.q 1 0
The [B] matrix is equal to zero in which of the following laminates?
.
.a a.	[0,90].
.a b.	[0,45].
.a c.	[0,45,45,0].
.a d.	[0,45,-45].
.A 3
.R
The [B] matrix is equal to zero the [0,45,45,0] laminate

.

.q 2 0
Which of the following will expand the most with temperature?
.
.a a.	Steel.
.a b.	Aluminum.
.a c.	Graphite epoxy in the direction along the fibers.
.a d.	Glass epoxy in the direction along the fibers.
.A 2
.R
Aluminum will expand the most as thermal expansion coefficient along the fiber directions are generally low.
.

.q 3 0
Which of the following will expand the most with temperature?
.
.a a.	Steel.
.a b.	Aluminum.
.a c.	Graphite/Epoxy in the direction parallel to the fibers.
.a d.	Glass/Epoxy in the direction perpendicular the fibers.
.A 4
.R
Generally, Glass/Epoxy will have a higher thermal expansion coefficient in the direction perpendicular to the direction of fibers than aluminum.  However, the value depends on the fiber volume fraction, type of glass fiber and epoxy grade.
.

.q 4 0
Which of the following laminates will not undergo bending from thermal loads?
.
.a a.	[0,45,-45].
.a b.	[0,45,90,90,45,0].
.a c.	[0,30,-45].
.a d.	[0,45,90,45,-45].
.A 2
.R
[0,45,90,90,45,0] will not undergo bending from thermal loads
.

.q 5 0
Hygrothermal stresses and strains are caused by
.
.a a.	Water pressure.
.a b.	Air pressure.
.a c.	Changes in humidity and temperature.
.a d.	Normal loads.
.A 3
.R
Hygrothermal stresses and strains are caused by changes in humidity and temperature
.

.q 6 0
If a hygrothermal load is the only load applied to a lamina, the overall mechanical load is equal to
.
.a a.	the same magnitude as the hygrothermal load.
.a b.	slightly less than the hygrothermal load.
.a c.	the inverse of the hygrothermal load.
.a d.	zero.
.A 4
.R
If a hygrothermal load is the only load applied to a lamina, the overall mechanical load is equal to zero
.

.q 7 0
Hygrothermal forces are considered fictitious thermal forces because
.
.a a.	they don't exist.
.a b.	they act like mechanical forces, but no mechanical force is present.
.a c.	they are uncommon.
.a d.	they can only be produced in a laboratory.
.A 2
.R
Hygrothermal forces are considered fictitious thermal forces because they act like mechanical forces, but no mechanical force is present
.

.q 8 0
Non-symmetric laminates undergo this when hygrothermal loads are applied
.
.a a.	Warpage.
.a b.	They fall apart.
.a c.	No change.
.a d.	Failure.
.A 1
.R
Non-symmetric laminates undergo warpage when hygrothermal loads are applied
.

.q 9 0
Which of the following laminates will not undergo warpage due to hygrothermal loads
.
.a a.	[0,90].
.a b.	[0,90,45].
.a c.	[0,45,-45,0].
.a d.	[45.90].
.A 3
.R
[0,45,-45,0] will not undergo warpage due to hygrothermal loads
.

.q 10 0
Matrix [A*] is known as the 
.
.a a.	Transformation matrix.
.a b.	Extensional compliance matrix.
.a c.	Pending stiffness matrix.
.a d.	Coupling stiffness matrix.
.A 2
.R
Matrix [A*] is known as the Extensional compliance matrix
.

.q 11 0
The coupling matrix [B] is zero for
.
.a a.	all analysis that need simplification.
.a b.	non-symmetric laminates.
.a c.	symmetric laminates.
.a d.	all quasi isotropic laminates.
.A 3
.R
The coupling matrix [B] is zero for symmetric laminates
.

.q 12 0
A typical graphite epoxy lamina of 0.005 inch thickness will fail at about an extensional load of
.
.a a.	1500 pounds.
.a b.	250 pounds.
.a c.	750 pounds.
.a d.	2400 pounds.
.A 3
.R
A typical graphite epoxy lamina of 0.005 inch thickness will fail at about an extensional load of 750 pounds
.

.q 13 0
Which one of the following assumptions does not relate to the classical lamination theory
.
.a a.	Each lamina is orthotropic.
.a b.	The lamina is thin with only in-plane loads.
.a c.	Each lamina is elastic.
.a d.	Slip occurs between lamina interfaces.
.A 4
.R
The assumption that slip occurs between lamina interfaces does not relate to the classical lamination theory
.

.q 14 0
[0/90/90/90/0] is an example of 
.
.a a.	an angle ply laminate.
.a b.	unsymmetric laminate.
.a c.	cross-ply laminate.
.A 3
.R
[0/90/90/0/90] is an example of a cross-ply laminate
.

.q 15 0
[A] [B] and [D] are called
.
.a a.	Extensional, Coupling, and Bending Stiffness matrices, respectively.
.a b.	Extensional, De-coupling, and Bending Stiffness matrices, respectively.
.a c.	Coupling, Bending, and Extensional Stiffness matrices, respectively.
.a d.	None of the above.
.A 1
.R
[A] [B] and [D] are called the Extensional, Coupling, and Bending Stiffness matrices, respectively
.

.q 16 0
The [B] matrix for an asymmetric laminate is 
.
.a a.	zero.
.a b.	non-zero.
.A 2
.R
The [B] matrix for an asymmetric laminate is non-zero
.

.q 17 0
The extensional stiffness matrix [A] for a laminate will not change if 
.
.a a.	stacking sequence is changed.
.a b.	angle of plies is changed.
.a c.	elastic properties of the lamina are changed.
.A 1
.R
The extensional stiffness matrix [A] for a laminate will not change if the stacking sequence is changed 
.

.q 18 2
What do you think of this test?
.
.a 8 60
.A kaw@eng.usf.edu