Space Shuttle Orbiter - Leading edge structural design/analysis and material allowables

1986 ◽  
Author(s):  
D. JOHNSON ◽  
D.M. CURRY ◽  
R. KELLY
2015 ◽  
Vol 16 (1) ◽  
pp. 51-68
Author(s):  
Kazimierz Flaga ◽  
Kazimierz Furtak

Abstract The aim of the article [1] was to discuss the application of steel-concrete composite structures in bridge engineering in the aspect of structural design, analysis and execution. It was pointed out that the concept of steel-concrete structural composition is far from exhausted and new solutions interesting from the engineering, scientific and aesthetic points of view of are constantly emerging. These latest trends are presented against the background of the solutions executed in Poland and abroad. Particular attention is focused on structures of double composition and steel-concrete structures. Concrete filled steel tubular (CFST) structures are highlighted.


2019 ◽  
Vol 207 ◽  
pp. 264-272 ◽  
Author(s):  
Michele Ferraiuolo ◽  
Roberto Scigliano ◽  
Aniello Riccio ◽  
Emanuele Bottone ◽  
Marco Rennella

Author(s):  
Donald V. Rosato ◽  
David P. Di Mattia ◽  
Dominick V. Rosato

2009 ◽  
Vol 22 (2) ◽  
pp. 123-133
Author(s):  
Raymond G. Holstein ◽  
Anthony N. Palazotto ◽  
Richard G. Cobb

2018 ◽  
Vol 29 (16) ◽  
pp. 3222-3241 ◽  
Author(s):  
Srinivas Vasista ◽  
Felix Nolte ◽  
Hans Peter Monner ◽  
Peter Horst ◽  
Marco Burnazzi

The numerical three-dimensional structural design of a large-displacement flexible morphing wing leading edge, otherwise known as a droop nose, is presented in this article. The droop nose is an essential component of a novel internally blown high-lift system for a transport aircraft to delay stall and reduce internal compressor requirements. A design chain consisting of optimization procedures was used to arrive at the structural design of the droop nose composed of a composite fiberglass skin with integral stringers and supporting kinematic mechanisms. The optimization tools aim to produce a design with minimal error to the critical target shapes. A maximum final error of 10.09 mm between calculated and target trajectories of the stringers was found after the kinematic optimization stage. After inputting the kinematic optimization results into the skin optimization stage and solving, a maximum error in the order of 13 mm and curvature difference 0.0028 1/mm were calculated, occurring in the outboard region. Prior two-dimensional analyses with similar shape deviations showed 0.4% lift reduction though further three-dimensional investigations are required. Concepts for integrating industrial requirements abrasion and lightning strike protection and in-flight de-icing into a multifunctional skin show promise and the resulting aerodynamic surface quality was found to be adequate.


2021 ◽  
Author(s):  
Mayank Chetan ◽  
Shulong Yao ◽  
D. Todd Griffith

Abstract. With the progression of novel design, material, and manufacturing technologies, the wind energy industry has successfully produced larger and larger wind turbine rotor blades while driving down the Levelized Cost of Energy (LCOE). Though the benefits of larger turbine blades are appealing, larger blades are prone to aero-elastic instabilities due to their long, slender, highly flexible nature, and this effect is accentuated as rotors further grow in size. In addition to the trend of larger rotors, new rotor concepts are emerging including two-bladed rotors and downwind configurations. In this work, we introduce a comprehensive evaluation of flutter behavior including classical flutter, edgewise vibration, and flutter mode characteristics for two-bladed, downwind rotors. Flutter speed trends and characteristics for a series of both two- and three-bladed rotors are analyzed and compared in order to illustrate the flutter behavior of two-bladed rotors relative to more well-known flutter characteristics of three-bladed rotors. In addition, we examine the important problem of blade design to mitigate flutter and present a solution to mitigate flutter in the structural design process. A study is carried out evaluating the effect of leading edge and trailing edge reinforcement on flutter speed and hence demonstrates the ability to increase the flutter speed and satisfy structural design requirements (such as fatigue) while maintaining or even reducing blade mass.


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