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.

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.

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.

Three-dimensional integrated guidance and control for terminal angle constrained attack against ground maneuvering target

2018 ◽  
Vol 233 (7) ◽  
pp. 2393-2412
Author(s):  
Chao Lai ◽  
Weihong Wang ◽  
Zhenghua Liu ◽  
Zheng Ma
Keyword(s):  
Three Dimensional ◽  
Dynamic Surface Control ◽  
State Observer ◽  
Extended State Observer ◽  
Extended State ◽  
Dynamic Surface ◽  
Guidance And Control ◽  
Integrated Guidance And Control ◽  
Nonlinear Extended State Observer ◽  
And Control

A neuro-adaptive fast terminal sliding-mode dynamic surface control method based on a finite-time stable nonlinear extended state observer is applied to integrated guidance and control design for skid-to-turn missile attacking a ground maneuvering target with terminal angle constraints. A three-dimensional integrated guidance and control design model against a maneuvering target for skid-to-turn missile is established without the assumption that the missile velocity vector and the line of sight coincide with each other. The non-singular fast terminal sliding surface is applied to construct the first error surface of dynamic surface control and the first virtual control law is designed to guarantee hitting accuracy with desired terminal angles. The finite-time stable nonlinear extended state observer is designed separately to estimate uncertainties in the system. And the neuro-adaptive technique is applied to compensate estimation errors of nonlinear extended state observer by training a three-layer feedforward neural network online. Synthesizing all of above, a neuro-adaptive fast terminal sliding-mode dynamic surface control based on nonlinear extended state observer is derived on Lyapunov stability theory, which guarantees stability of the system. Finally, the numerical simulations are conducted to demonstrate the effectiveness of the proposed three-dimensional integrated guidance and control scheme.

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