Modeling and Simulation for the Infrared Guidance System

2010 ◽  
Vol 40-41 ◽  
pp. 71-77
Author(s):  
Nan Li ◽  
Yan Jun Li ◽  
Yun Yan Zhang
Keyword(s):  
Control Method ◽  
Aerodynamic Force ◽  
Three Dimensional ◽  
Guidance System ◽  
Guidance Law ◽  
Detection And Tracking ◽  
Set Up ◽  
Trigger Mechanisms ◽  
Geometrical Relationship ◽  
Jamming Effect

The specific guidance simulation system for the infrared air-to-air missile is built. Seeker model including the target detection and tracking loop has simulated not only the different modes of field of view (FOV) according to the geometrical relationship between the target and missile, but also the jamming effect based on the equivalent target calculation; fuze model contains three different trigger mechanisms; guidance of missile is realized via three-dimensional proportional guidance law; the 6 DOF kinematics model and dynamic model of airframe are derived, through aerodynamic force and torque calculating, triple-channel autopilot model is set up by using the PID control method. Finally simulations under three different cases are implemented and the results show that the whole system is credible.

Three-Dimensional Impact Angle Guidance Laws Based on Model Predictive Control and Sliding Mode Disturbance Observer

2016 ◽  
Vol 138 (8) ◽  
Author(s):  
Shaoming He ◽  
Wei Wang ◽  
Jiang Wang
Keyword(s):  
Model Predictive Control ◽  
Predictive Control ◽  
Disturbance Observer ◽  
Control Method ◽  
Sliding Mode ◽  
Three Dimensional ◽  
Continuous Model ◽  
Guidance System ◽  
Guidance Law ◽  
Sliding Mode Disturbance Observer

This paper presents a suboptimal three-dimensional guidance law to intercept unknown maneuvering targets with terminal angle constraint using multivariable control design. The presented guidance law is essentially a composite control method, which is constructed through a combination of standard continuous model predictive control (MPC) and adaptive multivariable sliding mode disturbance observer (SMDO). More specifically, the MPC method is utilized to obtain optimal line-of-sight (LOS) angle tracking performance for nonmaneuvering targets, while the SMDO technique is used to estimate and compensate for the unknown target maneuver online. By virtue of the adaptive nature, the proposed guidance law does not require any information on the bounds of target maneuver and its gradient except for their existence. The stability of the closed-loop guidance system is also analyzed by using Lyapunov function method. Simulation results clearly confirm the effectiveness of the proposed formulation against a maneuvering target.

Three-dimensional cooperative interception guidance law with impact time constraint

2021 ◽  
pp. 095441002110105
Author(s):  
Li Hongxia ◽  
Deng Yifan ◽  
Yuanli Cai
Keyword(s):  
Finite Time ◽  
Control Method ◽  
Three Dimensional ◽  
Time Constraint ◽  
Lyapunov Theory ◽  
Guidance System ◽  
Consensus Protocol ◽  
Impact Time ◽  
Guidance Law ◽  
The Impact

This article proposes a new terminal cooperative guidance law with impact time constraint in three-dimensional (3D) engagement. Two parts are comprised by this guidance scheme to control the impact time and fulfill the interception. The guidance law along the line-of-sight (LOS) direction is first designed based on finite time consensus protocol to share time-to-go values among missiles and reach the consensus. Meanwhile, the guidance law on the LOS normal direction is developed based on the fast finite time control method to achieve the interception. The stability analysis of the proposed guidance law based on the Lyapunov theory is also demonstrated in detail. Moreover, the maneuvering target can be intercepted successfully under the presented control algorithm, and the guidance system can fulfill stability within finite time. Additionally, the effectiveness and applicability of the proposed guidance scheme are explicitly verified through simulation tests.

