Parametric and topology optimization of load bearing elements of aircraft fuselage structure

This paper presents the weight reduction of load bearing elements of aircraft DA-62 fuselage structure using parametric and topology optimizations methods. The structural analysis of rear part of aircraft fuselage in various load calculation conditions is performed. In the first step using parametri...

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Bibliographic Details
Published in:IOP conference series. Materials Science and Engineering 2020-09, Vol.934 (1), p.12029
Main Authors: Htet, Tun Lin, Prosuntsov, P V
Format: Article
Language:English
Subjects:
Aircraft
Airframes
Fuselages
Load bearing elements
Optimization
Structural analysis
Topology optimization
Weight reduction
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Summary:This paper presents the weight reduction of load bearing elements of aircraft DA-62 fuselage structure using parametric and topology optimizations methods. The structural analysis of rear part of aircraft fuselage in various load calculation conditions is performed. In the first step using parametric optimization of structure, allow to reduce its mass to 15.84 %. In addition using topology optimization of optimized structure by parametric modeling added mass reduction to 32.87% of total structural mass.
ISSN:1757-8981
1757-899X
DOI:10.1088/1757-899X/934/1/012029