Topology Optimization of Aircraft Fuselage Structure
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.
[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
[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
@article{"International Journal of Mechanical, Industrial and Aerospace Sciences:58953", author = "Muniyasamy Kalanchiam and Baskar Mannai", title = "Topology Optimization of Aircraft Fuselage Structure", 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.", volume = "7", number = "5", pages = "885-4", }