Development of Fault-Tolerant Flight Control Laws for the WVU YF-22 Model Aircraft

2007 ◽  
Author(s):  
Mario Perhinschi ◽  
Marcello Napolitano ◽  
Giampiero Campa ◽  
Brad Seanor ◽  
Srikanth Gururajan ◽  
...  
Keyword(s):  
Flight Control ◽  
Fault Tolerant ◽  
Control Laws ◽  
Model Aircraft

scholarly journals CONTROLLERS FOR FAULT TOLERANT ACTUATORS

Aviation ◽  
2007 ◽  
Vol 11 (1) ◽  
pp. 23-27 ◽  
Author(s):  
Bogusław Dołega ◽  
Paweł Rzucidło
Keyword(s):  
Flight Control ◽  
Fault Tolerant ◽  
Control Algorithms ◽  
Equipment Failure ◽  
Aircraft Control ◽  
Level Control ◽  
Control Laws ◽  
Handling Qualities ◽  
Effective Dynamics ◽  
High Level

The Fly‐by‐Wire technology enables flexible shaping of both effective dynamics and handling qualities of aircraft. This solution extends aircraft possibilities and supports the pilot by use of high‐level control laws. Application of FBW for aircraft would make flying both safer, and more popular. On the other hand the FBW system must be highly reliable. Advanced indirect flight control technology requires the use of actuators characterized by fault tolerant architecture. It should enable improvement of reliability of the aircraft control system and safety of performed flights effectively. The Electromechanical Actuator (EMA) consists of the electric motor, gearbox and controller. The actuator controller should be made intrinsically reliable and should be insensitive to other equipment failure. The conception of fault tolerant control algorithms as well as practical realization of it has been presented in this work. Tests of reliability of the complete EMA unit have also been presented herein.

Design and Flight Testing of Intelligent Flight Control Laws for the WVU YF-22 Model Aircraft

2005 ◽  
Author(s):  
Mario Perhinschi ◽  
Marcello Napolitano ◽  
Giampiero Campa ◽  
Brad Seanor ◽  
Srikanth Gururajan ◽  
...  
Keyword(s):  
Flight Control ◽  
Flight Testing ◽  
Control Laws ◽  
Model Aircraft

scholarly journals Design of Highly Redundant Fault Tolerant Control for Aircraft Elevator System

2020 ◽  
pp. 1-11
Author(s):  
Muhammad Tayyeb ◽  
Umar Riaz ◽  
Arslan Ahmed Amin ◽  
Omer Saleem ◽  
Muhammad Arslan ◽  
...  
Keyword(s):  
Flight Control ◽  
Fault Tolerant ◽  
Fault Tolerant Control ◽  
Environmental Safety ◽  
Aircraft Control ◽  
Sensors And Actuators ◽  
Control Laws ◽  
Modular Redundancy ◽  
Redundant Fault ◽  
Aircraft Crash

Elevators are surfaces of flight control, typically at the rear of an aircraft to control the pitch of the plane, the angle of attack and the wing lift. The most critical actuation device is longitudinal aircraft control, and its failures will result in a catastrophic aircraft crash. This paper proposes a Highly Redundant Fault Tolerant Control (HRFTC) policy for the aircraft to accommodate faults in the critical sensors and actuators. Modified Triple Modular Redundancy (MTMR) has been proposed for the sensors and Dual Redundancy (DR) has been proposed for the actuators.  The working of control laws, pilot order, signal conditioning, and failure are elaborated. Furthermore, the PID controller is used for the adjustment of the position of the elevator by comparing it with a set point. The results show that when a fault occurs, the system detects it successfully and tolerates it quickly without disturbing the flight of aircraft. The study is significant for the avionics industry for manufacturing highly reliable machines for human and environmental safety.

scholarly journals A Detail of Fault Tolerant Flight Control Techniques

2020 ◽  
Vol 9 (1) ◽  
pp. 617-625
Keyword(s):  
Fault Diagnosis ◽  
Flight Control ◽  
High Performance ◽  
Review Paper ◽  
Fault Tolerant ◽  
Fault Current ◽  
Control Laws ◽  
Control Techniques ◽  
Detection And Diagnosis

Fault tolerant flight control (FTFC) system deals with the detection and diagnosis of faults and looks at the task of regaining control in the presence of the fault. Current modern aircraft are made highly complex for comfort or high performance. The study of improvement in safety, redundancy, and adapting the flight control laws after its occurrence of faults has fascinated the thoughtfulness of several investigators in the previous two decades. Overall illustration of different fault diagnosis and fault-tolerant flight control approaches involved are provided in this review paper.

Design of Intelligent Flight Control Laws for the WVU YF-22 Model Aircraft

2004 ◽  
Author(s):  
Mario Perhinschi ◽  
Marcello Napolitano ◽  
Giampiero Campa ◽  
Brad Seanor ◽  
Srikanth Gururajan
Keyword(s):  
Flight Control ◽  
Control Laws ◽  
Model Aircraft

Simplified GPS model for UAV fault tolerant control laws design

2015 ◽  
Vol 3 (1) ◽  
pp. 39-60 ◽  
Author(s):  
Ghassan Al-Sinbol ◽  
Mario G Perhinschi ◽  
Brenton K Wilburn
Keyword(s):  
Flight Control ◽  
Fault Tolerant ◽  
Research Effort ◽  
Fault Tolerant Control ◽  
West Virginia University ◽  
Control Laws ◽  
Content Type ◽  
Autonomous Flight ◽  
Operational Conditions ◽  
Simulation Tools

Purpose – A simplified global positioning system (GPS) error model including models for a variety of abnormal operational conditions and failures is developed to provide simulation tools for the design, testing, and evaluation of autonomous flight fault tolerant control laws. The paper aims to discuss these issues. Design/methodology/approach – Analysis and experimental data are used to build simplified models for GPS position and velocity errors on all three channels. The GPS model is interfaced with West Virginia University unmanned aerial vehicles (UAV) simulation environment and its utility demonstrated through simulation for several autonomous flight scenarios including GPS abnormal operation. Findings – The proposed simplified GPS model achieves desirable levels of accuracy and realism for all components for the purpose of general UAV dynamic simulation and development of fault tolerant autonomous flight control laws. Research limitations/implications – The simplified GPS model allows investigating GPS malfunction effects on the performance of autonomous UAVs and designing trajectory tracking algorithms with advanced fault tolerant capabilities. Practical implications – The simplified GPS model has proved to be a flexible and useful tool for UAV simulation and design of autonomous flight control laws at normal and abnormal conditions. Originality/value – The outcomes of this research effort achieve a level of detail never attempted before in modeling GPS operation at normal and abnormal conditions for UAV simulation and autonomous flight control laws design using a simplified framework.

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