scholarly journals New Integrated Guidance and Control of Homing Missiles with an Impact Angle against a Ground Target

2018 ◽  
Vol 2018 ◽  
pp. 1-10 ◽  
Author(s):  
Shengjiang Yang ◽  
Jianguo Guo ◽  
Jun Zhou
Keyword(s):  
Control System ◽  
Control Method ◽  
Sliding Mode ◽  
Lyapunov Stability Theory ◽  
Impact Angle ◽  
Guidance And Control ◽  
Ground Target ◽  
Integrated Guidance And Control ◽  
And Control ◽  
The Impact

A new integrated guidance and control (IGC) law is investigated for a homing missile with an impact angle against a ground target. Firstly, a control-oriented model with impact angle error of the IGC system in the pitch plane is formulated by linear coordinate transformation according to the motion kinematics and missile dynamics model. Secondly, an IGC law is proposed to satisfy the impact angle constraint and to improve the rapidity of the guidance and control system by combining the sliding mode control method and nonlinear extended disturbance observer technique. Thirdly, stability of the closed-loop guidance and control system is proven based on the Lyapunov stability theory, and the relationship between the accuracy of the impact angle and the estimate errors of nonlinear disturbances is derived from stability of the sliding mode. Finally, simulation results confirm that the proposed IGC law can improve the performance of the missile guidance and control system against a ground target.

Integrated guidance and control of interceptors with impact angle constraint against a high-speed maneuvering target

2019 ◽  
Vol 233 (14) ◽  
pp. 5192-5204
Author(s):  
Guanjie Hu ◽  
Jianguo Guo ◽  
Jun Zhou
Keyword(s):  
Control System ◽  
High Speed ◽  
Control Method ◽  
Impact Angle ◽  
Adaptive Sliding Mode Control ◽  
Guidance And Control ◽  
Maneuvering Target ◽  
Integrated Guidance And Control ◽  
And Control ◽  
Impact Angle Constraint

An integrated guidance and control method is investigated for interceptors with impact angle constraint against a high-speed maneuvering target. Firstly, a new control-oriented model with impact angle constraint of the integrated guidance and control system is built in the pitch plane by combining the engagement kinematics and missile dynamics model between the interceptor and target. Secondly, the flight path angle of the target is estimated by extended Kalman filter in order to transform the terminal impact angle constraint into the terminal line-of-sight angle constraint. Thirdly, a nonlinear adaptive sliding mode control law of the integrated guidance and control system is designed in order to directly obtain the rudder deflection command, which eliminates time delay caused by the traditional backstepping control method. Then the Lyapunov stability theory is used to prove the stability of the whole closed-loop integrated guidance and control system. Finally, the simulation results confirm that the integrated guidance and control method proposed in this paper can effectively improve the interception performance of the interceptor to a high-speed maneuvering target.

scholarly journals Integrated Guidance and Control Based Air-to-Air Autonomous Attack Occupation of UCAV

2016 ◽  
Vol 2016 ◽  
pp. 1-18
Author(s):  
Chang Luo ◽  
Jie Wang ◽  
Hanqiao Huang ◽  
Pengfei Wang
Keyword(s):  
Control System ◽  
Dynamic Models ◽  
Control Method ◽  
Sliding Mode ◽  
Search Algorithm ◽  
Pattern Search ◽  
Adaptive Sliding Mode Control ◽  
Guidance And Control ◽  
Integrated Guidance And Control ◽  
And Control

An approach of air-to-air autonomous attack occupation for Unmanned Combat Aerial Vehicles (UCAVs) is proposed to improve attack precision and combat effectiveness. According to the shortage of UCAV in the task of attack occupation, kinematic and dynamic models of UCAV and missile loaded on it are formed. Then, attack zone and no-escape zone are calculated by pattern search algorithm, and the optimum attack position is indicated. To arrive at the optimum attack position accurately with restriction of gesture, a novel adaptive sliding mode control method is suggested to design the integrated guidance and control system of UCAV in the process of autonomous attack occupation. Key parameters of the control system are adaptively regulated, which further economize control energy at the same time. The simulation results show that compared with traditional methods our approach can guide the UCAV to the optimum attack position with stable gesture and economize nearly 25% control energy.

