scholarly journals Turning Direction Determination using Error Dynamics-Based Guidance Law for Stationary Target Observation

2014 ◽  
Vol 57 (2) ◽  
pp. 61-68
Author(s):  
Mingu KIM ◽  
Youdan KIM
Keyword(s):  
Stationary Target ◽  
Guidance Law ◽  
Error Dynamics

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.

Nonlinear dynamic image-based visual servoing of a quadrotor

2015 ◽  
Vol 3 (1) ◽  
pp. 1-21 ◽  
Author(s):  
Geoff Fink ◽  
Hui Xie ◽  
Alan F. Lynch ◽  
Martin Jagersand
Keyword(s):  
Visual Servoing ◽  
Lateral Position ◽  
Control Law ◽  
Stationary Target ◽  
Dynamic Image ◽  
Change Of State ◽  
Dependent Change ◽  
Exponentially Stable ◽  
Aerial Vehicle ◽  
Error Dynamics

This paper proposes a dynamic image-based visual servoing (IBVS) control law for a quadrotor unmanned aerial vehicle (UAV) equipped with a single fixed on-board camera facing downward. The motion control problem is to regulate the relative lateral position of the vehicle to a stationary target located on the ground. The control law is termed dynamic as it is based on the dynamics and kinematics of the vehicle. The proposed design uses a nonlinear input-dependent change of state coordinates and its error dynamics are proven to be locally exponentially stable with an estimate provided for the region of attraction. Experimental and simulation results demonstrate the method's ease of on-board implementation, performance, and robustness. The simulation and experimental results include a comparison with an established dynamic IBVS method. This comparison shows the proposed method can provide similar performance with the benefit of reduced complexity.

Guidance Law Design with Fixed-Time Convergent Error Dynamics

2021 ◽  
pp. 1-10
Author(s):  
Chunyan Wang ◽  
Wei Dong ◽  
Jianan Wang ◽  
Jiayuan Shan ◽  
Ming Xin
Keyword(s):  
Fixed Time ◽  
Guidance Law ◽  
Error Dynamics

Co-operative 3D salvo attack of multiple missiles under switching topologies subject to time-varying communication delays

2019 ◽  
Vol 123 (1262) ◽  
pp. 464-483
Author(s):  
X.L. Ai ◽  
L.L. Wang ◽  
Y.C. Shen
Keyword(s):  
Initial Conditions ◽  
Sufficient Conditions ◽  
Time Varying ◽  
Communication Delays ◽  
Proportional Navigation ◽  
Stationary Target ◽  
Switching Topologies ◽  
Guidance Law ◽  
Multiple Missiles ◽  
Proportional Navigation Guidance

ABSTRACTThis study focuses on the co-operative salvo attack problem of multiple missiles against a stationary target under jointly connected switching topologies subject to time-varying communication delays. By carefully exploring certain features of the typical pure proportional navigation guidance law, a two-stage distributed guidance scheme is proposed without any information on time-to-go in this study to realise the simultaneous attack of multiple missiles. In the first guidance stage, a co-operative guidance law is proposed using local neighbouring communications only to achieve consensus on range-to-go and heading error to provide favourable initial conditions for the latter phase, in which switching topologies and time-varying communication delays are taken into account when obtaining sufficient conditions of consensus in terms of linear matrix inequalities. Then, missiles disconnect from each other and are guided individually by the typical pure proportional navigation guidance law with the same navigation gain to realise salvo attack in the second guidance phase. Finally, numerical simulations are carried out to clearly validate the theoretical results.

Guidance law to control impact time constraining the seeker’s field of view?

