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
Analysis of Aircraft Survivability Against Fragmenting Warhead Threat
Date
2014-01-17
Author
Konokman, Hüseyin Emrah
Kayran, Altan
KAYA, MUSTAFA
Metadata
Show full item record
This work is licensed under a
Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License
.
Item Usage Stats
251
views
0
downloads
Cite This
The article presents the methodology of the aircraft survivability analysis considering vulnerability of the aircraft against fragmenting warhead threat. The initial step of the survivability analysis against a fragmenting warhead threat is to position the target and the warhead in proper coordinate systems for the calculation of warhead-target engagement. Once the warhead detonates at a miss distance from the target, the motions of the fragments are calculated considering the drag and the gravity forces and the initial velocity of the fragments. For the hit calculations, the shotline method is employed, and hit locations, thickness and material information are obtained. For the shotline analysis, the functions and required libraries of the BRL-CAD software are integrated in the code which is used as the shotline subroutine of the main survivability analysis code developed in Fortran 90. Fragment penetration calculations are performed based on THOR equations, and vulnerability assessment of the aircraft against fragmenting warhead threats is carried out in terms of cumulative probability of kill of the aircraft considering all redundant and non-redundant critical components. Cumulative probability of kill calculations are performed according to the fault tree which is established for the particular aircraft being studied. Kill criteria for fuel tank fuel fire is presented. Survivability analysis of an aircraft against fragmentation warhead threat is performed by means of the developed code.
URI
https://hdl.handle.net/11511/69639
DOI
https://doi.org/10.2514/6.2014-0355
Collections
Department of Aerospace Engineering, Conference / Seminar
Suggestions
OpenMETU
Core
Determination of dynamically equivalent fe models of aircraft structures by using modal test data
Karaağaçlı, Taylan; Özgüven, Hasan Nevzat; Yıldız, Erdinç N.; Department of Mechanical Engineering (2010)
Reliable flutter analysis of aircraft structures is a major requirement to determine safe flight envelops. Dynamically equivalent finite element model of an aircraft structure correlating well with experimental modal is a major requirement for a reliable flutter analysis. Currently available model updating techniques require enormous time and engineering work to achieve appropriate finite element models of aircraft structures. The method developed within the scope of this thesis work aims to remove importan...
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...
Simulation of the Transient Response of a Helicopter Turboshaft Engine to Hot-Gas Ingestion
Uzol, Oğuz; Yavrucuk, İlkay (2008-06-09)
Hot-Gas Ingestion (HGI) to the engines can potentially occur when a rotorcraft or a VTOL/STOVL fixed-wing aircraft is operating in close proximity to the ground. Especially for helicopters, due to the rotor downwash hot exhaust gases get recirculated into the engine inlet. Similar conditions may also occur due to the ingestion of hot exhaust gases from rocket launchers or gun fire. In this study, we present the results of a simulation of the transient response of a helicopter turboshaft engine to HGI. Speci...
Design and evaluation of a helicopter main rotor electrohydraulic control system
Düzağaç, Hasan Ali; Çalışkan, Hakan; Balkan, Raif Tuna; Department of Mechanical Engineering (2022-8-26)
Helicopters are widely used aircrafts for several purposes. Main Rotor of a Helicopter creates necessary flight forces for performing flight operation. Orientation of a Helicopter Rotor System is determined and controlled manually by pilot and automatically by automatic control system via hydraulically operated flight control actuators. In this research, a novel electrohydraulically operated helicopter main rotor control system is mathematically designed and developed to improve overall performance of contr...
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...
Citation Formats
IEEE
ACM
APA
CHICAGO
MLA
BibTeX
H. E. Konokman, A. Kayran, and M. KAYA, “Analysis of Aircraft Survivability Against Fragmenting Warhead Threat,” 2014, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/69639.