scholarly journals Integrated Guidance and Control of Multiple Interceptors with Impact Angle Constraints Considered

2019 ◽  
Vol 37 (2) ◽  
pp. 273-282
Author(s):  
Xiang Liu ◽  
Xiaogeng Liang
Keyword(s):  
Cooperative Control ◽  
Control Algorithm ◽  
Control Method ◽  
Impact Angle ◽  
Dynamic Surface ◽  
Guidance And Control ◽  
Integrated Guidance And Control ◽  
And Control ◽  
Impact Angle Constraint ◽  
Distributed Cooperative Control

To solve the multi-interceptor coordination problem and to intercept the target with impact angle constraint, a novel distributed cooperative control algorithm with impact angle constraint based on integrated guidance and control is proposed. First, the mathematic model of integrated guidance and control is established by combining the interceptor-target relative motion model with the dynamic equation of the interceptor on pitch plane. The time varying gain extended state observer is developed to estimate and compensate the unknown disturbance. Based on the estimated value and fast nonsingular dynamic surface sliding control method, the IGC algorithm of leader is given; Then, based on distributed cooperative "leader-follower" model, the cooperative control strategy of multi-interceptor is designed, and gives out speeds in two directions on pitch plane, which are transformed to the command of total velocity and trajectory angle based on kinematic relations. Finally, to control the follower, the time varying gain extended state observer and the dynamic surface sliding control method are adopted. The simulation results demonstrate the effectiveness of the distributed cooperative control algorithm.

scholarly journals Integrated Guidance and Control of Interceptor Missile Based on Asymmetric Barrier Lyapunov Function

2019 ◽  
Vol 2019 ◽  
pp. 1-17
Author(s):  
Xiang Liu ◽  
Xiaogeng Liang
Keyword(s):  
Lyapunov Function ◽  
Control Method ◽  
Sliding Mode ◽  
Aerodynamic Force ◽  
Dynamic Control ◽  
Dynamic Surface ◽  
Guidance And Control ◽  
Barrier Lyapunov Function ◽  
Integrated Guidance And Control ◽  
And Control

In this study, a novel integrated guidance and control (IGC) algorithm based on an IGC method and the asymmetric barrier Lyapunov function is designed; this algorithm is designed for the interceptor missile which uses a direct-force/aerodynamic-force control scheme. First, by considering the coupling between the pitch and the yaw channels of the interceptor missile, an IGC model of these channels is established, and a time-varying gain extended state observer (TVGESO) is designed to estimate unknown interferences in the model. Second, by considering the system output constraint problem, an asymmetric barrier Lyapunov function and a dynamic surface sliding-mode control method are employed to design the control law of the pitch and yaw channels to obtain the desired control moments. Finally, in light of redundancy in such actuators as aerodynamic rudders and jet devices, a dynamic control allocation algorithm is designed to assign the desired control moments to the actuators. Moreover, the results of simulations show that the IGC algorithm based on the asymmetric barrier Lyapunov function for the interceptor missile allows the outputs to meet the constraints and improves the stability of the control system of the interceptor missile.

scholarly journals Integrated Guidance and Control Method for the Interception of Maneuvering Hypersonic Vehicle Based on High Order Sliding Mode Approach

2015 ◽  
Vol 2015 ◽  
pp. 1-19 ◽  
Author(s):  
Kang Chen ◽  
Bin Fu ◽  
Yuening Ding ◽  
Jie Yan
Keyword(s):  
Fourth Order ◽  
Control Method ◽  
Sliding Mode ◽  
High Order ◽  
Control Input ◽  
Guidance And Control ◽  
Near Space ◽  
Sliding Manifold ◽  
Integrated Guidance And Control ◽  
And Control

