scholarly journals Novel Fractional Order Calculus Extended PN for Maneuvering Targets

2017 ◽  
Vol 2017 ◽  
pp. 1-9 ◽  
Author(s):  
Jikun Ye ◽  
Humin Lei ◽  
Jiong Li
Keyword(s):  
Fractional Order ◽  
Memory Function ◽  
Kinematic Model ◽  
Guidance System ◽  
The Novel ◽  
Fractional Order Calculus ◽  
Maneuvering Target ◽  
Guidance Law ◽  
Maneuvering Targets ◽  
Operation Rules

Based on the theory of fractional order calculus (FOC), a novel extended proportional guidance (EPN) law for intercepting the maneuvering target is proposed. In the first part, considering the memory function and filter characteristic of FOC, the novel extended PN guidance algorithm is developed based on the conventional PN after introducing the properties and operation rules of FOC. Further, with the help of FOC theory, the average load and ballistics characteristics of proposed guidance law are analyzed. Then, using the small offset kinematic model, the robustness of the new guidance law against autopilot parameters is studied theoretically by analyzing the sensitivity of the closed loop guidance system. At last, representative numerical results show that the designed guidance law obtains a better performance than the traditional PN for maneuvering target.

scholarly journals A Fuzzy Guidance System for Rendezvous and Pursuit of Moving Targets

Robotics ◽  
2020 ◽  
Vol 9 (4) ◽  
pp. 110
Author(s):  
Michael Alibani ◽  
Mario Innocenti ◽  
Lorenzo Pollini
Keyword(s):  
Direction Of Arrival ◽  
Guidance System ◽  
Target Velocity ◽  
Control Loops ◽  
Maneuvering Target ◽  
Guidance Law ◽  
Maneuvering Targets ◽  
Heading Control ◽  
Rendezvous Point ◽  
Takagi Sugeno

This article presents the development of a fuzzy guidance system (FGS) for unmanned aerial vehicles capable of pursuing and performing rendezvous with static and mobile targets. The system is designed to allow the vehicle to approach a maneuvering target from a desired direction of arrival and to terminate the rendezvous at a constant distance from the target. In order to perform a rendezvous with a maneuvering target, the desired direction of arrival is adjusted over time to always approach the target from behind, so that the aircraft and target velocity vectors become aligned. The proposed guidance system assumes the presence of an autopilot and uses a set of Takagi–Sugeno fuzzy controllers to generate the orientation and speed references for the velocity and heading control loops, given the relative position and velocity between the aircraft and the target. The FGS treats the target as a mobile waypoint in a 4-D space (position in 2-dimensions, desired crossing heading and speed) and guides the aircraft on suitable trajectories towards the target. Only when the vehicle is close enough to the rendezvous point, the guidance law is complemented with an additional linear controller to manage the terminal formation keeping phase. The capabilities of the proposed rendezvous-FGS are verified in simulation on both maneuvering and non-maneuvering targets. Finally, experimental results using a multi-rotor aerial system are presented for both fixed and accelerating targets.

Partial Stabilization Approach to 3-Dimensional Guidance Law Design

2011 ◽  
Vol 133 (6) ◽  
Author(s):  
T. Binazadeh ◽  
M. J. Yazdanpanah
Keyword(s):  
System Dynamics ◽  
The State ◽  
Guidance System ◽  
Missile Guidance ◽  
State Variables ◽  
New Approach ◽  
3 Dimensional ◽  
Guidance Law ◽  
Maneuvering Targets

In this paper, a new approach to design the 3-dimensional missile guidance law, based on partial stabilization, is presented. The approach is based on the classification of the state variables within the guidance system dynamics with respect to their required stabilization properties. The resulting guidance law enables the missile to intercept highly maneuvering targets within a finite interception time. Effectiveness of the proposed guidance law is demonstrated through analysis and simulations.

Fast fixed-time convergent smooth adaptive guidance law with terminal angle constraint for interception of maneuvering targets

2020 ◽  
pp. 095441002096509
Author(s):  
Peng Zhang ◽  
Xiaoyu Zhang
Keyword(s):  
Stability Theory ◽  
Sliding Mode ◽  
Fixed Time ◽  
Guidance System ◽  
Time Stability ◽  
Terminal Sliding Mode ◽  
Guidance Law ◽  
Maneuvering Targets ◽  
System States ◽  
Terminal Angle Constraint

This paper introduces a fast fixed-time guidance law with terminal angle constraint for interception of maneuvering targets, which is based on the structure of singularity-free fast terminal sliding mode and the fixed-time stability theory. Different from the finite-time stability, the fixed-time stability can predefine the maximum stabilization time of system states which is independent on the initial value of system states. Under the proposed guidance law, the guidance system can achieve stabilization within settling time which decides by the parameters of controller. In addition, an adaptive law is proposed which alleviate the chattering of sliding mode and smooths the guidance law. Meanwhile, the proof of the sliding mode manifold and system states fixed-time convergence is given by Lyapunov stability theory. Finally, numerical simulations demonstrate the performance of the proposed guidance law is satisfying.

