scholarly journals Integrated Guidance and Control Design For Time-Constrained Interception

2020 ◽  
Author(s):  
Abhinav Sinha ◽  
Shashi Ranjan Kumar ◽  
Dwaipayan Mukherjee
Keyword(s):  
Sliding Mode ◽  
Control Design ◽  
Lateral Acceleration ◽  
Restrictive Assumption ◽  
Guidance And Control ◽  
Overall Design ◽  
Maneuvering Target ◽  
Wide Range ◽  
Integrated Guidance And Control ◽  
And Control

This paper proposes integrated guidance and control design to intercept a non-maneuvering target at a pre-specified time of interception. The problem is addressed considering nonlinear engagement kinematics and the interceptor is steered using the combined effects of canard as well as tail configurations (dual control interceptors). Different formulations of time-to-go, without the restrictive assumption of interceptor's small heading angle, have been used in deriving the guidance commands, allowing the proposed strategies to remain effective over a wide range of impact time values. A weighted effort allocation scheme, in canard and tail deflections, has been proposed to generate the required lateral acceleration. The overall design uses sliding mode control owing to its simplicity of design. Finally, simulations are presented for various scenarios, including impaired actuator, vindicating the efficacy of the proposed technique.

scholarly journals Integrated Guidance and Control Design For Time-Constrained Interception

2020 ◽  
Author(s):  
Abhinav Sinha ◽  
Shashi Ranjan Kumar ◽  
Dwaipayan Mukherjee
Keyword(s):  
Sliding Mode ◽  
Control Design ◽  
Lateral Acceleration ◽  
Restrictive Assumption ◽  
Guidance And Control ◽  
Overall Design ◽  
Maneuvering Target ◽  
Wide Range ◽  
Integrated Guidance And Control ◽  
And Control

This paper proposes integrated guidance and control design to intercept a non-maneuvering target at a pre-specified time of interception. The problem is addressed considering nonlinear engagement kinematics and the interceptor is steered using the combined effects of canard as well as tail configurations (dual control interceptors). Different formulations of time-to-go, without the restrictive assumption of interceptor's small heading angle, have been used in deriving the guidance commands, allowing the proposed strategies to remain effective over a wide range of impact time values. A weighted effort allocation scheme, in canard and tail deflections, has been proposed to generate the required lateral acceleration. The overall design uses sliding mode control owing to its simplicity of design. Finally, simulations are presented for various scenarios, including impaired actuator, vindicating the efficacy of the proposed technique.

Integral barrier Lyapunov functions-based integrated guidance and control design for strap-down missile with field-of-view constraint

2021 ◽  
pp. 014233122098132
Author(s):  
Bin Zhao ◽  
Zhenxin Feng ◽  
Jianguo Guo
Keyword(s):  
Sliding Mode ◽  
State Equation ◽  
Field Of View ◽  
Feedback Form ◽  
Theoretical Derivation ◽  
Guidance And Control ◽  
Integrated Guidance And Control ◽  
Twisting Algorithm ◽  
And Control ◽  
Special Time

The problem of the integrated guidance and control (IGC) design for strap-down missile with the field-of-view (FOV) constraint is solved by using the integral barrier Lyapunov function (iBLF) and the sliding mode control theory. Firstly, the nonlinear and uncertainty state equation with non-strict feedback form for IGC design is derived by using the strap-down decoupling strategy. Secondly, a novel adaptive finite time disturbance observer is proposed to estimate the uncertainties based on an improved adaptive gain super twisting algorithm. Thirdly, the special time-varying sliding variable is designed and the iBLF is employed to handle the problem of FOV constraint. Theoretical derivation and simulation show that the IGC system is globally uniformly ultimately bounded and the FOV angle constraint is also guaranteed not only during the reaching phase but also during the sliding mode phase.

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 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.

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