Topology Optimization of Aircraft Fuselage Structure

Authors: Muniyasamy Kalanchiam, Baskar Mannai

Abstract:

Topology Optimization is a defined as the method of determining optimal distribution of material for the assumed design space with functionality, loads and boundary conditions [1]. Topology optimization can be used to optimize shape for the purposes of weight reduction, minimizing material requirements or selecting cost effective materials [2]. Topology optimization has been implemented through the use of finite element methods for the analysis, and optimization techniques based on the method of moving asymptotes, genetic algorithms, optimality criteria method, level sets and topological derivatives. Case study of Typical “Fuselage design" is considered for this paper to explain the benefits of Topology Optimization in the design cycle. A cylindrical shell is assumed as the design space and aerospace standard pay loads were applied on the fuselage with wing attachments as constraints. Then topological optimization is done using Finite Element (FE) based software. This optimization results in the structural concept design which satisfies all the design constraints using minimum material.

Keywords: Fuselage, Topology optimization, payloads, designoptimization, Finite Element Analysis.

Digital Object Identifier (DOI): doi.org/10.5281/zenodo.1073625

References:

[1] Abbani Rinku, Prashanth R, Naveen Kumar R O.,"Structural Optimization of Light Transport Aircraft Components", Altair HTC- 2008
[2] Roman Stainko, "A short excursion on topology optimization"
[3] O. M├╝ller, A. Albers, J. Sauter, P. Allinger, "Topology Optimization of Large Real World Structures", NAFEMS
[4] Altair Optistruct - User manual.
[5] Michael Chun - Yung Nu, "Airframe Structural Design".
[6] Muniyasamy Kalanchiam, Uma anand Duraisamy, "Application of Topology Optimization in Aerospace", SAE Technical Paper 2009-01- 3200, 2009