionmentioning

confidence: 99%

Fast Robust Integrated Guidance and Control Design of Interceptors

Song

Zhang

2016

In this brief, a fast robust integrated guidance and control design approach, considering the 3-D interception of interceptors for hypersonic vehicles, is proposed. The proposed method is designed using the modified fast terminal sliding mode control and dynamic surface control with signal compensation. The fractional integral fast terminal sliding functions are presented independently, and all the sliding phases run parallel to increase the system response speed. Utilizing the dynamic surface control method, the robust compensation signals are constructed to eliminate the influence of uncertainty equivalents thoroughly. Therefore, the proposed approach guarantees the fast convergence of line-of-sight angular rates and the system robustness for uncertainties. The simulation results demonstrate the robustness of the proposed controller, and a variety of comparison studies are also carried out to demonstrate the advantage of the new approach.Index Terms-Dynamic surface control, fast terminal sliding mode (FTSM) control, integrated guidance and control (IGC), interceptor.

“…SDRE based missile longitudinal autopilot and three-loop acceleration autopilot were proposed (Mracek et al (1997); Cimen (2011)). A guidance and control integrated system using SDRE was also proposed (Vaddi et al (2009)). However, those researches were conducted under the assumption that system parameters such as mass and velocity do not change and aerodynamic uncertainties are not considered.…”

Section: Introductionmentioning

confidence: 99%

Adaptive SDRE Based Boost-Phase Missile Autopilot Design Using Single and Modular Neural Networks

Lee

Kim

et al. 2015

IFAC-PapersOnLine

Adaptive autopilot is designed using State-Dependent Riccati Equation (SDRE) and Neural Networks (NN), which guarantees the control performance during the boost-phase of missile. Rapid changes of parameters and aerodynamic uncertainties degrade the control performance of missile during the boost-phase. To deal with the nonlinearity of the missile system due to the rapid changes of parameters, SDRE technique is adopted to design baseline controller, and to compensate the effects of aerodynamic uncertainties, modular NN is proposed to design auxiliary controller. Numerical simulations are performed to demonstrate the performance of the proposed autopilot.