Crashworthiness tests on model aircraft fuselage structures

1979 ◽  
Keyword(s):  
Aircraft Fuselage ◽  
Model Aircraft

Determination of a soundproofing capacity of the model aircraft fuselage compartment

2009 ◽  
Vol 52 (2) ◽  
pp. 235-239
Author(s):  
A. Ya. Zverev ◽  
V. V. Chernykh
Keyword(s):  
Aircraft Fuselage ◽  
Model Aircraft

A model to assess the fatigue behaviour of ageing aircraft fuselage

2001 ◽  
Vol 24 (10) ◽  
pp. 677-686 ◽  
Author(s):  
I. D. Diamantakos ◽  
G. N. Labeas ◽  
SP. G. Pantelakis ◽  
TH. B. Kermanidis
Keyword(s):  
Fatigue Behaviour ◽  
Aircraft Fuselage

scholarly journals In-Plane Heatwave Thermography as Digital Inspection Technique for Fasteners in Aircraft Fuselage Panels

2020 ◽  
Vol 11 (1) ◽  
pp. 132
Author(s):  
Michael Stamm ◽  
Peter Krüger ◽  
Helge Pfeiffer ◽  
Bernd Köhler ◽  
Johan Reynaert ◽  
...  
Keyword(s):  
Inspection Time ◽  
Scanning Laser ◽  
Aviation Industry ◽  
Automated Inspection ◽  
Comparison Study ◽  
Laser Doppler Vibrometry ◽  
Inspection Method ◽  
Aircraft Fuselage ◽  
Temporal Tracking ◽  
Lock In

The inspection of fasteners in aluminium joints in the aviation industry is a time consuming and costly but mandatory task. Until today, the manual procedure with the bare eye does not allow the temporal tracking of a damaging behavior or the objective comparison between different inspections. A digital inspection method addresses both aspects while resulting in a significant inspection time reduction. The purpose of this work is to develop a digital and automated inspection method based on In-plane Heatwave Thermography and the analysis of the disturbances due to thermal irregularities in the plate-like structure. For this, a comparison study with Ultrasound Lock-in Thermography and Scanning Laser Doppler Vibrometry as well as a benchmarking of all three methods on one serviceable aircraft fuselage panel is performed. The presented data confirm the feasibility to detect and to qualify countersunk rivets and screws in aluminium aircraft fuselage panels with the discussed methods. The results suggest a fully automated inspection procedure which combines the different approaches and a study with more samples to establish thresholds indicating intact and damaged fasteners.

Implementation of value-driven optimisation for the design of aircraft fuselage panels

2009 ◽  
Vol 117 (2) ◽  
pp. 381-388 ◽  
Author(s):  
Sylvie Castagne ◽  
Richard Curran ◽  
Paul Collopy
Keyword(s):  
Aircraft Fuselage

FEM-BEM Modeling and Experimental Verification of the Vibro-Acoustic Behaviour of a Section of Aircraft Fuselage

2016 ◽  
Author(s):  
Viken N. Koukounian ◽  
Chris K. Mechefske
Keyword(s):  
Transmission Loss ◽  
Pressure Fluctuations ◽  
Experimental Methodology ◽  
Reverberation Chamber ◽  
Aircraft Fuselage ◽  
Ongoing Work ◽  
Damping Materials ◽  
Fuselage Skin ◽  
International Testing ◽  
Testing Standards

The aerodynamics of an aircraft in flight impose significant stresses upon the structure. Specifically, the mechanics of fluid flow are highly turbulent and, the layer around the aircraft, is referred to the turbulent boundary layer (TBL). The TBL incites a gradient of pressure fluctuations across the fuselage skin resulting in its vibration, and in turn, the generation of noise inside the passenger cabin. The investigation herein proposes a hybrid FEM-BEM modeling technique to predict the aforementioned vibro-acoustic response and an experimental methodology to verify the results (following ASTM and ANSI international testing standards). The described expectations required construction of an acoustic facility consisting of a reverberation chamber and a semi-anechoic room, the development of DAQ software using LabVIEW, an assembly of DAQ hardware using National Instruments products, and the post-processing of test data using Microsoft Excel. The principal quantity of interest is transmission loss (though insertion loss, absorption and other metrics are also calculated). Two panels (0.04in (40thou) and 0.09in (90thou) in thickness) were simulated and tested (0.01in = 1thou). The calculated error of the proposed methodology is within a maximum of 5dB, with an average of 1dB. Ongoing work is investigating complex constructions and the use of damping materials.

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