Adaptive Control for Steering Engine Fault of Ducted Fan UAV

For the steering engine fault of ducted fan UAV that may arise during the hovering, designing adaptive controller for attitude control. First, concentrating on modeling of the hovering state of ducted fan UAV, and getting the relationship between steering engine and attitude control. Then analyzing the impact of steering engine fault on the attitude control system basing on the control model. Finally, designing model reference adaptive controller basing on the fault model, so that the ducted fan UAV can maintain good attitude control if steering engine fault occurs during the hovering. Simulation results show that when steering engine fault occurs, the model reference adaptive controller can effectively inhibit the adverse effects brought by steering engine fault, so the attitude control system has strong adaptability and robustness.

Download Full-text

Adaptive augmentation of the attitude control system for a multirotor unmanned aerial vehicle

Proceedings of the Institution of Mechanical Engineers Part G Journal of Aerospace Engineering ◽

10.1177/0954410018820193 ◽

2018 ◽

Vol 234 (10) ◽

pp. 1587-1596

Author(s):

G Bressan ◽

A Russo ◽

D Invernizzi ◽

M Giurato ◽

S Panza ◽

...

Keyword(s):

Control System ◽

Unmanned Aerial Vehicle ◽

Attitude Control ◽

Adaptive Controller ◽

Attitude Control System ◽

Loop Dynamics ◽

The Standard Model ◽

Aerial Vehicle ◽

Adaptation Law ◽

Model Reference Adaptive

In this paper, the adaptive augmentation of the attitude control system for a multirotor unmanned aerial vehicle is considered. The proposed approach allows to combine a baseline controller with an adaptive one and to disable or enable the adaptive controller when needed, in order to take the advantages of both the controllers. To improve transient performance with respect to the standard model reference adaptive controller, an observed-based approach is exploited. The adaptation law is based on the error between the output of an observer of the nominal closed-loop dynamics and the actual output of the system with uncertainties. Experimental results obtained by testing the proposed approach on a quadrotor unmanned aerial vehicle are presented to compare the performance, in terms of disturbance rejection, with respect to the baseline controller and to a [Formula: see text] adaptive augmentation scheme.

Download Full-text

Model reference adaptive attitude control for near space hypersonic vehicle with mismatched uncertainties

Transactions of the Institute of Measurement and Control ◽

10.1177/0142331218776713 ◽

2018 ◽

Vol 41 (5) ◽

pp. 1301-1312

Author(s):

Jianguo Guo ◽

Tianbao Zhang ◽

Cheng Cheng ◽

Jun Zhou

Keyword(s):

Control System ◽

Attitude Control ◽

Angular Rate ◽

Hypersonic Vehicle ◽

Control Loop ◽

Attitude Control System ◽

Model Reference ◽

Near Space ◽

Mismatched Uncertainties ◽

Model Reference Adaptive

In this paper, a new model reference adaptive attitude control based on backstepping approach is presented for near space hypersonic vehicle with mismatched uncertainties. Firstly, the attitude dynamic model of near space hypersonic vehicle is divided into two control loops, which is composed of an attitude angle control loop and an attitude angular rate control loop. Secondly, a novel model reference adaptive attitude control approach is proposed by introducing reference model to avoid the calculating expansion problem in backstepping technique. Meanwhile, the reference models for every loop are independently designed to improve the tracking performance. The stability of attitude control system is strictly proven by using Lyapunov stability theory. Finally, the simulation results demonstrate that the attitude control system by applying the proposed method has good stability, dynamic property and strong robustness in the presence of input constraints and parameters perturbation.

Download Full-text

A study of the quadratic performance index for a VTOL prefilter model reference attitude control system

10.2514/6.1969-884 ◽

1969 ◽

Cited By ~ 2

Author(s):

L. CORLISS ◽

T. GOSSETT

Keyword(s):

Control System ◽

Performance Index ◽

Attitude Control ◽

Attitude Control System ◽

Model Reference ◽

Quadratic Performance Index ◽

Quadratic Performance

Download Full-text

Design of a Control System for an Organic Flight Array Based on a Neural Network Controller

International Journal of Aerospace Engineering ◽

10.1155/2018/1250908 ◽

2018 ◽

Vol 2018 ◽

pp. 1-11 ◽

Cited By ~ 4

Author(s):

