A Novel Partial Integrated Guidance and Control Scheme Based on Three Dimensional Relative Dynamics

2021 ◽  
Author(s):  
JianHua Wang ◽  
ChengHu Yun ◽  
Zejie Cui ◽  
Long Cheng
Keyword(s):  
Three Dimensional ◽  
Guidance And Control ◽  
Control Scheme ◽  
Relative Dynamics ◽  
Integrated Guidance And Control ◽  
And Control

Active disturbance rejection guidance and control scheme for homing missiles with impact angle constraints

2018 ◽  
Vol 233 (3) ◽  
pp. 1133-1146
Author(s):  
Jian Hua Wang ◽  
Yuan Wen Cai ◽  
Long Cheng ◽  
Yan Li ◽  
Chao Jun Xin ◽  
...  
Keyword(s):  
Disturbance Rejection ◽  
Three Dimensional ◽  
Impact Angle ◽  
Degree Of Freedom ◽  
Guidance And Control ◽  
Active Disturbance Rejection ◽  
Control Scheme ◽  
Homing Missiles ◽  
Six Degree Of Freedom ◽  
And Control

An active disturbance rejection guidance and control scheme for homing missiles with three-dimensional impact angle constraints is proposed. The six-degree-of-freedom dynamical and kinematical models containing model uncertainties and disturbances are established. A strict feedback relative dynamics between the target and homing missile in three-dimensional space are deduced. A reconstructed reduced-order attitude controller design model is proposed. A two-loop control structure with respect to the centroid guidance loop and rotational control loop is conducted to implement the six-degree-of-freedom guidance and control system with the help of second-order sliding mode approach and extended state observers. The tracking loop of the Euler angles of the missile can be elided and the number of six-degree-of-freedom control parameters can be reduced. Finally, the effectiveness and robustness of the newly proposed guidance and control scheme are investigated and verified via six-degree-of-freedom nonlinear simulation studies.

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.

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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