Three-dimensional adaptive fixed-time guidance law against maneuvering targets with impact angle constraints and control input saturation

2021 ◽  
pp. 014233122110598
Author(s):  
Fei Ma ◽  
Yunjie Wu ◽  
Siqi Wang ◽  
Xiaofei Yang ◽  
Yueyang Hua
Keyword(s):  
Sliding Mode ◽  
Input Saturation ◽  
Three Dimensional ◽  
Fixed Time ◽  
Impact Angle ◽  
Guidance System ◽  
Control Input ◽  
Guidance Law ◽  
The Stability ◽  
And Control

This paper presents an adaptive fixed-time guidance law for the three-dimensional interception guidance problem with impact angle constraints and control input saturation against a maneuvering target. First, a coupled guidance model formulated by the relative motion equation is established. On this basis, a fixed-time disturbance observer is employed to estimate the lumped disturbances. With the help of this estimation technique, the adaptive fixed-time sliding mode guidance law is designed to accomplish accurate interception. The stability of the closed-loop guidance system is proven by the Lyapunov method. Simulation results of different scenarios are executed to validate the effectiveness and superiority of the proposed guidance law.

Robust impact angle constraints guidance law with autopilot lag and acceleration saturation consideration

2018 ◽  
Vol 41 (1) ◽  
pp. 182-192 ◽  
Author(s):  
Junhong Song ◽  
Shenmin Song
Keyword(s):  
Upper Bound ◽  
Finite Time ◽  
Sliding Mode ◽  
Three Dimensional ◽  
Impact Angle ◽  
Guidance System ◽  
Control Technique ◽  
Backstepping Method ◽  
Terminal Sliding Mode ◽  
Guidance Law

In this paper, for the three-dimensional terminal guidance problem of a missile intercepting a manoeuvring target, a robust continuous guidance law with impact angle constraints in the presence of both an acceleration saturation constraint and a second-order-lag autopilot is developed. First, based on non-singular fast terminal sliding mode and adaptive control, a step-by-step backstepping method is used to design the guidance law. In the process of guidance law design, with the use of a finite-time control technique, virtual control laws are developed, a tracking differentiator is used to eliminate the ‘explosion of complexity’ problem inherent in the traditional backstepping method, and an additional system is constructed to deal with the acceleration saturation problem; its states are used for guidance law design and stability analysis. Moreover, the target acceleration is considered bounded disturbance, but the upper bound is not required to be known in advance, whereas the upper bound is estimated online by a designed adaptive law. Next, finite-time stability of the guidance system is strictly proved by using a Lyapunov method. Finally, numerical simulations are presented to demonstrate the excellent guidance performances of the proposed guidance law in terms of accuracy and efficiency.

Three-dimensional suboptimal guidance law based on θ – D technique and nonlinear disturbance observer

2019 ◽  
Vol 233 (14) ◽  
pp. 5122-5133
Author(s):  
Chaoyuan Man ◽  
Rongjie Liu ◽  
Shihua Li
Keyword(s):  
Disturbance Observer ◽  
Three Dimensional ◽  
Guidance System ◽  
Nonlinear Disturbance Observer ◽  
Guidance Law ◽  
Quadratic Performance Index ◽  
Unknown Disturbances ◽  
Quadratic Performance ◽  
Nonlinear Disturbance ◽  
Hamilton Jacobi Bellman

In this paper, a nonlinear suboptimal guidance system is presented for the missile targeting an unknown arbitrary target. An integrated quadratic performance index is minimized in this guidance law, and the whole design is based on the exact 3D nonlinear missile-target dynamics without any linearization. Considering that the Hamilton–Jacobi–Bellman equation of a nonlinear system is quite difficult to be solved, the [Formula: see text] method is used to obtain the approximate solution without complicated online computations. Moreover, the target accelerations are regarded as the unknown disturbances, and the robustness against the target maneuvering and the external disturbances is enhanced by introducing the feedforward compensation based on the nonlinear disturbance observer. In addition, no priori knowledge like the time-to-go is needed in this suboptimal guidance law. Simulation studies show that the proposed composite guidance system can guarantee that the missile intercepts the arbitrary maneuvering target with satisfied performance.

