Error Dynamics-Based Guidance Law of UAVs for Target Observation under Wind Disturbance

2012 ◽  
Author(s):  
Mingu Kim ◽  
Youdan Kim
Keyword(s):  
Wind Disturbance ◽  
Guidance Law ◽  
Error Dynamics

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

scholarly journals Hierarchical Robust Adaptive Control for Wind Turbines with Actuator Fault

2022 ◽  
pp. 1-8
Author(s):  
Sina Ameli ◽  
Olugbenga Anubi
Keyword(s):  
Wind Turbines ◽  
Tracking Error ◽  
Robust Adaptive Control ◽  
Control Input ◽  
Wind Disturbance ◽  
Rotor Speed ◽  
Low Level ◽  
Robust Adaptive ◽  
Error Dynamics ◽  
High Level

Abstract This paper solves the problem of regulating the rotor speed tracking error for wind turbines in the full-load region by an effective robust-adaptive control strategy. The developed controller compensates for the uncertainty in the control input effectiveness caused by a pitch actuator fault, unmeasurable wind disturbance, and nonlinearity in the model. Wind turbines have multi-layer structures such that the high-level structure is nonlinearly coupled through an aggregation of the low-level control authorities. Hence, the control design is divided into two stages. First, an ℒ2 controller is designed to attenuate the influence of wind disturbance fluctuations on the rotor speed. Then, in the low-level layer, a controller is designed using a proposed adaptation mechanism to compensate for actuator faults. The theoretical results show that the closed-loop equilibrium point of the regulated rotor speed tracking error dynamics in the high level is finite-gain ℒ2 stable, and the closed-loop error dynamics in the low level is globally asymptotically stable. Simulation results show that the developed controller significantly reduces the root-mean- square of the rotor speed error compared to some well-known works, despite the largely fluctuating wind disturbance, and the time-varying uncertainty in the control input effectiveness.

Study of Proportional Navigation Guidance of Reentry Vehicle Considering Wind Disturbance

2014 ◽  
Vol 490-491 ◽  
pp. 368-374
Author(s):  
Li Jia Zhang ◽  
Yi Xin Huang ◽  
Yu Zhang ◽  
Zhao Ying Li
Keyword(s):  
Wind Disturbance ◽  
Proportional Navigation ◽  
Reentry Vehicle ◽  
Guidance Law ◽  
Terminal Constraints ◽  
Velocity Deviation ◽  
The Impact ◽  
Large Wind ◽  
Terminal Guidance ◽  
Proportional Navigation Guidance

Proportional navigation guidance law is widely applied in the terminal guidance of the reentry vehicle. However, the guidance accuracy of the traditional PNG law is largely affected by the wind disturbance. To improve the impact precision, the proposed method applies a feedback of angular velocity deviation to the traditional PNG law. With the proposed method, the vehicle could satisfy the terminal constraints under large wind disturbance. Also, simulation results validate that the proposed method can well enhance the performance of the vehicle.

Guidance law to control impact angle and time based on optimality of error dynamics

2018 ◽  
Vol 233 (10) ◽  
pp. 3577-3588 ◽  
Author(s):  
Bin Li ◽  
Defu Lin ◽  
Jiang Wang ◽  
Song Tian
Keyword(s):  
Impact Angle ◽  
Error Feedback ◽  
Time Error ◽  
Optimal Error ◽  
Impact Time ◽  
Guidance Law ◽  
The Difference ◽  
Error Dynamics ◽  
Miss Distance ◽  
Impact Angle Constraint

In this work, a new guidance law with a meaningful performance index is designed to satisfy terminal impact angle and impact time constraints based on optimal error dynamics, which can be used for salvo attacks or cooperative missions of multi-missile. The analytical solution of the proposed guidance law is a combination of trajectory shaping guidance law and an additional impact time error feedback term that is proportional to the difference between the desired and the true impact times. Trajectory shaping guidance law aims to achieve the desired terminal impact angle and zero miss distance, whereas the extra term aims to meet the desired impact time. The minimum and maximum feasible impact times that consider the seeker's field-of-view limit, terminal impact angle constraint, and missile's maneuvering acceleration limit are calculated to provide the feasible boundary range of the desired impact time. Numerical simulations of several engagement situations demonstrate the effectiveness of the proposed guidance law in the accuracy of terminal impact angle and impact time.

Optimal Control of an Unmanned Lighter-Than-Air Vehicle Through Way-Point Navigation

2012 ◽  
Author(s):  
Ghassan M. Atmeh ◽  
Kamesh Subbarao
Keyword(s):  
Optimal Control ◽  
Kalman Filter ◽  
Wind Disturbance ◽  
Linear Quadratic ◽  
Proportional Navigation ◽  
Guidance Law ◽  
Air Vehicle ◽  
Optimal Linear ◽  
Guidance Laws ◽  
Proportional Navigation Guidance

The work presented in this paper deals with designing two, optimal, Linear-Quadratic controllers that are capable of navigating an airship through a series of planar waypoints. Two guidance laws are considered, a track-specific guidance law and a proportional navigation guidance law. Each provides commands to their corresponding controller based on vehicle and waypoint positions. A novel implementation of the extended Kalman filter (EKF) provides the required states and wind speed estimates to enhance the performance of the track-specific guidance law in the presence of wind disturbance.

Anti-Sway Crane Control Considering Wind Disturbance and Container Mass

2013 ◽  
Vol 133 (3) ◽  
pp. 262-271
Author(s):  
Kentaro Sato ◽  
Kiyoshi Ohishi ◽  
Toshimasa Miyazaki
Keyword(s):  
Wind Disturbance ◽  
Crane Control
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