Mechanics of Aircraft structures
C.T. Sun
4.1
A uniform beam of a thin-walled angle section as shown in Fig. 4.19 is
subjected to the bending M y ( M z = 0 ). Find the neutral axis and bending
stress distribution over the cross-section.
Figure 4.19
Thin-w
MAE 166A Analysis of Flight Structures
Homework4. Due date October 28, 2016
Reading assignment: Chapter 3
Solve the following problems from Sun book
1
2
3
4
5
6
Problem 3.5
Problem 3.6
Problem 3.8
Problem 3.9
Problem 3.10
Problem 3.12
MAE 166A Analysis of Flight Structures
Homework6. Due date November 11, 2016
Reading assignment: Chapter 4 again
Solve the following problems from Sun book
1
2
3
4
5
Problem 4.4
Problem 4.7
Problem 4.9
Problem 5.1
Problem 5.2
MAE 166A Analysis of Flight Structures
Homework1. Due date October 7, 2016
Reading assignment: Chapter1 and review beam theory from 101
Solve the following problem from Sun book
1.
2.
3.
4.
5.
6.
7.
Problem 1.3
Problem 1.4
Problem 1.6
Problem 2.2
Problem
MAE 166A Analysis of Flight Structures
Homework5. Due date November 4, 2016
Reading assignment: Chapter 4
Solve the following problems from Sun book
1.
2.
3.
4.
5.
Problem 4.1
Problem 4.2
Problem 4.4
Problem 4.5
Problem 4.6
MAE 166A Analysis of Flight Structures
Homework3. Due date October 21, 2016
Reading assignment: Chapter 3
a) Solve the following problems from Sun book
1
2
3
4
5
b)
1.
2.
3.
Problem 2.17 (also find the displacement field)
Problem 2.18
Problem 3.1
Problem
MAE 166A Analysis of Flight Structures
Homework2. Due date October 14, 2016
Reading assignment: Chapter 2
a) Consider a state of stress given by
xx = 4
yy = -2
xy = 4
Use Mohrs circle to determine the stress tensor as seen by an observer who is
rotated 15
MAE 166A Analysis of Flight Structures
Homework6. Due date November 23, 2016
Reading assignment: Chapter 5
Solve the following problems from Sun book
1
2
3
4
5
6
7
Problem 5.3
Problem 5.5
Problem 5.7
Problem 5.11
Problem 5.15
Problem 6.3
Problem 6.4
Mechanics of Aircraft structures
C.T. Sun
1.3
The dimensions of a steel (300M) I-beam are b = 50 mm, t = 5 mm, and h = 200
mm (Fig. 1.17). Assume that t and h are to be fixed for an aluminum(7075-T6)
I-beam. Find the width b for the aluminum beam so that
1. Consider a state of stress given by
xx = 4 MPa
yy = -2 MPa
xy = 4 MPa
Use Mohrs circle to determine the stress tensor as seen by an observer who is rotated 15
degrees clockwise from the x axis.
We can use two-point method to draw the Mohrs circle.
The
Mechanics of Aircraft structures
C.T. Sun
3.2
Show that the Prandtl stress function for bars of circular solid sections is also
valid for bars of hollow circular sections as shown in Fig. 3.34. Find the torsion
constant J in terms of the inner radius ai a
Mechanics of Aircraft structures
C.T. Sun
2.17
Consider a thin rectangular panel loaded as shown in Fig. 2.20. Show that the
Airy stress function
= c1 x 2 + c 2 xy + c3 y 2
solves the problem. Find the constants c1, c2, c3.
y
0
0
b
x
a
Figure 2.20 Thin r
Mechanics of Aircraft structures
C.T. Sun
4.4
Compare the bending capabilities of the two sections of Figs. 4.21 and 4.22 if
M y = 0, Mz 0.
Figure 4.21
Stringer-web section
Figure 4.22
Stringer-web section
Solution:
The thin sheets are assumed to be negli
Mechanics of Aircraft structures
C.T. Sun
3.5
The two-cell section in Fig.3.35 is obtained from the single-cell section of
Fig.3.36 by adding a vertical web of the same thickness as the skin. Compare the
torsional rigidity of the structures of Figs. 3.35