Abstract
This paper presents the comparison of structural deformation of generic metals and the new age composite materials on the aircraft nose during a crash. The analysis is conducted to be able to make more educated predictions of the internal structure damage caused when the airplane has a head on collision with a vertical obstacle (buildings) or when affected by a bird strike. Two nose profiles widely seen nowadays are spherically blunted tangent ogive and elliptical. These nose cones have been designed based on model to prototype ratio on NX CAD. CFD has been performed on the nose designs and solved on ANSYS Fluent for flow visualizations. Materials like Aluminum alloy (which is still widely used in fuselage frames) and Carbon Fiber Reinforced Polymer with epoxy resins, have been applied to the CAD models. These were analyzed for stress, strain and deformation on ANSYS 18.1 by simulating the crash of the nose on a thick structural steel plate. After the analysis, it was inferred that the elliptical nose made of Carbon Fiber Reinforced Polymer has less structural deformation on being crashed.
Highlights
The design of the nose cone of aircraft is such that it can move through a compressible fluid
Data collected of the nose cone profiles from the research papers
The materials that we decided to assign to the nose cones are Aluminium Alloy 2024-T3 and carbon fiber reinforced polymers (CFRPs) (70% carbon unidirectional fibers in epoxy matrix)
Summary
Flying may be the safest mode of transit, accidents could occur through involvement of humans, because of mechanical failure, or due to any sort of crime[22]. A FEM model of aircraft was analyzed in LS Dyna for a vertical drop test at 30ft/s It was to study the impact of the occupants and the structures [4]. Fiber metal laminates have less moisture absorbing capacity than carbon epoxy composites due to its metallic barriers [5] They have great stiffness to weight ratio, less fatigue and resistant to corrosion [5]. A number of fiber metal laminates of aluminium/ boron titanium/ carbon/epoxy can be developed for better properties. There has been not any significant contribution in the study of the crash impact to the nose structure of the aircraft and the communication systems that it houses. One of the reasons why composite structures and metal sandwich laminates are still not used in the aircraft structures is because of the lack of development in computer aided engineering solutions. This report will explore the study of comparison between a generic metallic nose and a composite nose
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