Results 191 to 200 of about 15,386 (232)

Assessment of Materials for Fuselage Panels Considering Fatigue Behavior

Materials Science Forum, 2012
Minimum-weight designs are frequently too costly to manufacture, whereas less expensive and easy to fabricate and assemble designs are often much heavier. The most efficient design on the basis of both cost and weight often lies between these two extremes.
S.M.O. Tavares, Pedro P. Camanho, P.M.S.T. de Castro   +2 more
openaire   +1 more source

Observations from the Inspection of an Aged Fuselage Panel

Journal of Aircraft, 2005
An aged aluminum 7075-T6 fuselage panel was inspected for evidence of time-based degradation. Although corrosion pitting and intergranular attack (IGA) were the focus of the investigation, evidence of cracking and fretting wear were documented as well.
Paul N. Clark, Kimberli Jones, J. T. Huang, David W. Hoeppner   +3 more
openaire   +1 more source

Progress in laser beam welding of aircraft fuselage panels

ICALEO 2008: 27th International Congress on Laser Materials Processing, Laser Microprocessing and Nanomanufacturing, 2008
The most challenging objective for future metallic fuselages is to reduce weight and to obtain lower production costs in comparison to CFRP-Materials. On the metallic side, Airbus established successful laser beam welded stringer-skin-joints in the lower fuselage to overcome current limitations of conventional riveting techniques [1-7].
Dirk Dittrich, Berndt Brenner, Bernd Winderlich, Eckhard Beyer, Jens Hackius   +4 more
openaire   +1 more source

Methodologies for optimal design of composite fuselage crown panels

35th Structures, Structural Dynamics, and Materials Conference, 1994
A computer-based optimization design algorithm known as COSTADE is discussed. The primary focus of the paper is on skin-stringer crown panel design, although the approach used is applicable to fuselage keel and side panel design as well. The underlying design philosophy and methods used to calculate effective panel stiffness, strength, damage tolerance,
M. Tuttle, Z. Zabinsky
openaire   +1 more source

Mechanical Behavior of a Fuselage Stiffened Carbon-Epoxy Panel under Debonding Load

Journal of Aeronautics & Aerospace Engineering, 2018
The present project sets out the analysis of mechanical behaviour of a carbon-epoxy stiffened panel under bending load. For this purpose, the National Polytechnic Institute of Mexico counts with a non-airworthy B727-200 as experimental platform. The first step was to calculate the aerodynamics loads and flight envelope of the aircraft.
M, Torres, H, Hernández-Moreno, Ea, Franco-Urquiza, Ma, González-Villa   +3 more
openaire   +2 more sources

NUMERICAL-EXPERIMENTAL CORRELATION OF A STIFFENED FUSELAGE PANEL

2002
Leuven ...
FRANCO, FRANCESCO, NATALE C, AUSILIO G, MARULO, FRANCESCO   +3 more
openaire   +3 more sources

Modeling of a Helicopter Fuselage Panel with Active Vibration Control

Proceedings of the 5th International Conference on Mechatronics and Control Engineering, 2016
In this study, modeling of a helicopter fuselage panel with active vibration control is carried out. In order to represent the helicopter body shell, a cabin panel clamped from four edges is designed. Piezoelectric patches are attached on the body according to the literature.
Erdi Gülbahçe, Mehmet Çelik
openaire   +1 more source

Knowledge Based Design Method for Fibre Metal Laminate Fuselage Panels

Volume 2: 31st Design Automation Conference, Parts A and B, 2005
Fibre Metal Laminates (FML) are a member of the hybrid materials family, consisting of alternating metal layers and layers of fibres embedded in a resin. Improved damage resistance and tolerance result in a significant weight and maintenance cost reduction compared to aluminium.
B. Vermeulen, M. J. L. van Tooren, L. J. B. Peeters   +2 more
openaire   +1 more source

Experimental Modal Analysis of an Aircraft Fuselage Panel

Hypersonic aircraft structures must operate in complex loading conditions and very high temperatures, making the design of a robust and reusable platform very challenging. An analytical and experimental test program was developed by the Air Force Research Laboratory (AFRL) and industry.
Travis A. Wyen, Joshua J. Schoettelkotte, Ricardo A. Perez, Thomas G. Eason   +3 more
openaire   +1 more source

C-130 Weldbonded Fuselage Panel Flight Evaluation Program.

1977
Abstract : The objective of this program was to conduct an in-service evaluation of the C-130 weldbonded fuselage panel. A total of seven nondestructive inspections were conducted during which all of the inspections included visual and ultrasonic inspection of the weldbonded joints.
openaire   +1 more source