Bokyoung Oh ◽

Junho Jeong ◽

Jinyoung Suk ◽

Seungkeun Kim

Keyword(s):

Neural Network ◽

Control System ◽

Flight Control ◽

Attitude Control ◽

Adaptive Controller ◽

Model Inversion ◽

Operational Conditions ◽

Ducted Fan ◽

Neural Network Controller ◽

The Neural Network

This paper presents a flight control system for an organic flight array (OFA) with a new configuration consisting of multimodularized ducted-fan unmanned aerial vehicles. The OFA has a distinguished advantage of assembling or separating with respect to its missions or operational conditions because of its reconfigurable structure. Therefore, designing a controller that can be flexibly applied in each situation is necessary. First, a dynamic modeling of the OFA based on a single ducted-fan vehicle is performed. Second, the inner loop for attitude control is designed through dynamic model inversion and a PD controller. However, an adaptive control component is needed to flexibly cope with the uncertainty because the operating environment of the OFA is varied, and uncertainty exists depending on the number of modules to be assembled and disturbances. In addition, the performance of the neural network adaptive controller is verified through a numerical simulation according to two scenarios.

Download Full-text

High Accuracy Attitude Control System Design for Satellite with Flexible Appendages

Mathematical Problems in Engineering ◽

10.1155/2014/695758 ◽

2014 ◽

Vol 2014 ◽

pp. 1-6 ◽

Cited By ~ 1

Author(s):

Wenya Zhou ◽

Haixu Wang ◽

Zhengwei Ruan ◽

Zhigang Wu ◽

Enmei Wang

Keyword(s):

Control System ◽

Attitude Control ◽

Design Method ◽

Notch Filter ◽

Vibration Signal ◽

High Accuracy ◽

Frequency Variation ◽

Attitude Control System ◽

The Impact ◽

Flexible Appendages

In order to realize the high accuracy attitude control of satellite with flexible appendages, attitude control system consisting of the controller and structural filter was designed. When the low order vibration frequency of flexible appendages is approximating the bandwidth of attitude control system, the vibration signal will enter the control system through measurement device to bring impact on the accuracy or even the stability. In order to reduce the impact of vibration of appendages on the attitude control system, the structural filter is designed in terms of rejecting the vibration of flexible appendages. Considering the potential problem of in-orbit frequency variation of the flexible appendages, the design method for the adaptive notch filter is proposed based on the in-orbit identification technology. Finally, the simulation results are given to demonstrate the feasibility and effectiveness of the proposed design techniques.

Download Full-text

INNOSAT ATTITUDE CONTROL SYSTEM BASED ON ADAPTIVE NEURO-CONTROLLER

Journal of Information and Communication Technology ◽

10.32890/jict.10.2011.8108 ◽

2011 ◽

Author(s):

Siti Maryam Sharun ◽

Mohd Yusoff Mashor ◽

Norhayati Mohd Nazid ◽

Sazali Yaacob ◽

Wan Nurhadani Wan Jaafar

Keyword(s):

Control System ◽

Attitude Control ◽

Reference Model ◽

Operating Conditions ◽

Least Square ◽

Recursive Least Square ◽

Attitude Control System ◽

Model Reference ◽

Mlp Network ◽

Neuro Controller

The current research focuses on the designing of an intelligent controller for the Attitude Control System (ACS) of the Innovative Satellite (InnoSAT). The InnoSAT mission is to demonstrate local innovative space technology amongst the institutions of higher learning in the space sector. In this study, an Adaptive Neuro-controller (ANC) based on the Hybrid Multi Layered Perceptron (HMLP) network has been developed. The Model Reference Adaptive Control (MRAC) system is used as a control scheme to control a time varying systems where the performance specifications are given in terms of a reference model. The Weighted Recursive Least Square (WRLS) algorithm will adjust the controller parameters to minimize error between the plant output and the model reference output. The objective of this paper is to analyse the time response and the tracking performance of the ANC based on the HMLP network and the ANC based on the standard MLP network for controlling an InnoSAT attitude. These controllers have been tested using an InnoSAT model with some variations in operating conditions such as varying gain, measurement noise and disturbance torques. The simulation results indicated that the the ANC based on the HMLP network is adequate to control satellite attitude and give better results than the ANC based on the MLP network.

Download Full-text