A manufacturer of single-seater racing cars was considering materials and thicknesses of a sandwich panel concept for the chassis. The design case assumed a 600mm wide simply supported panel of the form shown below, subject to a central point load of 1500N. The distance between the supports was 1.20m.
A manufacturer of single-seater racing cars was considering materials and thicknesses of a sandwich panel concept for the chassis. The design case assumed a 600mm wide simply supported panel of the form shown below, subject to a central point load of 1500N. The distance between the supports was 1.20m.
Elements Of Electromagnetics
7th Edition
ISBN:9780190698614
Author:Sadiku, Matthew N. O.
Publisher:Sadiku, Matthew N. O.
ChapterMA: Math Assessment
Section: Chapter Questions
Problem 1.1MA
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![A manufacturer of single-seater racing cars was considering materials and
thicknesses of a sandwich panel concept for the chassis. The design case assumed
a 600mm wide simply supported panel of the form shown below, subject to a central
point load of 1500N. The distance between the supports was 1.20m.
D =
8 =
To a reasonable approximation the expression for panel stiffness, D, is:
Estsbd²
2
:
[5.44mm]
✓
1.20m
Material
SMC
Core
1500N
and the mid-span deflection, 8, is given by:
WL³ WLtc
+
48D 4bd² Gc
where:
where:
Some data for candidate materials are shown in the table below.
Young's
Modulus
Es = Young's modulus of skin
ts
= thickness of skin
to = core thickness
b
d = tc + 2.ts/2 = tc+ts
Density
(Mg.m-³)
1.8
0.2
tcd h
= panel width = 600mm
W = 1500N,
Span, L = 1.20m
Shear modulus of core material, Gc= 50MPa
(GPa)
10
i. Calculate the mid-span deflections, of a panel with 40mm core thickness,
constructed with 2.0mm thick sheet moulding compound (SMC) skins.](/v2/_next/image?url=https%3A%2F%2Fcontent.bartleby.com%2Fqna-images%2Fquestion%2F27ae1c65-6d36-429b-9d72-b207dc1611cc%2Fc123b563-45f3-4d81-9814-7240baf662dd%2Fjhng4vb_processed.png&w=3840&q=75)
Transcribed Image Text:A manufacturer of single-seater racing cars was considering materials and
thicknesses of a sandwich panel concept for the chassis. The design case assumed
a 600mm wide simply supported panel of the form shown below, subject to a central
point load of 1500N. The distance between the supports was 1.20m.
D =
8 =
To a reasonable approximation the expression for panel stiffness, D, is:
Estsbd²
2
:
[5.44mm]
✓
1.20m
Material
SMC
Core
1500N
and the mid-span deflection, 8, is given by:
WL³ WLtc
+
48D 4bd² Gc
where:
where:
Some data for candidate materials are shown in the table below.
Young's
Modulus
Es = Young's modulus of skin
ts
= thickness of skin
to = core thickness
b
d = tc + 2.ts/2 = tc+ts
Density
(Mg.m-³)
1.8
0.2
tcd h
= panel width = 600mm
W = 1500N,
Span, L = 1.20m
Shear modulus of core material, Gc= 50MPa
(GPa)
10
i. Calculate the mid-span deflections, of a panel with 40mm core thickness,
constructed with 2.0mm thick sheet moulding compound (SMC) skins.
![ii. Using the data from part i, calculate the overall mass of a 1.2m long x
0.6m wide sandwich panel made with SMC skins.[10.944kg]
iii. Calculate the maximum bending stress in the skin and the shear stress in
the core for a panel made with SMC skins.
[9.35 MPa and 0.03 MPa, respectively]
The expression for bending stress, σs, is:
Mh
bt d²
=
Os
where M = applied bending moment
h = overall panel thickness
The expression for shear stress, tc, is:
Q
bd
where Q = shear force.
Tc
=](/v2/_next/image?url=https%3A%2F%2Fcontent.bartleby.com%2Fqna-images%2Fquestion%2F27ae1c65-6d36-429b-9d72-b207dc1611cc%2Fc123b563-45f3-4d81-9814-7240baf662dd%2Fyo6gjp_processed.png&w=3840&q=75)
Transcribed Image Text:ii. Using the data from part i, calculate the overall mass of a 1.2m long x
0.6m wide sandwich panel made with SMC skins.[10.944kg]
iii. Calculate the maximum bending stress in the skin and the shear stress in
the core for a panel made with SMC skins.
[9.35 MPa and 0.03 MPa, respectively]
The expression for bending stress, σs, is:
Mh
bt d²
=
Os
where M = applied bending moment
h = overall panel thickness
The expression for shear stress, tc, is:
Q
bd
where Q = shear force.
Tc
=
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