3,057,826 research outputs found
Optimal design of a composite wing structure for a flying-wing aircraft subject to multi-constraint
Full text linkThis thesis presents a research project and results of design and optimization of a composite wing structure for a large aircraft in flying wing configuration. The design process started from conceptual design and preliminary design, which includes initial sizing and stressing followed by numerical modelling and analysis of the wing structure. The research was then focused on the minimum weight optimization of the /composite wing structure /subject to multiple design /constraints. The modelling, analysis and optimization process has been performed by using the NASTRAN code. The methodology and technique not only make the modelling in high accuracy, but also keep the whole process within one commercial package for practical application.
The example aircraft, called FW-11, is a 250-seat commercial airliner of flying wing configuration designed through our MSc students Group Design Project (GDP) in Cranfield University. Started from conceptual design in the GDP, a high-aspect-ratio and large sweepback angle flying wing configuration has been adopted. During the GDP, the author was responsible for the structural layout design and material selection. Composite material has been chosen as the preferable material for both the inner and outer wing components. Based on the derivation of structural design data in the conceptual phase, the author continued with the preliminary design of the outer wing airframe and then focused on the optimization of the composite wing structure. Cont/d
Letter from Leonard F. Wing (father) to his son Leonard F. Wing, 4 September 1945
No full textLetter from Leonard F. Wing (father) to his son Leonard F. Wing acknowledging receipt of his previous letter that he will not be getting a discharge, and that Leonard Wing (father) should be getting released within 3-6 months. He is about to leave for Japan, expecting to see his son there.Transcription may be subject to error
Letter from Leonard F. Wing to his father Leonard F. Wing, 27 August 1945
No full textLetter from Leonard F. Wing to his father Leonard F. Wing, letting him know that he received a promotion. Local news sources are speculating that Leonard F. Wing (father) will run for the Senate after he is dischanged. Leonard (son) hopes they are both discharged at the same time and can spend more time together
Letter from Leonard F. Wing (father) to his son Leonard F. Wing, 22 September 1945
No full textLetter from Leonard F. Wing (father) to his son Leonard F. Wing congratulating his son on receiving the promotion, and looking forward to seeing him in Japan.Transcription may be subject to error
Letter from Leonard F. Wing (father) to his son Leonard F. Wing, 18 September 1945
No full textLetter from Leonard F. Wing (father) to his son Leonard F. Wing announcing that the 43rd Army will be demobilizing back to the U. S. and they will likely not see each other as planned. He mentions that he has not been feeling well but assures his son that the doctors are telling him not to worry. (Leonard F. Wing passed away from a heart attack in December, 1945.) He also relates the devastation in multiple Japanese cities.Transcription may be subject to error
Letter from Leonard F. Wing (son) to his father Leonard F. Wing, 12 September 1945
No full textLetter from Leonard F. Wing (son) to his father Leonard F. Wing letting his father know that he is shipping out soon in the role of general's aide, which he assumes will be working with his father
Letter from Leonard F. Wing to his father Leonard F. Wing, 7 September 1945
No full textLetter from Leonard F. Wing to his father Leonard F. Win
Design and fabrication of indium phosphide air-bridge waveguides with MEMS functionality
No full textData used in publication:
Wing H. Ng, Nina Podoliak, Peter Horak, Jiang Wu, Huiyun Liu, William J. Stewart, and Anthony J. Kenyon,
"Design and fabrication of indium phosphide air-bridge waveguides with MEMS functionality"
Submitted to SPIE Microtechnologies conference, 4-6 May 2015, Barcelona, Spain</span
Optimal design of a flying-wing aircraft inner wing structure configuration
Full text linkFlying-wing aircraft are considered to have great advantages and potentials in
aerodynamic performance and weight saving. However, they also have many
challenges in design. One of the biggest challenges is the structural design of
the inner wing (fuselage). Unlike the conventional fuselage of a tube
configuration, the flying-wing aircraft inner wing cross section is limited to a
noncircular shape, which is not structurally efficient to resist the internal
pressure load. In order to solve this problem, a number of configurations have
been proposed by other designers such as Multi Bubble Fuselage (MBF),
Vaulted Ribbed Shell (VLRS), Flat Ribbed Shell (FRS), Vaulted Shell
Honeycomb Core (VLHC), Flat Sandwich Shell Honeycomb Core (FLHC), Y
Braced Box Fuselage and the modified fuselage designed with Y brace
replaced by vaulted shell configurations. However all these configurations still
inevitably have structural weight penalty compared with optimal tube fuselage
layout. This current study intends to focus on finding an optimal configuration
with minimum structural weight penalty for a flying-wing concept in a preliminary
design stage.
A new possible inner wing configuration, in terms of aerodynamic shape and
structural layout, was proposed by the author, and it might be referred as
‘Wave-Section Configuration’. The methodologies of how to obtain a structurally
efficient curvature of the shape, as well as how to conduct the initial sizing were
incorporated.
A theoretical analysis of load transmission indicated that the Wave-Section
Configuration is feasible, and this was further proved as being practical by FE
analysis. Moreover, initial FE analysis and comparison of the Wave-Section
Configuration with two other typical configurations, Multi Bubble Fuselage and
Conventional Wing, suggested that the Wave-Section Configuration is an
optimal design in terms of weight saving. However, due to limitations of the
author’s research area, influences on aerodynamic performances have not yet
been taken into account
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