scholarly journals Guidance Law and Neural Control for Hypersonic Missile to Track Targets

2016 ◽  
Vol 2016 ◽  
pp. 1-10 ◽  
Author(s):  
Wenxing Fu ◽  
Binbin Yan ◽  
Xiaofei Chang ◽  
Jie Yan
Keyword(s):  
Neural Control ◽  
Controller Design ◽  
Sliding Mode ◽  
External Disturbance ◽  
Control Laws ◽  
Guidance And Control ◽  
Maneuvering Target ◽  
Guidance Law ◽  
Control Command ◽  
And Control

Hypersonic technology plays an important role in prompt global strike. Because the flight dynamics of a hypersonic vehicle is nonlinear, uncertain, and highly coupled, the controller design is challenging, especially to design its guidance and control law during the attack of a maneuvering target. In this paper, the sliding mode control (SMC) method is used to develop the guidance law from which the desired flight path angle is derived. With the desired information as control command, the adaptive neural control in discrete time is investigated ingeniously for the longitudinal dynamics of the hypersonic missile. The proposed guidance and control laws are validated by simulation of a hypersonic missile against a maneuvering target. It is demonstrated that the scheme has good robustness and high accuracy to attack a maneuvering target in the presence of external disturbance and missile model uncertainty.

Performance analysis of differential geometric guidance law against high-speed target with arbitrarily maneuvering acceleration

2018 ◽  
Vol 233 (10) ◽  
pp. 3547-3563 ◽  
Author(s):  
Ke-Bo Li ◽  
Wen-Shan Su ◽  
Lei Chen
Keyword(s):  
High Speed ◽  
Control System Design ◽  
Proportional Navigation ◽  
Full Account ◽  
Guidance And Control ◽  
Maneuvering Target ◽  
Guidance Law ◽  
Classical Differential Geometry ◽  
Relative Dynamics ◽  
And Control

The interception of high-speed target with an arbitrary maneuvering acceleration causes serious troubles to the guidance and control system design of airborne missile. A novel guidance law based on the classical differential geometry curve theory was proposed not long ago. Although it is believed and numerically demonstrated that this differential geometric guidance law (DGGL) is superior to the classical pure proportional navigation (PPN) in intercepting high-speed targets, its performance has not been thoroughly analyzed. In this paper, using the Lyapunov-like approach, the performance of DGGL against the high-speed target with an arbitrary but upper-bounded maneuvering acceleration is well studied. The upper bounds of the LOS rate and commanded acceleration of DGGL are obtained, and conditions that guarantee the capture of this type of maneuvering target are also presented. The nonlinear relative dynamics between the missile and target is taken into full account. Finally, the proposed theoretical findings are demonstrated by numerical simulation examples.

Suboptimal Guidance and Control Design for a Missile with Onboard Strapdown Seeker

2011 ◽  
Vol 110-116 ◽  
pp. 2513-2520
Author(s):  
Netra Singh ◽  
Manoranjan Sinha
Keyword(s):  
Coupling Effect ◽  
Three Dimensional ◽  
Impact Angle ◽  
Terminal Phase ◽  
Dynamic Inversion ◽  
Control Laws ◽  
Guidance And Control ◽  
Guidance Law ◽  
Hamilton Jacobi Bellman ◽  
And Control

Dynamic inversion control in conjunction with nonlinear suboptimal three dimensional (3-D) guidance law, in terminal phase, is implemented in both the pitch and yaw plane for a short range surface to surface missile with onboard active strapdown seeker. The implemented guidance and control laws intercept the target with a minimum miss distance in addition to meeting the various constraints such as line of sight, seeker field-of-view (FOV), and impact angle. This is achieved using approximate solution to Hamilton-Jacobi-Bellman (HJB) equation [1]. Dynamic inversion control is implemented in two time scales for the inner loop body rate and outer loop angles. Various nonlinearities including that due to the coupling effect between pitch and yaw channels are accounted for in the six-degree-of-freedom (6-DOF) formulation.

