GROUND VIBRATION TEST PLANNING OF A FIGHTER AIRCRAFT BY USING A ROUGH FINITE ELEMENT MODEL

Date

2013-11-21

Author

Koksal, Sertac
Yildiz, Erdinc Nuri
Yazıcıoğlu, Yiğit
Özgen, Gökhan Osman

Metadata

Show full item record

This work is licensed under a Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.

Item Usage Stats

51
views

0
downloads

Certification process is one of the crucial procedures for safety in the design of a new aerial platform. Flight flutter testing is the most critical component for the certification process. Usually a flutter analysis is performed beforehand for the planning of flight flutter testing of an aircraft which mostly requires the Finite Element Model (FEM) together with Ground Vibration Testing (GVT) to construct the structural dynamic model of the complete aircraft for the flutter analyses. GVT is not only required for new aircraft design but also when considerable changes are made to an existing aircraft or when new external load configurations are introduced. Experimental methods require high effort, high budget, long time, and much repetition. Therefore, the computational and theoretical studies seem more applicable in the early phase. However, GVT of an available fighter aircraft in defense projects becomes an issue for the designers if a detailed FEM of the aircraft is not available prior to test. Hence, planning of the GVT in early stage is vital for project leaders. In this study, a rough FEM of a fighter aircraft is developed and correlated to available GVT data for planning purpose. The representative mode shapes are evaluated by estimation of the several sections of the aircraft. It is also shown that a rough FEM of the aircraft can be utilized for determination of the measurement and excitation points on the aircraft in planning stage. The geometrical properties, physical limitations and basic requirements of GVT are also taken into account for an efficient planning.

URI

https://hdl.handle.net/11511/53235

Conference Name

ASME International Mechanical Engineering Congress and Exposition (IMECE2013)

Collections

Department of Mechanical Engineering, Conference / Seminar

Suggestions

OpenMETU
Core

Missile system design and optimization integrated with system engineering methodologies Karataban, Deniz.; Kutay, Ali Türker; Department of Aerospace Engineering (2019) In the missile system design process, customer’s requirements and system design are entirely interrelated. From the beginning of the design process, customer requirements should be taken into consideration carefully to avoid an inappropriate design. Moreover, in order to handle the changes in the requirements efficiently, both the requirement’s implementation into the design and design processes should be accelerated. Within the scope of this thesis, a design optimization tool that provides solutions to the...
Design and analysis of fixturing in assembly of sheet metal components of helicopters Bayar, Fatih Mehmet; Gökler, Mustafa İlhan; Department of Mechanical Engineering (2007) Assembling of the compliant parts used in aviation industry is a challenging process. Assembly fixtures are quite important tools in this effort and widely used in industry. In fixturing of easily deformable sheet metal parts, besides restraining the rigid body motion of the parts, the possible deformations that may occur during the assembly process and the spring-back effect on the final product need to be taken in to consideration. In order to guarantee a successful assembling, in other words, to obtain t...
Static and dynamic aeroelastic analysis of a very light Aircraft Demirer, Halime Gül; Kayran, Altan; Department of Aerospace Engineering (2021-9-10) Aircraft design processes need to ensure that the aircraft is aeroelastically stable within its operational envelope. This thesis presents an overview of the static aeroelastic, flutter and gust response analysis of a very light aircraft. MSC.FlightLoads and MSC.Nastran are used for aeroelastic modeling and analysis. The methods to be used in the aeroelastic analysis of the VLA are tested on the AGARD 445.6 wing, and the results are in good agreement with the literature. Aeroelastic model corrections such a...
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...
Static and Dynamic Aeroelastic Analysis of a Very Light Aircraft Demirer, Halime Gül; Kayran, Altan (2021-09-08) Aircraft design processes need to ensure that the aircraft will be aeroelastically stable within its operational envelope. This paper presents an overview of the static aeroelastic analysis results, flutter analysis and gust response analysis results of a very light aircraft. MSC.FlightLoads and MSC.Nastran are used for aeroelastic modeling and analysis. Aerodynamic calculations are based on the Doublet-Lattice Method (DLM), the aerodynamic theory employed by Nastran for subsonic flows. DLM requires all lif...

Citation Formats

S. Koksal, E. N. Yildiz, Y. Yazıcıoğlu, and G. O. Özgen, “GROUND VIBRATION TEST PLANNING OF A FIGHTER AIRCRAFT BY USING A ROUGH FINITE ELEMENT MODEL,” presented at the ASME International Mechanical Engineering Congress and Exposition (IMECE2013), San Diego, CA, 2013, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/53235.