Fracture Control in Ballistic-Damaged Graphite/Epoxy Wing Structure

2009 ◽  
pp. 338-338-22
Author(s):  
JG Avery ◽  
SJ Bradley ◽  
KM King
Keyword(s):  
Wing Structure ◽  
Fracture Control

scholarly journals Design and experimental structural analysis of a solar powered aircraft wing structure

2021 ◽  
Vol 1057 (1) ◽  
pp. 012027
Author(s):  
Govindu Sandhya ◽  
Vemireddy Sri Rishitha ◽  
S Sriram ◽  
VM Sreehari
Keyword(s):  
Structural Analysis ◽  
Aircraft Wing ◽  
Wing Structure ◽  
Solar Powered

Blood Circulation in Insect Wings

1964 ◽  
Vol 96 (1-2) ◽  
pp. 98-98 ◽  
Author(s):  
J. W. Arnold
Keyword(s):  
Blood Circulation ◽  
The Body ◽  
Insect Wings ◽  
Wing Structure ◽  
Wing Veins ◽  
Taxonomic Groups ◽  
Modified Forms ◽  
Surrounding Membrane

Despite their inert appearance, the wings of insects are living appendages and are supplied with blood. This is true for definitive wings as well as for developing ones, and for modified wings such as tegmina, elytra, hemelytra, and halteres as for those that are specialized for flight. Typically the blood circulates only through the wing veins, but in some insects it escapes into the surrounding membrane in certain areas, and in highly modified forms it may be entirely unconfined. The course of circulation is basically the same in the wings of most insects. It flows outward from the body in the costo-medial veins, moves toward the posterior margins via cross-veins, and returns to the body through the cubito-anal veins and axillary cord. However, rhe precise route followed is highly variable concomitant with distinctive patterns of venation in different taxonomic groups and with wing structure. This is illustrated for a number of orders.

Effect of Film Thickness on Fatigue Strength of TiAl Alloy Coated with TiAlN Film at Elevated Temperature

2005 ◽  
Vol 297-300 ◽  
pp. 1446-1451 ◽  
Author(s):  
Takeshi Kasuya ◽  
Hideto Suzuki
Keyword(s):  
Thin Film ◽  
Fatigue Strength ◽  
Film Thickness ◽  
Thick Film ◽  
Physical Vapor Deposition ◽  
Tial Alloy ◽  
Testing Machine ◽  
Intermetallic Alloy ◽  
Fracture Control ◽  
The Difference

The fatigue strength of TiAl intermetallic alloy coated with TiAlN film was studied in vacuum at 1073K using a SEM-servo testing machine. In addition, three kinds of TiAlN films were given by physical vapor deposition (1, 3, and 10μ m). The fatigue strength of 3μ m was highest. Also, the fatigue strength of 1μ m was lowest. From this result, existence of optimum film thickness was suggested because the difference of fatigue strength arose in each film thickness. The justification for existence of optimum film thickness is competition of 45-degree crack and 90-degree crack. The 45-degree crack is phenomenon seen in the thin film (1μ m), and is caused by plastic deformation of TiAl substrate. The 45-degree crack is the factor of the fatigue strength fall by the side of thin film. In contrast, the 90-degree crack is phenomenon in the thick film (10μ m), and is caused as result of reaction against load to film. The 90-degree crack is the factor of the fatigue strength fall by the side of thick film. In conclusion, the optimum film thickness can perform meso fracture control, and improves fatigue strength.

SIMP for Complex Structures

2016 ◽  
Vol 846 ◽  
pp. 535-540
Author(s):  
David J. Munk ◽  
David W. Boyd ◽  
Gareth A. Vio
Keyword(s):  
Natural Frequencies ◽  
Dynamic Loads ◽  
Topology Optimisation ◽  
Complex Structures ◽  
Structural Failure ◽  
Frequency Range ◽  
Aerodynamic Loading ◽  
Frequency Excitation ◽  
Wing Structure ◽  
Lifting Surfaces

Designing structures with frequency constraints is an important task in aerospace engineering. Aerodynamic loading, gust loading, and engine vibrations all impart dynamic loads upon an airframe. To avoid structural resonance and excessive vibration, the natural frequencies of the structure must be shifted away from the frequency range of any dynamic loads. Care must also be taken to ensure that the modal frequencies of a structure do not coalesce, which can lead to dramatic structural failure. So far in industry, no aircraft lifting surfaces are designed from the ground up with frequency optimisation as the primary goal. This paper will explore computational methods for achieving this task.This paper will present a topology optimisation algorithm employing the Solid Isotropic Microstructure with Penalisation (SIMP) method for the design of an optimal aircraft wing structure for rejection of frequency excitation.

Fracture Control in Composite Materials Using Integral CrackArresters

1977 ◽  
Vol 14 (10) ◽  
pp. 994-999 ◽  
Author(s):  
T. E. Hess ◽  
S. L. Huang ◽  
H. Rubin
Keyword(s):  
Composite Materials ◽  
Fracture Control

scholarly journals Fundamental study on strategy of crack injection repair based on fracture control design concepts.

2002 ◽  
pp. 169-177
Author(s):  
Minoru KUNIEDA ◽  
Kosuke WAKATSUKI ◽  
Toshiro KAMADA ◽  
Keitetsu ROKUGO
Keyword(s):  
Control Design ◽  
Fundamental Study ◽  
Design Concepts ◽  
Fracture Control

DIA-based proteome reveals the involvement of cuticular proteins and lipids in the wing structure construction in the silkworm

2021 ◽  
Vol 238 ◽  
pp. 104155
Author(s):  
Chunyan Fang ◽  
Zhanfeng Ye ◽  
Tingting Gai ◽  
Kunpeng Lu ◽  
Fangyin Dai ◽  
...  
Keyword(s):  
Cuticular Proteins ◽  
Wing Structure
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