Application of Super Twisting Guidance Law Based on Extended State Observer

2013 ◽  
Vol 433-435 ◽  
pp. 1009-1014 ◽  
Author(s):  
Yang Chong ◽  
Ke Zhang
Keyword(s):  
Sliding Mode ◽  
External Disturbance ◽  
State Observer ◽  
Extended State Observer ◽  
Extended State ◽  
Maneuvering Target ◽  
Guidance Law ◽  
Target Acceleration ◽  
Twisting Algorithm ◽  
Miss Distance

In order to intercept high maneuvering target, a super twisting guidance law based on extended state observer (ESO) is proposed. The target acceleration can be defined as external disturbance which can be estimated in ESO and compensated in super twisting guidance law. The super twisting algorithm can effectively decrease the undesired charting which exists in normal sliding mode control. The simulation results which are verified via computer show that this guidance law has strong robustness, target acceleration can be estimated and compensated, and has good miss distance.

INTELLIGENT PASSIVE CONTROL FOR LOWER LIMB REHABILITATION SYSTEM

2013 ◽  
Vol 37 (3) ◽  
pp. 1023-1033 ◽  
Author(s):  
Ming-Shium Hsieh ◽  
Chin-Sheng Chen ◽  
Kuan-Sheng Chien
Keyword(s):  
Passive Control ◽  
Controller Design ◽  
Sliding Mode ◽  
Virtual Work ◽  
External Disturbance ◽  
Angular Position ◽  
Continuous Passive Motion ◽  
Constraint Induced Movement Therapy ◽  
Limb Rehabilitation ◽  
And Control

This paper proposes the design and control of continuous passive motion (CPM) machine based on constraint-induced movement therapy (CIMT). First, the dynamic model of the CPM machine is derived for further controller design by the principal of virtual work. Then, an intelligent sliding-mode control (ISMC) system which involved recurrent Hermite neural network (RHNN) estimator to estimate the unknown external disturbance and uncertainty is proposed to track the angular position and velocity of the CPM machine.

Design of integrated smooth sliding mode of guidance and control for intercepting the hypersonic aircraft

2020 ◽  
pp. 002072092094444
Author(s):  
Qin Zhong ◽  
Yonghua Fan ◽  
Jie Yan ◽  
Xiaofeng Zhang
Keyword(s):  
Sliding Mode ◽  
Variable Structure ◽  
Side Window ◽  
Guidance And Control ◽  
Near Space ◽  
Guidance Law ◽  
Hypersonic Aircraft ◽  
Aerodynamic Control ◽  
Sliding Mode Variable Structure ◽  
And Control

A strategy of intercepting the near-space hypersonic aircraft is proposed, which is based on infrared window guidance, change the guidance law from side window constraint to the fixed lead angle, the sliding mode variable structure guidance law with prefix angle constraint is designed. First, setting up the dynamic model for the end of interceptor with direct force/aerodynamic control, deriving the integrated mathematical model of interceptor’s longitudinal guidance and control. Then, by using smooth sliding mode control, the interceptor’s variable structure guidance law with prefix angle constraint is designed. Last, the simulation results show that the designed guidance law can achieve high precision interception for hypersonic vehicle.

Integrated Guidance, Control and Maneuver for Anti-Vessel Missiles Based on Backstepping Method

2011 ◽  
Vol 69 ◽  
pp. 126-131
Author(s):  
Cong Ying Li ◽  
Jin Yong Yu ◽  
Lei Han ◽  
Wen Guang Zhang
Keyword(s):  
Sliding Mode ◽  
Integrated Design ◽  
Control Law ◽  
Backstepping Method ◽  
Guidance Control ◽  
Guidance And Control ◽  
Guidance Law ◽  
Maneuvering Targets ◽  
And Control ◽  
Accuracy Performance

Integrated guidance, control and maneuver for anti-vessel missiles against vessel targets was studied. Firstly, the integrated guidance and autopilot model of the yaw plane was formulated, the guidance and control law was designed based on the backstepping method and sliding mode control theory. For the unavailable information of the vessel target, an estimating method was given. Integration of guidance and maneuver was realized based on a new guidance law. Finally, to verify the effectiveness and rightness of the integrated design scheme, the simulation of some anti-vessel missile against maneuvering targets had been made, the simulation results showed that high accuracy performance of guidance and control system can be got.

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.

Robust sliding mode guidance and control for soft landing on small bodies

2012 ◽  
Vol 349 (2) ◽  
pp. 493-509 ◽  
Author(s):  
Zhang Zexu ◽  
Wang Weidong ◽  
Li Litao ◽  
Huang Xiangyu ◽  
Cui Hutao ◽  
...  
Keyword(s):  
Sliding Mode ◽  
Soft Landing ◽  
Small Bodies ◽  
Guidance And Control ◽  
And Control
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