Nonlinear integrated guidance and control based on adaptive backstepping scheme

2017 ◽  
Vol 89 (3) ◽  
pp. 415-424 ◽  
Author(s):  
Seyed Hamed Seyedipour ◽  
Mohsen Fathi Jegarkandi ◽  
Saeed Shamaghdari
Keyword(s):  
Nonlinear System ◽  
Nonlinear Model ◽  
Adaptive Backstepping ◽  
Content Type ◽  
Guidance And Control ◽  
Air Vehicle ◽  
Backstepping Controller ◽  
Integrated Guidance And Control ◽  
And Control ◽  
Adaptive Backstepping Controller

Purpose The purpose of this paper is to design an adaptive nonlinear controller for a nonlinear system of integrated guidance and control. Design/methodology/approach A nonlinear integrated guidance and control approach is applied to a homing, tail-controlled air vehicle. Adaptive backstepping controller technique is used to deal with the problem, and the Lyapanov theory is used in the stability analysis of the nonlinear system. A nonlinear model of normal force coefficient is obtained from an existing nonlinear model of lift coefficient which was validated by open loop response. The simulation was performed in the pitch plane to prove the benefits of the proposed scheme; however, it can be readily extended to all the three axes. Findings Monte Carlo simulations indicate that using nonlinear adaptive backstepping formulation meaningfully improves the performance of the system, while it ensures stability of a nonlinear system. Practical implications The proposed method could be used to obtain better performance of hit to kill accuracy without the expense of control effort. Originality/value A nonlinear adaptive backstepping controller for nonlinear aerodynamic air vehicle is designed and guaranteed to be stable which is a novel-based approach to the integrated guidance and control. This method makes noticeable performance improvement, and it can be used with hit to kill accuracy.

Finite-time convergence of an nth nonlinear system with unmatched disturbance and its application in integrated guidance and control system

2018 ◽  
Vol 09 (05) ◽  
pp. 1850039 ◽  
Author(s):  
Cong Zhang
Keyword(s):  
Control System ◽  
Nonlinear System ◽  
Finite Time ◽  
Recursive Procedure ◽  
Sign Function ◽  
Guidance And Control ◽  
Finite Time Convergence ◽  
Integrated Guidance And Control ◽  
Power Integrator ◽  
And Control

The finite-time convergence problem of an [Formula: see text]th nonlinear system with unmatched disturbance is primarily studied in this paper. During the recursive procedure, a new finite-time controller is designed and proven by adding a sign function and a power integrator. Meanwhile, a [Formula: see text] positive definite and proper Lyapunov function, which satisfies the finite-time Lyapunov stability law, is designed. Finally, the designed finite-time controller is applied to some examples and an application of integrated guidance and control system to test and verify its advantage and practicability.

scholarly journals Three-Dimensional Integrated Guidance and Control for Near Space Interceptor Based on Robust Adaptive Backstepping Approach

2016 ◽  
Vol 2016 ◽  
pp. 1-11 ◽  
Author(s):  
Changsheng Gao ◽  
Chunwang Jiang ◽  
Yan Zhang ◽  
Wuxing Jing
Keyword(s):  
Relative Motion ◽  
Upper Bound ◽  
Three Dimensional ◽  
Backstepping Method ◽  
Adaptive Backstepping ◽  
Guidance And Control ◽  
Near Space ◽  
Integrated Guidance And Control ◽  
Robust Adaptive ◽  
And Control

This study presents a novel integrated guidance and control method for near space interceptor, considering the coupling among different channels of the missile dynamics, which makes the most of the overall performance of guidance and control system. Initially, three-dimensional integrated guidance and control model is employed by combining the interceptor-target relative motion model with the nonlinear dynamics of the interceptor, which establishes a direct relationship between the interceptor-target relative motion and the deflections of aerodynamic fins. Subsequently, regarding the acceleration of the target as bounded uncertainty of the system, an integrated guidance and control algorithm is designed based on robust adaptive backstepping method, with the upper bound of the uncertainties unknown. Moreover, a nonlinear tracking differentiator is introduced to reduce the “compute explosion” caused by backstepping method. It is proved that tracking errors of the state and the upper bound of the uncertainties converge to the neighborhoods of the origin exponentially. Finally, simulations results show that, compared to the conventional guidance and control design, the algorithm proposed in this paper has greater advantages in miss distance, required normal overload, and flight stability, especially when attacking high-maneuvering targets.

scholarly journals Adaptive Integrated Guidance and Fault Tolerant Control Using Backstepping and Sliding Mode

2015 ◽  
Vol 2015 ◽  
pp. 1-7 ◽  
Author(s):  
Mohsen Fathi Jegarkandi ◽  
Asghar Ashrafifar ◽  
Reza Mohsenipour
Keyword(s):  
Fault Tolerant ◽  
Sliding Mode ◽  
Fault Simulation ◽  
Actuator Fault ◽  
Adaptive Backstepping ◽  
Guidance And Control ◽  
Proposed Model ◽  
Integrated Guidance And Control ◽  
Homing Missiles ◽  
And Control

A new method of integrated guidance and control for homing missiles with actuator fault against manoeuvring targets is proposed. Model of the integrated guidance and control system in the pitch plane with actuator fault and some uncertainty is developed. A control law using combination of adaptive backstepping and sliding mode approaches is designed to achieve interception in the presence of bounded uncertainties and actuator fault. Simulation results show that new approach has better performance than adaptive backstepping and has good performance in the presence of actuator fault.

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.

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