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
Investigation of fatigue behaviour of external stores under fixed wing aircraft platforms during random vibration
Download
index.pdf
Date
2015
Author
Okur, Emre
Metadata
Show full item record
Item Usage Stats
328
views
103
downloads
Cite This
In this study, fatigue behaviour of an external store during captive carriage at the underwing and wingtip of a fixed wing aircraft platform is investigated. The F-16C jet aircraft was determined as a fixed wing aircraft platform in this thesis which is commonly used by Turkish Army. As the external store, a data measurement store (DMS) was designed to measure loads during captive carrage. While the DMS was being attached to the F-16C jet aircraft, it flew in 5 different sorties. Acceleration and strain data were collected during these sorties. Accelerometers were used to generate power specral densities (PSD) for the vibration tests and fatigue analyses. Strain gages were placed to the most critical locations for fatigue calculations. For fatigue calculations, annual flight of F-16C jet aircraft was taken into consideration. From this annual flight data, an ideal average sortie for F-16C jet aircraft (IASF-16JA) was generated. Acceleration and strain data collected from 5 different sorties were separated and picked according to this ideal average F-16C jet aircraft sortie. For data processing and analyses Matlab, MS Excel, Ncode, MSC – Patran ve MSC – Nastran were used. Strain data were used for fatigue calculations and acceleration vi data were used to generate captive carriage vibration profiles. Also, using these vibration profiles a sample fatigue analysis was done. Moreover, reduction and determination of the vibration test duration was explanied.
Subject Keywords
Materials
,
Metals
,
Airplanes
,
Vibration (Aeronautics).
URI
http://etd.lib.metu.edu.tr/upload/12619337/index.pdf
https://hdl.handle.net/11511/24900
Collections
Graduate School of Natural and Applied Sciences, Thesis
Suggestions
OpenMETU
Core
Fatigue and fracture analysis of helicopter fuselage structures
Özcan, Rıza; Dağ, Serkan; Department of Mechanical Engineering (2013)
In this study a methodology is developed for the fatigue and fracture analysis of helicopter fuselage structures, which are considered as the stiffened panels. The damage tolerance behavior of the stiffened panels multiaxially loaded is investigated by implementing virtual crack closure technique (VCCT). Validation of VCCT is done through comparison between numerical analysis and the studies from literature, which consists of stiffened panels uniaxially loaded and the panel with an inclined crack. A program...
Design of an LPV Based Fractional Controller for the Vibration Suppression of a Smart Beam
Onat, Cem; Şahin, Melin; Yaman, Yavuz; Eswar, Prasad; Saılu, Nemana (2011-12-01)
One of the major problems encountered in the active vibration control of aircraft wings is the changing mass due to the in-flight fuel consumption. In this study, a Linear Parameter Varying (LPV) based fractional controller is designed for the suppression of the flexural vibrations of a smart beam. The designed controller is sensitive to the varying mass properties. The smart beam studied was a cantilever aluminium beam with eight surface bonded Lead-Zirconate-Titanate (PZT) patches. The smart beam was exci...
Investigation of rotor rotor interactions for two helicopters in forward flight using free vortex wake methodology
Tonkal, Ozan Çağrı; Pehlivan, Sercan; Sezer Uzol, Nilay; İşler, Veysi (null; 2010-07-01)
This paper presents an investigation of the aerodynamic interactions between two UH-1H helicopter rotors in forward flight. The wake flow structure and performance characteristics of the rotors are investigated when the rear rotor is operating within the wake of the front rotor. A 3-D unsteady vortex-panel method potential flow solver based on a free-vortex-wake methodology is used for this purpose. The solver is validated using the experimental data from the Caradonna-Tung experiments. The interactional an...
EXPERIMENTAL INVESTIGATION OF FLIGHT AND PHYSICAL PARAMETERS AFFECTING THE VIBRATION RESPONSE SEVERITY OF SUBSYSTEM CARRIED BY JET AIRCRAFT
Kaplan, Engin Metin; Özer, Mehmet Bülent (null; 2017-09-22)
In this study, Experimental Modal Analysis (EMA) of a subsystem carried by a jet aircraft which is in real flight condition is performed. The main purpose of this study is to investigate relationship between vibration response of the subsystem and flight parameters like mach number, attitude, propulsion severity and number of the jet engine of the jet type aircraft, also physical parameters as mass, mass moment of inertia in three axes of the subsystem. Parameters are collected in real flight condition by d...
Development of a method for maximum structural response prediction of a store externally carried by a jet fighter
Kaplan, Engin Metin; Acar, Erdem; Özer, Mehmet Bülent (2021-01-01)
Experimental structural response of equipment mounted in store carried externally by jet type aircraft is investigated, predicted and compared with responses suggested by military standards in this study. A representative store which is similar to Mark-83 warhead with guidance units in terms of mass and geometry is used in this study. The main scope of this study is to evaluate the structural response proposed by military standards with real test conditions and also suggest a new method with an artificial n...
Citation Formats
IEEE
ACM
APA
CHICAGO
MLA
BibTeX
E. Okur, “Investigation of fatigue behaviour of external stores under fixed wing aircraft platforms during random vibration,” M.S. - Master of Science, Middle East Technical University, 2015.