Instruction on FEM Analysis Using MSC Nastran/Patran. Linear and Buckling Analysis

Reinforcing Beams on a Fugelage Structure Using very Thin Skin, Fixed at one End

Seminar Paper , 2014 , 34 Pages , Grade: 5

Engineering - Aerospace Technology

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.

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Aim

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.

Software Version

M.Sc. Nastran 2012.2

Patran 2011-64 bit.

File required

None

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.

Load,

2379 N

Fixed end of

the structure

Reenforcing

beams

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Instructions for exercise

1. Create a new database

A

B

C

D

E

F

Create a new database:

A.

File / New...

B.

Enter

criss_cross_reenforc

ement.db as the File

name

C.

Click OK

D.

Select Default

E.

Select Structural

F.

Click OK

---

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A

B

C

D

E

F

A. Click on Home option.

B. Arrange the Co-ordinate as shown

in the figure at left hand side.

C. Click on Geometry option and

Select: Create/Point/XYZ.

D. Uncheck the Auto execute.

E. Insert [3600 0 0] in Point

Coordinate list.

F. Click Apply.

G. Do the same steps for a Point

Coordinate list of [3800 0 0]

---

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After all these steps the geometry should look like the below given figure.

Create curve geometry:

A. Click on the Geometry icon

B. Geometry:

Create/Curve/2Dcircle

C. Input Radius 187

D. Enter construction plane list

Coord 0.1

E. Uncheck Auto Execute

F. Enter <3600 0 0> as the

Center point list

G. Click Apply

H. Create another curve

following the same steps,

Enter <3800 0 0> as the

Center point list

B

A

C

D

E

F

---

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Create Point Geometry

A. Click on the Geometry icon

B. Geometry:

Create/Point/Interpolate

C. Option: Curve

D. Enter 10 in Number of Interior

Points

E. Uncheck Auto Execute

F. Select Curve 1 and 2 in the

curve list

G. Click Apply

A

B

C

D

E

F

G

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p.s: We are creating 2 point curve between one point of the first circular curve and second point of the

other circular curve as our aim is to create straight curve in an angle between two circular curves.

Create Curve Geometry

A. Click on the Geometry icon

B. Geometry: Create/Curve/Point

C. Option: 2 point

D. Uncheck Auto Execute

E. Select Point 1 as shown in picture as

starting point list.

F. Select Point 2 as shown in the picture

as ending point list

G. Click Apply

H. Follow the same steps and create a

curve for point 3 and 4.

I. Follow the steps for every points.

1

2

3

4

A

B

C

D

E

F

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After all the above mentioned steps the geometry should look like the following fig:

A. Click on the Preferences

icon.

B. Select the Picking option.

C. Check the Enclosed entire

entity option.

D. Click the Close option.

A

B

C

D

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Note: In this step we will break the circular curves at every point on the curves. That means we will

break that one circular curve in ten small curves.

A. Click on the Geometry icon.

B. Geometry: Edit/Curve/Break.

C. Option: Point.

D. Check the Delete Original curves.

E. Uncheck Auto Execute.

F. In the Curve list select the circular curve as

shown in the figure.

G. In the Break point list option select all the

points on the selected curve similarly how

we selected the curve list.

H. Click Apply.

I. Follow the same steps for the curve at the

other end of the cylinder.

A

B

C

D

E

F

G

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2

1

3

4

A. Click on the Geometry icon

B. Geometry: Create/Surface/Curve

C. Option: 2 Curve.

D. Uncheck Auto Execute.

E. In the starting curve list select the curve

marked as 1 in the figure.

F. In the ending curve list option select the

curve marked as 2 in the figure.

G. Click Apply.

H. Follow the same steps for all the curves.

A

B

C

D

E

F

G

• College: Warsaw University (FACULTY OF POWER AND AERONAUTICAL ENGINEERING)
• Course: M.Sc AEROSPACE ENGINEERING
• Grade: 5
• Author: SOURAV PAUL (Author)
• Publication Year: 2014
• Pages: 34
• Catalog Number: V298375
• ISBN (eBook): 9783656966234
• ISBN (Book): 9783656966241
• Language: English
• Tags: MSC NASTRAN/PATRAN, FEM ANALYSIS