scholarly journals Extended-State-Observer-Based Collision-Free Guidance Law for Target Tracking of Autonomous Surface Vehicles with Unknown Target Dynamics

Complexity ◽  
2018 ◽  
Vol 2018 ◽  
pp. 1-10 ◽  
Author(s):  
Shengnan Gao ◽  
Zhouhua Peng ◽  
Dan Wang ◽  
Lu Liu
Keyword(s):  
Target Tracking ◽  
State Observer ◽  
Extended State Observer ◽  
Guidance System ◽  
Extended State ◽  
Reduced Order ◽  
Maneuvering Target ◽  
Guidance Law ◽  
Autonomous Surface Vehicle ◽  
Velocity Information

This paper is concerned with the target tracking problem of an autonomous surface vehicle in the presence of a maneuvering target. The velocity information of target is totally unknown to the follower vehicle, and only the relative distance and angle between the target and follower are obtained. First, a reduced-order extended state observer is used to estimate the unknown relative dynamics due to the unavailable velocity of the target. Based on the reduced-order extended state observer, an antidisturbance guidance law for target tracking is designed. The input-to-state stability of the closed-loop target tracking guidance system is analyzed via cascade theory. Furthermore, the above result is extended to the case that collisions between the target and leader are avoided during tracking, and a collision-free target tracking guidance law is developed. The main feature of the proposed guidance law is twofold. First, the target tracking can be achieved without using the velocity information of the target. Second, collision avoidance can be achieved during target tracking. Simulation results show the effectiveness of the proposed antidisturbance guidance law for tracking a maneuvering target with the arbitrary bounded velocity.

scholarly journals Impact Time Guidance Law Considering Autopilot Dynamics Based on Variable Coefficients Strategy for Maneuvering Target

2015 ◽  
Vol 2015 ◽  
pp. 1-10 ◽  
Author(s):  
Wei Shang ◽  
Jie Guo ◽  
Shengjing Tang ◽  
Yueyue Ma ◽  
Yao Zhang
Keyword(s):  
Finite Time ◽  
Sliding Mode ◽  
Variable Coefficients ◽  
Guidance System ◽  
Impact Time ◽  
Maneuvering Target ◽  
Guidance Law ◽  
Convergence Control ◽  
Unknown Disturbance ◽  
The Impact

This paper investigates the terminal guidance problem for the missile intercepting a maneuvering target with impact time constraint. An impact time guidance law based on finite time convergence control theory is developed regarding the target motion as an unknown disturbance. To further improve the performance of the guidance law, an autopilot dynamics which is considered as a first-order lag is taken into consideration. In the proposed method, the coefficients change with the relative distance between missile and target. This variable coefficient strategy ensures that the missile impacts the target at the desired time with little final miss distance. Then it is proved that states of the guidance system converge to sliding mode in finite time under the proposed guidance law. Numerical simulations are presented to demonstrate the effectiveness of the impact time guidance law with autopilot dynamics (ITGAD).

scholarly journals A fractional-order model describing the dynamics of the novel coronavirus (COVID-19) with nonsingular kernel

2021 ◽  
Vol 146 ◽  
pp. 110859
Author(s):  
Ahmed Boudaoui ◽  
Yacine El hadj Moussa ◽  
Zakia Hammouch ◽  
Saif Ullah
Keyword(s):  
Fractional Order ◽  
The Novel ◽  
Order Model ◽  
Fractional Order Model ◽  
Novel Coronavirus

Adjustable impact-time-control guidance law against non-maneuvering target under limited field of view

2021 ◽  
pp. 095441002110129
Author(s):  
Jun-Yong Lee ◽  
Hyeong-Guen Kim ◽  
H Jin Kim
Keyword(s):  
Field Of View ◽  
Control Technique ◽  
Moving Target ◽  
Time Error ◽  
Stationary Target ◽  
Impact Time ◽  
Maneuvering Target ◽  
Time Control ◽  
Guidance Law ◽  
Intercept Point

This article proposes an impact-time-control guidance law that can keep a non-maneuvering moving target in the seeker’s field of view (FOV). For a moving target, the missile calculates a predicted intercept point (PIP), designates the PIP as a new virtual stationary target, and flies to the PIP at the desired impact time. The main contribution of the article is that the guidance law is designed to always lock onto the moving target by adjusting the guidance gain. The guidance law for the purpose is based on the backstepping control technique and designed to regulate the defined impact time error. In this procedure, the desired look angle, which is a virtual control, is designed not to violate the FOV limit, and the actual look angle of the missile is kept within the FOV by tracking the desired look angle. To validate the performance of the guidance law, numerical simulation is conducted with different impact times. The result shows that the proposed guidance law intercepts the moving target at the desired impact time maintaining the target lock-on condition.

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