CLARKSON UNIVERSITY Department of Mechanical and Aeronautical Engineering AE/ME 350 Aircraft Structural Analysis (Fall 2010) Test 2 Solution Closed book Closed notes Time 1:15 hour
1. Sketch a V-n diagram and label the axes and the limit lines.
10.0 10.0

Homework I 8/23/2006
Problem overview The beam of a rectangular thin-walled section (i.e. t is very small) is designed to carry both bending moment M and torque T. The following series of questions is intended to illuminate the weight efficiency issues as

Problem 2.1 Solution:
a)
x ' x ' u x x x(1 ) x(1 0.03) 1.03x y ' y v y y y (1 ) y (1 0.01) 0.99 x z ' z z
b)
xx
xy
c)
dv du d 0.01 zz 0.03 yy 0 dy dx dz dv du d dv d d 0 yz 0 xz 0 dx dy dy dz dx dz
V ' x ' y ' z ' 1.03 x *0.99 y * z 1.0197 xyz V V

Calculate the maximum shear stress for two cases: (a) xx = yy = zz = 4MPa xy = 1MPa (b) same as case a, except that zz = 0 . Why is the maximum shear stress larger in case b? The three principal stresses for case a) are 1 = 5, 2 = 4, 3 = 3MP a so the maxi

Problem4.3.ForsectionsinFigures4.20and4.21thesymmetrymeansthatwehavebendingonly abouttheyaxis(samedirectionasthemoment),sothatonecanuseEqs.4.31and4.32.Forthesection inFig.4.22,theabsenceofsymmetrymeansthatyouneedtouseEq.4.33. a. Youfirstwanttocalculatethe

Problem 5.3 Find the shear center ysc for the sections of Figures 5.30 and 5.32. For the four-stringer section, assume the tin sheets are ineffective in bending. Solution a) For the section of Figure. 5.30 100mm t=2mm 200mm
The moment of inertia of the th

Example - SF, BM, Torsion Calculation
Rectangular wing: chord = 0.5 m, span = 4 m, TOGW = 5,000 N, nmax = 4 Wing area = 2 sq m, AR = b/c =8
Calculate total lift force (approx. normal force) on each wing: Lw = (W * n *1.5 / 2) =15,000 N (Ultimate load on e

FlexuralShearinThinWalledSections
OpenThinWalledSection
Usesn coordinatesystemforthinwalledsections.Thesaxisisalongwall centerline,naxisisperpendiculartoit.
z
n
xn
z
xs
x
Vz s
x
C
y
xs Shearstressalongwall= Shearstressperpendiculartosaxis= xn xn Since

CLARKSON UNIVERSITY Department of Mechanical and Aeronautical Engineering AE/ME 350 Aircraft Structural Analysis (Fall 2010) Sample Test #1 Closed book Closed notes Time : 1:15 hour
1. List the five main requirements/design criteria for aircraft structura

CLARKSON UNIVERSITY Department of Mechanical and Aeronautical Engineering AE/ME 350 Aircraft Structural Analysis (Fall 2010) Sample Test #2 Closed book Closed notes Time 1:15 hour
1. Sketch a V-n diagram and label the axes and the limit lines. 2. What is