Three-dimensional cooperative guidance laws against stationary and maneuvering targets

In order to improve the guiding accuracy in intercepting the hypersonic vehicle, this article presents a finite-time guidance law based on the observer and head-pursuit theory. First, based on a two-dimensional model between the interceptor and target, this study applies the fast power reaching law to head-pursuit guidance law so that it can alleviate the chattering phenomenon and ensure the convergence speed. Second, target maneuvers are considered as system disturbances, and the head-pursuit guidance law based on an observer is proposed. Furthermore, this method is extended to a three-dimensional case. Finally, comparative simulation results further verify the superiority of the guidance laws designed in this article.

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Multiple missiles fixed-time cooperative guidance without measuring radial velocity for maneuvering targets interception

ISA Transactions ◽

10.1016/j.isatra.2021.07.023 ◽

2021 ◽

Author(s):

Peng Zhang ◽

Xiaoyu Zhang

Keyword(s):

Radial Velocity ◽

Fixed Time ◽

Maneuvering Targets ◽

Multiple Missiles ◽

Cooperative Guidance

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3D Nonlinear Guidance Law for Bank-to-Turn Missile

Advanced Materials Research ◽

10.4028/www.scientific.net/amr.317-319.727 ◽

2011 ◽

Vol 317-319 ◽

pp. 727-733

Author(s):

Shuang Chun Peng ◽

Liang Pan ◽

Tian Jiang Hu ◽

Lin Cheng Shen

Keyword(s):

Three Dimensional ◽

Lyapunov Theory ◽

Line Of Sight ◽

Rate Model ◽

Guidance Law ◽

Terminal Constraints ◽

Guidance Laws ◽

3D Guidance ◽

Guidance Model ◽

Vector Description

A new three-dimensional (3D) nonlinear guidance law is proposed and developed for bank-to-turn (BTT) with motion coupling. First of all, the 3D guidance model is established. In detail, the line-of-sight (LOS) rate model is established with the vector description method, and the kinematics model is divided into three terms of pitching, swerving and coupling, then by using the twist-based method, the LOS direction changing model is built for designing the guidance law with terminal angular constraints. Secondly, the 3D guidance laws are designed with Lyapunov theory, corresponding to no terminal constraints and terminal constraints, respectively. And finally, the simulation results show that the proposed guidance law can effectively satisfy the guidance precision requirements of BTT missile.

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A new three-dimensional guidance law based on reduced-order extended state observer for highly maneuvering targets

2021 IEEE 10th Data Driven Control and Learning Systems Conference (DDCLS) ◽

10.1109/ddcls52934.2021.9455533 ◽

2021 ◽

Author(s):

Pengjuan Ma ◽

Sen Chen ◽

Zhiliang Zhao

Keyword(s):

Three Dimensional ◽

State Observer ◽

Extended State Observer ◽

Extended State ◽

Reduced Order ◽

Guidance Law ◽

Maneuvering Targets

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Proportional Navigation (PN) Based Tracking of Ground Targets by Quadrotor UAVs

Volume 1: Aerial Vehicles; Aerospace Control; Alternative Energy; Automotive Control Systems; Battery Systems; Beams and Flexible Structures; Biologically-Inspired Control and its Applications; Bio-Medical and Bio-Mechanical Systems; Biomedical Robots and Rehab; Bipeds and Locomotion; Control Design Methods for Adv. Powertrain Systems and Components; Control of Adv. Combustion Engines, Building Energy Systems, Mechanical Systems; Control, Monitoring, and Energy Harvesting of Vibratory Systems ◽

10.1115/dscc2013-3887 ◽

2013 ◽

Cited By ~ 2

Author(s):

Ruoyu Tan ◽

Manish Kumar

Keyword(s):

Target Tracking ◽

Proportional Navigation ◽

Tracking Method ◽

Maneuvering Targets ◽

Time Optimal ◽

Aerial Vehicle ◽

Quadrotor Uavs ◽

The One ◽

Rotary Wing ◽

Guidance Laws

This paper addresses the problem of controlling a rotary wing Unmanned Aerial Vehicle (UAV) tracking a target moving on ground. The target tracking problem by UAVs has received much attention recently and several techniques have been developed in literature most of which have been applied to fixed wing aircrafts. The use of quadrotor UAVs, the subject of this paper, for target tracking presents several challenges especially for highly maneuvering targets since the development of time-optimal controller (required if target is maneuvering fast) for quadrotor UAVs is extremely difficult due to highly non-linear dynamics. The primary contribution of this paper is the development of a proportional navigation (PN) based method and its implementation on quad-rotor UAVs to track moving ground target. The PN techniques are known to be time-optimal in nature and have been used in literature for developing guidance systems for missiles. There are several types of guidance laws that come within the broad umbrella of the PN method. The paper compares the performance of these guidance laws for their application on quadrotors and chooses the one that performs the best. Furthermore, to apply this method for target tracking instead of the traditional objective of target interception, a switching strategy has also been designed. The method has been compared with respect to the commonly used Proportional Derivative (PD) method for target tracking. The experiments and numerical simulations performed using maneuvering targets show that the proposed tracking method not only carries out effective tracking but also results into smaller oscillations and errors when compared to the widely used PD tracking method.

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