An Guidance and Control Method with Feedforward Compensation for Target Tracking by Satellite

2020 ◽  
Author(s):  
Ziyao Xu ◽  
Peng Xu ◽  
Rui Peng ◽  
Qidong Lu ◽  
Shengwen Li
Keyword(s):  
Target Tracking ◽  
Control Method ◽  
Guidance And Control ◽  
And Control

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.

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.

Horizontal path following for underactuated AUV based on dynamic circle guidance

Robotica ◽  
2015 ◽  
Vol 35 (4) ◽  
pp. 876-891 ◽  
Author(s):  
Huang Xinjing ◽  
Li Yibo ◽  
Du Fei ◽  
Jin Shijiu
Keyword(s):  
Control Method ◽  
Autonomous Underwater Vehicles ◽  
Path Following ◽  
Mapping Function ◽  
Convex Mapping ◽  
Guidance And Control ◽  
Path Following Control ◽  
And Control ◽  
Cross Track ◽  
Path Point

SUMMARYA 2D path following control method for Autonomous Underwater Vehicles (AUVs) based on dynamic circle heading modification (DCHM) is presented. The method makes a dynamic auxiliary circle, whose radius depends on the cross-track error e, to intersect the desired path to get a new expected path point, and then determines a modified expected heading for the AUV. The guidance function is achieved by a direct mapping between e and the heading modification value Ψm. Several cases are tested in order to demonstrate the performance of the guidance and control method based on DCHMs for a real AUV. Results show that methods using a convex mapping function between e and Ψm based on our new idea can easily achieve a better convergence of path following, and reduce the error between the actual and desired heading angles. We can also customize a discretionary mapping between e and Ψm to get better path following performance.

scholarly journals The Quadrotor Dynamic Modeling and Indoor Target Tracking Control Method

2014 ◽  
Vol 2014 ◽  
pp. 1-9 ◽  
Author(s):  
Dewei Zhang ◽  
Hui Qi ◽  
Xiande Wu ◽  
Yaen Xie ◽  
Jiangtao Xu
Keyword(s):  
Target Tracking ◽  
Dynamic Model ◽  
Nonlinear Dynamic ◽  
Tracking Control ◽  
Feedback Linearization ◽  
Control Method ◽  
Measurement Unit ◽  
Control Algorithms ◽  
Nonlinear Dynamic Model ◽  
And Control

A reliable nonlinear dynamic model of the quadrotor is presented. The nonlinear dynamic model includes actuator dynamic and aerodynamic effect. Since the rotors run near a constant hovering speed, the dynamic model is simplified at hovering operating point. Based on the simplified nonlinear dynamic model, the PID controllers with feedback linearization and feedforward control are proposed using the backstepping method. These controllers are used to control both the attitude and position of the quadrotor. A fully custom quadrotor is developed to verify the correctness of the dynamic model and control algorithms. The attitude of the quadrotor is measured by inertia measurement unit (IMU). The position of the quadrotor in a GPS-denied environment, especially indoor environment, is estimated from the downward camera and ultrasonic sensor measurements. The validity and effectiveness of the proposed dynamic model and control algorithms are demonstrated by experimental results. It is shown that the vehicle achieves robust vision-based hovering and moving target tracking control.

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.

Intelligent Control Method of Ground to Air Missile Based on FCMAC

2011 ◽  
Vol 128-129 ◽  
pp. 168-171
Author(s):  
Gang Li ◽  
Hao He ◽  
Gang Fang ◽  
Jian Feng Wu
Keyword(s):  
Neural Network ◽  
Intelligent Control ◽  
Fuzzy Neural Network ◽  
Control Method ◽  
Basic Structure ◽  
Control Methods ◽  
Missile Guidance ◽  
Guidance And Control ◽  
Fuzzy Neural ◽  
And Control

Intelligent control methods of missile guidance and control system (GACS) are studied in this paper. Secondly, the component and principle of GACS is introduced. Based on the fuzzy neural network, this paper constructs a basic structure of the intelligent control method of missile. Meanwhile, a new intelligent control method of rolling channel of missile based on Fuzzy Cerebella Model Articulation Controller (FCMAC) is designed. Under complicated environmental conditions, the missile can be accurately controlled with this method. Finally, the application value is illustrated. It’s very meaningful to improve the combat capability.

Sign in / Sign up

Export Citation Format

Share Document