Aeroelastic optimization on composite skins of large aircraft wings

2012 ◽  
Vol 55 (4) ◽  
pp. 1078-1085 ◽  
Author(s):  
Lu Liang ◽  
ZhiQiang Wan ◽  
Chao Yang
Keyword(s):  
Aircraft Wings ◽  
Composite Skins ◽  
Large Aircraft

Wing Testing: A Method of Testing the Wing Structure of Large Aircraft Adopted by Vickers Armstrong

1945 ◽  
Vol 49 (417) ◽  
pp. 599-610
Author(s):  
H. H. Gardner
Keyword(s):  
Structural Testing ◽  
Strength Testing ◽  
Aircraft Wings ◽  
Wing Structure ◽  
Work Done ◽  
Large Aircraft

During the lecture on structural testing given by Dr. Pugsley to the Royal Aeronautical Society, reference was made to the work done at Weybridge on the strength testing of aircraft wings, and during the discussion the lecturer suggested that details of this work should be submitted to the Society for publication. This paper attempts to give a brief outline of some of the more interesting developments which have taken place during the war period, together with a few notes on the arguments which led to the adoption of the final form of test gear.

Resolvent Analysis of Large Aircraft Wings in Edge-of-the-Envelope Transonic Flow

2022 ◽  
Author(s):  
Jelle Houtman ◽  
Sebastian Timme ◽  
Ati Sharma
Keyword(s):  
Transonic Flow ◽  
Aircraft Wings ◽  
Large Aircraft

Large aircraft flying qualities revisited

1990 ◽  
Author(s):  
R. MEYER ◽  
E. HUSBAND
Keyword(s):  
Flying Qualities ◽  
Large Aircraft

scholarly journals Aeroelastic Stability Analysis of Electric Aircraft Wings with Distributed Electric Propulsors

Aerospace ◽  
2021 ◽  
Vol 8 (4) ◽  
pp. 100
Author(s):  
Mohammadreza Amoozgar ◽  
Michael I. Friswell ◽  
Seyed Ahmad Fazelzadeh ◽  
Hamed Haddad Khodaparast ◽  
Abbas Mazidi ◽  
...  
Keyword(s):  
Angular Momentum ◽  
Electric Propulsion ◽  
Aeroelastic Stability ◽  
Concentrated Mass ◽  
High Lift ◽  
Aircraft Wings ◽  
Time Space ◽  
Beam Equations ◽  
Geometrically Exact Beam ◽  
Electric Aircraft

In this paper, the effect of distributed electric propulsion on the aeroelastic stability of an electric aircraft wing was investigated. All the electric propulsors, which are of different properties, are attached to the wing of the aircraft in different positions. The wing structural dynamics was modelled by using geometrically exact beam equations, while the aerodynamic loads were simulated by using an unsteady aerodynamic theory. The electric propulsors were modelled by using a concentrated mass attached to the wing, and the motor’s thrust and angular momentum were taken into account. The thrust of each propulsor was modelled as a follower force acting exactly at the centre of gravity of the propulsor. The nonlinear aeroelastic governing equations were discretised using a time–space scheme, and the obtained results were verified against available results and very good agreement was observed. Two case studies were considered throughout the paper, resembling two flight conditions of the electric aircraft. The numerical results show that the tip propulsor thrust, mass, and angular momentum had the most impact on the aeroelastic stability of the wing. In addition, it was observed that the high-lift motors had a minimal effect on the aeroelastic stability of the wing.

scholarly journals Multiscale Characterization of E-Glass/Epoxy Composite Exposed to Extreme Environmental Conditions

2021 ◽  
Vol 5 (3) ◽  
pp. 80
Author(s):  
George Youssef ◽  
Scott Newacheck ◽  
Nha Uyen Huynh ◽  
Carlos Gamez
Keyword(s):  
Power Distribution ◽  
Epoxy Composite ◽  
Fire Retardant ◽  
Sandwich Composite ◽  
Dynamic Mechanical Analyzer ◽  
Fire Event ◽  
Balsa Wood ◽  
X Ray ◽  
Dynamic Mechanical ◽  
Composite Skins

Fiber-reinforced polymer matrix composites continue to attract scientific and industrial interest since they offer superior strength-, stiffness-, and toughness-to-weight ratios. The research herein characterizes two sets of E-Glass/Epoxy composite skins: stressed and unstressed. The stressed samples were previously installed in an underground power distribution vault and were exposed to fire while the unstressed composite skins were newly fabricated and never-deployed samples. The mechanical, morphological, and elemental composition of the samples were methodically studied using a dynamic mechanical analyzer, a scanning electron microscope (SEM), and an x-ray diffractometer, respectively. Sandwich composite panels consisting of E-glass/Epoxy skin and balsa wood core were originally received, and the balsa wood was removed before any further investigations. Skin-only specimens with dimensions of ~12.5 mm wide, ~70 mm long, and ~6 mm thick were tested in a Dynamic Mechanical Analyzer in a dual-cantilever beam configuration at 5 Hz and 10 Hz from room temperature to 210 °C. Micrographic analysis using the SEM indicated a slight change in morphology due to the fire event but confirmed the effectiveness of the fire-retardant agents in quickly suppressing the fire. Accompanying Fourier transform infrared and energy dispersive X-ray spectroscopy studies corroborated the mechanical and morphological results. Finally, X-ray diffraction showed that the fire event consumed the surface level fire-retardant and the structural attributes of the E-Glass/Epoxy remained mainly intact. The results suggest the panels can continue field deployment, even after short fire incident.

Notes on Power Operated Controls for Large Aircraft

1945 ◽  
Vol 49 (410) ◽  
pp. 51-54
Author(s):  
A. Gouge
Keyword(s):  
North America ◽  
North Atlantic ◽  
The North ◽  
The World ◽  
The North Atlantic ◽  
Large Aircraft

A Study of the air routes of the world brings out almost at once the fact that some of the most difficult route are also the most attractive. For instance, the North Atlantic route which couples North America with Europe is certainly one of the most difficult in the world, but also by the fact that it couples two of the most densely populated, as well as the most wealthy groups of people in the world, one of the most attractive.

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