This paper focuses on the integrated guidance and control (IGC) method applied in the interception of maneuvering near space hypersonic vehicles using the homogeneous high order sliding mode (HOSM) approach. The IGC model is derived by combining the target-missile relative motion and dynamic equations. Then, a fourth-order sliding mode controller is implemented in the augmented IGC model. To estimate the high order derivatives of the sliding manifold which is required in the HOSM method, an Arbitrary Order Robust Exact Differentiator is presented. At last, the idea of virtual control is introduced to alleviate the chattering of the control input without using any saturation functions which may lead to a loss of the robustness. And the stability of the closed-loop system with presented fourth-order homogeneous HOSM controller is also proved theoretically. Finally, simulation results are provided and analyzed to demonstrate the effectiveness of the proposed method in three typical engagement scenarios.

scholarly journals Research on Integrated Guidance and Control of Distributed Cooperation of Multi-Interceptor with State Coupling

2018 ◽  
Vol 2018 ◽  
pp. 1-15
Author(s):  
Xiang Liu ◽  
Xiaogeng Liang
Keyword(s):  
Sliding Mode Control ◽  
Cooperative Control ◽  
Control Method ◽  
Sliding Mode ◽  
Distributed Network ◽  
Dynamic Surface ◽  
Guidance And Control ◽  
Mode Control ◽  
Integrated Guidance And Control ◽  
And Control

With the aim of achieving cooperative target interception by using multi-interceptor, a distributed cooperative control algorithm of the multi-interceptor with state coupling is proposed based on the IGC (integrated guidance and control) method. Considering the coupling relationship between the pitch and ya w channels, a state coupling “leader” IGC model is established, an FTDO (finite-time disturbance observer) is designed for estimating the unknown interference of the model, and the “leader” controller is designed according to the adaptive dynamic surface sliding-mode control law. Secondly, the cooperative control strategy of the multi-interceptor is designed with the “leader-follower” distributed network mode to obtain the speed in the three directions of the interceptor in air and transform them to the general flight speed, trajectory inclination angle, and trajectory deflection instruction by using the transformational relation of kinematics. Finally, the “follower” controller is designed with the FTDO and dynamic surface sliding-mode control. The designed multi-interceptor distributed cooperative IGC algorithm with state coupling has good stability according to the simulation results of two different communication topologies.

scholarly journals Design of integrated Guidance and control system in the pitch channel using observer based chattering free sliding mode theory

2020 ◽  
Vol 14 (1) ◽  
pp. 49-63
Author(s):  
Mohammad Javad Rajabi ◽  
Ahmad Reza Vali ◽  
Vahid Behnamgol ◽  
◽  
◽  
...  
Keyword(s):  
Control System ◽  
Sliding Mode ◽  
Mode Theory ◽  
Guidance And Control ◽  
Chattering Free ◽  
Integrated Guidance And Control ◽  
And Control

Finite-time integrated guidance and control system for hypersonic vehicles

2020 ◽  
pp. 014233122094193
Author(s):  
Chong Zhenyu ◽  
Guo Jianguo ◽  
Zhao Bin ◽  
Guo Zongyi ◽  
Lu Xiaodong
Keyword(s):  
Control System ◽  
Finite Time ◽  
Lyapunov Stability Theory ◽  
Hypersonic Vehicles ◽  
Nonlinear Simulation ◽  
Loop Control ◽  
Finite Time Stability ◽  
Guidance And Control ◽  
Integrated Guidance And Control ◽  
And Control

A finite-time integrated guidance and control (IGC) method is proposed in this study for hypersonic vehicles. The IGC dynamic model is initially built by combining the 3D relative kinematics and dynamics equations. Then, by introducing the adaptive control technology and the backstepping approach, an IGC scheme with adaptive parameters is presented to guarantee the finite-time stability of a closed-loop control system on the basis of Lyapunov stability theory. Nonlinear simulation results demonstrate the effectiveness and robustness of the proposed IGC method for hypersonic vehicles compared with other robust IGC methods.

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