2018 ◽  
Vol 91 (1) ◽  
pp. 20-29 ◽  
Author(s):  
Jian Hu ◽  
Naigang Cui ◽  
Yuliang Bai ◽  
Yunhai Geng
Keyword(s):  
Stability Theory ◽  
Lyapunov Stability Theory ◽  
Field Of View ◽  
Convergence Time ◽  
Stationary Target ◽  
Content Type ◽  
Impact Time ◽  
Finite Time Stability ◽  
Guidance Law ◽  
The Impact

Purpose The purpose of this paper is to present a novel guidance law that is able to control the impact time while the seeker’s field of view (FOV) is constrained. Design/methodology/approach The new guidance law is derived from the framework of Lyapunov stability theory to ensure interception at the desired impact time. A time-varying guidance gain scheme is proposed based on the analysis of the convergence time of impact time error, where finite-time stability theory is used. The circular trajectory assumption is adopted for the derivation of accurate analytical estimation of time-to-go. The seeker’s FOV constraint, along with missile acceleration constraint, is considered during guidance law design, and a switching strategy to satisfy it is designed. Findings The proposed guidance law can drive missile to intercept stationary target at the desired impact time, as well as satisfies seeker’s FOV and missile acceleration constraints during engagement. Simulation results show that the proposed guidance law could provide robustness against different engagement scenarios and autopilot lag. Practical implications The presented guidance law lays a foundation for using cooperative strategies, such as simultaneous attack. Originality/value This paper presents further study on the impact time control problem considering the seeker’s FOV constraint, which conforms better to reality.

Cooperative Salvo Attack Using Guidance Law of Multiple Missiles

2015 ◽  
Vol 19 (2) ◽  
pp. 301-306 ◽  
Author(s):  
Jie Zeng ◽  
◽  
Lihua Dou ◽  
Bin Xin
Keyword(s):  
Mean Value ◽  
Stationary Target ◽  
Impact Time ◽  
State Variable ◽  
Guidance Law ◽  
Multiple Missiles ◽  
The Common ◽  
The Mean ◽  
Guidance Problem ◽  
Common Target

In this article, a guidance problem for cooperative salvo attack of multiple missiles against a single stationary target is investigated. The proposed guidance law combines the well-known PNG law and cooperative acceleration command, which is based on the feedback of state error between the current missile and the mean value of participant missiles. The state variable in this paper is used as the approximate calculation of time-to-go. The cooperative acceleration command is designed to adjust the flight path and impact time, which leads the multi-missiles to hit the common target simultaneously. During the engagement, the velocities of missiles are not changed and presetting impact time is not needed. Simulation results show the effectiveness of the proposed guidance law.

scholarly journals A Multiple Power Reachable Sliding Mode Control Approach for Guidance of Miniature Laser Beam Riding Steered Munition

2021 ◽  
Vol 2021 ◽  
pp. 1-11
Author(s):  
Jun-Fang Fan ◽  
Shi-Wei Chen
Keyword(s):  
Laser Beam ◽  
Sliding Mode ◽  
Incidence Angle ◽  
Stationary Target ◽  
Control Approach ◽  
Guidance Law ◽  
Straight Line ◽  
Trajectory Approach ◽  
Multiple Power ◽  
Arctangent Function

For a two-stage launch miniature shoulder munition steered with a laser beam riding system, the laser beam points to the target with a limited field radius and approximate straight-line spatial path; thus, the munition could not fly into the laser information field after the powered flight. The miniature munition dynamics are established firstly; then, an adaptive multiple power reachable sliding mode controller is presented and adopted to constrain both the trajectory inclination and pitch angle, which makes the munition enter the field and fly under control in the field with desired attitude angles, respectively. Considering the constraints of the incidence angle and the radius of the laser information field, an arctangent function curve is selected as the expected trajectory, and an adaptive multiple power reachable integral sliding mode guidance law is detailed, which makes the munition trajectory approach and converges to the expected curve fastly with limited acceleration. Therefore, the miniature munition flight trajectory is planned and optimized. Convergence and stability are analyzed based on the Lyapunov method. The numerical simulation against the stationary target is performed to fully demonstrate the efficacy of the proposed method.

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