Volume 30, Issue 3, May 2017, Pages 540–544
K. BALAJI1, P. GRACEKUMAR2, K. MAHIMAIPRABHU3, M. MANIKANDAN4, and R. RAGHUL5
1 Aeronautical Engineering, Karpagam Institute of Technology, India
2 Aeronautical Engineering, Karpagam Institute of Technology, India
3 Aeronautical Engineering, Karpagam Institute of Technology, India
4 Aeronautical Engineering, Karpagam Institute of Technology, India
5 Aeronautical Engineering, Karpagam Institute of Technology, India
Original language: English
Copyright © 2017 ISSR Journals. This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.
To determine the load distribution in main helicopter rotor blade in study Computational Fluid Dynamics (CFD) and Finite Element Method (FEM) software is used. The aim of the present investigation is the development of a CFD and FEM by using CFD computation procedure capable of accurately simulating the pressure distribution test and velocity test of main helicopter blade and using FEM to simulating flow of thermal behavior test. For this purpose the complete of main rotor blade in CATIA model are used in CATIA modeling. Primary attention in this investigation is focused on defining load on main helicopter rotor blade because of metal trailing edge segments of these blade were replaced with a new segments made from honeycomb composite materials. As critical structural parts with greetings to strength here are glued joints between metal and composite segments of trailing edge are considered. For precise stress analysis of these segments, including glued joints, the finite element method is used.
Author Keywords: ANSYS FLUENT, CATIA, CFD, FEM, ROTOR BLADE.
K. BALAJI1, P. GRACEKUMAR2, K. MAHIMAIPRABHU3, M. MANIKANDAN4, and R. RAGHUL5
1 Aeronautical Engineering, Karpagam Institute of Technology, India
2 Aeronautical Engineering, Karpagam Institute of Technology, India
3 Aeronautical Engineering, Karpagam Institute of Technology, India
4 Aeronautical Engineering, Karpagam Institute of Technology, India
5 Aeronautical Engineering, Karpagam Institute of Technology, India
Original language: English
Copyright © 2017 ISSR Journals. This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.
Abstract
To determine the load distribution in main helicopter rotor blade in study Computational Fluid Dynamics (CFD) and Finite Element Method (FEM) software is used. The aim of the present investigation is the development of a CFD and FEM by using CFD computation procedure capable of accurately simulating the pressure distribution test and velocity test of main helicopter blade and using FEM to simulating flow of thermal behavior test. For this purpose the complete of main rotor blade in CATIA model are used in CATIA modeling. Primary attention in this investigation is focused on defining load on main helicopter rotor blade because of metal trailing edge segments of these blade were replaced with a new segments made from honeycomb composite materials. As critical structural parts with greetings to strength here are glued joints between metal and composite segments of trailing edge are considered. For precise stress analysis of these segments, including glued joints, the finite element method is used.
Author Keywords: ANSYS FLUENT, CATIA, CFD, FEM, ROTOR BLADE.
How to Cite this Article
K. BALAJI, P. GRACEKUMAR, K. MAHIMAIPRABHU, M. MANIKANDAN, and R. RAGHUL, “CHANGING COMPOSITE MATERIAL IN MAIN HELICOPTER ROTOR BLADE,” International Journal of Innovation and Scientific Research, vol. 30, no. 3, pp. 540–544, May 2017.
