Show/Hide Menu
Hide/Show Apps
Logout
Türkçe
Türkçe
Search
Search
Login
Login
OpenMETU
OpenMETU
About
About
Open Science Policy
Open Science Policy
Open Access Guideline
Open Access Guideline
Postgraduate Thesis Guideline
Postgraduate Thesis Guideline
Communities & Collections
Communities & Collections
Help
Help
Frequently Asked Questions
Frequently Asked Questions
Guides
Guides
Thesis submission
Thesis submission
MS without thesis term project submission
MS without thesis term project submission
Publication submission with DOI
Publication submission with DOI
Publication submission
Publication submission
Supporting Information
Supporting Information
General Information
General Information
Copyright, Embargo and License
Copyright, Embargo and License
Contact us
Contact us
A Model based approach for aircraft sensor fault detection
Download
index.pdf
Date
2018
Author
Serçekman, Ömür
Metadata
Show full item record
Item Usage Stats
308
views
151
downloads
Cite This
This thesis presents a reformative approach to a model-based fault detection and diagnosis (FDD) method that improves the capability of aircraft flight control systems and acquires low complexity and computational requirements. The main objective of the FDD techniques that are extensively applied in industrial systems is to increase the sensitivity of fault detection scheme with respect to additional noise, uncertainty or disturbances. The designed fault detection model is integrated to a civil aircraft model of Boeing 747. The developed system mainly consists of a nonlinear closed-loop aircraft model to verify the effectiveness of sensor fault detection technique, an observer to estimate states of the aircraft during steady state flight, a fault indicator to propagate faulty responses to the system and a reconfigurator to identify flight condition if it is faulty or fault-free by comparing the states which are achieved from sensors in real-time. Fault detection is accomplished by using mainly a Kalman filter as a linear observer design. The scheme presented based on Kalman filter decreases the effect of model uncertainty extensions, constitutes a residual sensitive to stuck faults and maintains a reliable fault detection approach incorporating the rejection of false alarm that is required for system reliability. The monitoring progression of the state estimation permits to observe any off-nominal system attitude and detects faults. The developed method is a viable solution for earlier detection of sensor stuck to lower threshold amplitude under multi- simulation tests performed in MATLAB Simulink.
Subject Keywords
Flight control.
,
Airplanes
,
Guidance systems (Flight).
URI
http://etd.lib.metu.edu.tr/upload/12622795/index.pdf
https://hdl.handle.net/11511/27682
Collections
Graduate School of Natural and Applied Sciences, Thesis
Suggestions
OpenMETU
Core
A Model Based Approach for Sensor Fault Detection in Civil Aircraft Control Surface
Sercekman, O.; Kutay, Ali Türker (2018-04-26)
A model-based fault detection and diagnosis (FDD) solution improves the capability in a civil aircraft control surface whereas having low complexity and computational requirements. The main objective of the FDD. techniques that are extensively applied in industrial systems is to increase the sensitivity of fault detection scheme while maintaining a reliable system response with respect to additional unknown inputs. In the paper, a reformative approach to an observer-based fault detection method is introduce...
Determining a strategy for favorable acquisition and utilization of complex technologies: flight simulation training devices (FSTD)
Boztaş, Ömer; Erdil, Erkan; Özgen, Serkan; Department of Science and Technology Policy Studies (2012)
The thesis investigates the elements of a consistent strategy for favorable acquisition and utilization of Flight Simulation Training Devices (FSTD), thus Full Flight Simulators (FFS) and Flight Training Devices (FTD). The primary purpose is to determine a knowledge-based strategy for the end-user, acquisition professional, aviation firms and institutions. Hence, it could be possible to shed a light for cooperative groups and main institutions of national innovation system involved in entrepreneurial and in...
A model - based jamming detection method for electro-hydrostatic actuators
Poyraz, Emre Murat; Turgut, Ali Emre; Çalışkan, Hakan (2020-09-01)
An anomaly or a fault, which may be treated as insignificant in a complicated engineering system, like an electro–hydraulic flight control actuator, can cause considerable performance degradation and deteriorating effects or even worse it may end up with a catastrophic system failure. One of the problems commonly observed in air vehicles is called jamming. Jamming is the type of failure where an actuator connected to a flight control surface permanently gets stuck at a certain position and does not move any...
Aircraft motion dynamics and lateral trajectory tracking algorithm design for the enhancement of flight safety
Günhan, Cahide Yeliz; Demirbaş, Kerim; Department of Electrical and Electronics Engineering (2018)
This thesis aspires to cover the fundamentals of an aircraft control for Flight Management System (FMS). FMS, trajectory tracking and performance requirements of a flight are the focal points of the thesis. In view of this, the thesis consists of the outlined components to achieve its goal; (i) generating paths - which denotes the creation of reference paths for trajectory by complying with the avionic performance standardizations, (ii) controlling the aircraft – which propagates the control commands by usi...
A Control System Architecture for Control of Non-Affine in Control, Open-Loop Unstable Underactuated Systems
Marangoz, Alp; Kutay, Ali Türker (2017-07-25)
In this paper, a control system architecture for control of non-affine in control, open-loop unstable underactuated system is discussed. Passivization of the unactuated (internal) system dynamics achieved through perturbation of trajectories of the actuated states, which are calculated through adaptive dynamic inversion technique, based on Tikhonov's theorem. Performance of the controller is shown through simulation of two open-loop unstable and locally uncontrollable example problems.
Citation Formats
IEEE
ACM
APA
CHICAGO
MLA
BibTeX
Ö. Serçekman, “A Model based approach for aircraft sensor fault detection,” M.S. - Master of Science, Middle East Technical University, 2018.