The aim of this exercise is to perform a Finite Element Analysis using M.Sc. Patran/Nastran tool on a hyperboloid structure. The structure is a part of the tail section of PW-6U glider. Angular straight Beams are created as re-enforcement of the structure. The load is taken from the manual of the PW-6U glider and a Linear and a Buckling analysis is performed to see the effect of the beams on the structural strength.
Table of Contents
Aim
Software Version
File required
Problem Description
Instructions for exercise
1. Create a new database
2. Create curve geometry
3. Create Point Geometry
4. Create Curve Geometry
5. Create Point Geometry
6. Create Curve Geometry
7. Create mesh seeds
8. Create curve mesh
9. Create surface mesh
10. Create material Properties
11. Create Beam Properties
12. Create 2D shell
13. Create Node at both the side of the cylinder
14. Create RBE 2
15. Create Boundary conditions
16. Apply Load
17. Perform Analysis
18. Access Result File
19. Attach Results
20. Buckling Analysis
Objectives and Topics
The primary objective of this exercise is to perform a finite element analysis (FEA) on a hyperboloid fuselage section, representative of the tail section of a PW-6U glider, to evaluate its structural integrity under specific loading conditions. The study investigates the effect of reinforcing beams on the structural strength and buckling behavior of a thin-skinned aircraft component.
- Finite Element Analysis (FEA) using MSC Patran and Nastran.
- Structural modeling of thin-skinned fuselage sections.
- Implementation and evaluation of angular straight reinforcing beams.
- Linear static analysis and buckling analysis.
- Assessment of structural response to horizontal loading.
Excerpt from the Book
Problem Description
The primary design of a small fuselage section of an aircraft.
Design of re-enforcing beams for the fuselage and the aim is to evaluate the structural integrity of the entire structure.
The beams are made of Aluminium, E = 69000 M.Pa, Poisson Ratio = 0.33.
The beams are solid rectangular beams with W = 3, H = 7.
The skin of the fuselage is also made of aluminium and having a thickness of 0.5mm.
One end of the fuselage is totally fixed and the other side is under a load of 2379 N which is horizontal with the axis of the structure. (The load is given in ‘Y’ axis).
The structure should be able to take the load and the beams should be able to perform properly under buckling while the skin is kept very thin.
Summary of Chapters
Aim: Defines the purpose of performing FEA on a hyperboloid aircraft structure to assess structural strength and the impact of reinforcement.
Software Version: Lists the specific versions of MSC Patran and Nastran required to execute the simulation steps.
Problem Description: Outlines the technical specifications, material properties, dimensions, and boundary conditions for the fuselage section.
Instructions for exercise: Provides a comprehensive, step-by-step tutorial on building the geometry, meshing, material assignment, and performing both linear and buckling analyses.
Keywords
Finite Element Analysis, MSC Patran, MSC Nastran, Fuselage Structure, Hyperboloid, Reinforcing Beams, Buckling Analysis, Linear Static Analysis, Structural Integrity, Aluminium, PW-6U Glider, Thin Skin, Boundary Conditions, Meshing, RBE2
Frequently Asked Questions
What is the primary purpose of this exercise?
The primary purpose is to learn how to conduct a Finite Element Analysis on a complex hyperboloid fuselage structure using MSC Patran and Nastran, specifically focusing on its structural integrity and buckling characteristics.
What are the main thematic areas covered in this document?
The document covers FEA workflows including geometry creation, meshing, application of material properties, setting up boundary conditions and loads, and running linear static and buckling simulations.
What is the core research question or objective?
The objective is to evaluate how the addition of angular reinforcing beams affects the structural strength and buckling performance of a thin-skinned aircraft fuselage component under a specified horizontal load.
Which scientific software tools are utilized for this analysis?
The analysis utilizes M.Sc. Nastran 2012.2 and Patran 2011-64 bit.
What topics are addressed in the main part of the document?
The main body provides detailed procedural instructions for the entire simulation pipeline, from creating the geometric database to post-processing and visualizing the stress and buckling results.
Which keywords best describe this study?
Key terms include Finite Element Analysis, Fuselage Structure, Reinforcing Beams, Buckling Analysis, Structural Integrity, and MSC Patran/Nastran.
How is the fuselage modeled regarding its reinforcement?
The model incorporates solid rectangular aluminum beams as reinforcements and a thin aluminum skin (0.5mm thickness) to simulate the structural behavior of the tail section.
What specific boundary conditions are applied to the model?
One end of the fuselage is fixed (rigidly constrained), while the other end is subjected to a 2379 N horizontal load applied via an MPC (RBE2) element connected to a center node.
- Citation du texte
- SOURAV PAUL (Auteur), 2014, Instruction on FEM Analysis Using MSC Nastran/Patran. Linear and Buckling Analysis, Munich, GRIN Verlag, https://www.grin.com/document/298375