Three-dimensional finite-time guidance law based on sliding mode adaptive RBF neural network against a highly manoeuvering target

2022 ◽  
pp. 1-20
Author(s):  
G. Wu ◽  
K. Zhang ◽  
Z. Han
Keyword(s):  
Neural Network ◽  
Finite Time ◽  
Sliding Mode ◽  
Rbf Neural Network ◽  
Three Dimensional ◽  
Lyapunov Theory ◽  
Guidance System ◽  
Guidance Law ◽  
Target Acceleration ◽  
Terminal Guidance

Abstract In order to intercept a highly manoeuvering target with an ideal impact angle in the three-dimensional space, this paper promises to probe into the problem of three-dimensional terminal guidance. With the goal of the highly target acceleration and short terminal guidance time, a guidance law, based on the advanced fast non-singular terminal sliding mode theory, is designed to quickly converge the line-of-sight (LOS) angle and the LOS angular rate within a finite time. In the design process, the target acceleration is regarded as an unknown boundary external disturbance of the guidance system, and the RBF neural network is used to estimate it. In order to improve the estimation accuracy of RBF neural network and accelerate its convergence, the parameters of RBF neural network are adjusted online in real time. At the same time, an adaptive law is designed to compensate the estimation error of the RBF neural network, which improves the convergence speed of the guidance system. Theoretical analysis demonstrates that the state and the sliding manifold of the guidance system converge in finite time. According to Lyapunov theory, the stability of the system can be guaranteed by online adjusting the parameters of RBF neural network and adaptive parameters. The numerical simulation results verify the effectiveness and superiority of the proposed guidance law.

3D Guidance Law with INS/IR Integration for Increasing Penetration Force

2012 ◽  
Vol 548 ◽  
pp. 719-723
Author(s):  
Qiang Xing ◽  
Wan Chun Chen ◽  
Bao Yin Ming
Keyword(s):  
Electromagnetic Interference ◽  
Three Dimensional ◽  
Guidance System ◽  
Flight Vehicle ◽  
Guidance Law ◽  
Infrared Seeker ◽  
Optimal Guidance ◽  
Penetration Force ◽  
Modern Warfare ◽  
3D Guidance

In the modern warfare, the trajectory of flight vehicle was required to have the ability to be adjusted in specified shape to increasing the penetration force. This paper deals with the guidance law and data fusion system to impact a target in specified direction for precision guided munitions. A three-dimensional guidance law is designed by combining the optimal guidance law and terminal acceleration tuning methodology. A new configuration of Extended Kalman Filter (EKF) is employed to obtain the range and angle information from INS and infrared seeker to improve the survivability of guidance system in the circumstance with strong electromagnetic interference.

scholarly journals Guidance and Control Method for Vehicle with Strap-down Seeker

2019 ◽  
Vol 291 ◽  
pp. 01003
Author(s):  
Li Fugui ◽  
Jia Shengwei ◽  
Tong Zeyou ◽  
Zhao Changjian ◽  
Li Yahui ◽  
...  
Keyword(s):  
Kalman Filter ◽  
Extended Kalman Filter ◽  
Control Method ◽  
Guidance System ◽  
Measurement Unit ◽  
Flight Vehicle ◽  
Guidance And Control ◽  
Guidance Law ◽  
Optimal Guidance ◽  
And Control

Guidance and control method was presented in this paper for flight vehicle with a strap-down seeker. Firstly, an extended Kalman filter was constructed in LOS (line of sight) coordinate system to estimate the guidance signal based on the information measured by strap-down seeker and inertial measurement unit. Secondly, an optimal guidance law which could reduce the target maneuvering and guidance system dynamics was proposed. Thirdly, three-loop acceleration autopilot with pseudo-angle of attack feedback was presented to control the flight vehicle. Finally, the proposed methods were simulated under typical condition. The simulation results demonstrated that the proposed methods were valid, and good performance could be achieved by the guidance and control method with the guidance signal estimated by the extended Kalman filter.

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