Answer:
1. 142.1 GPa
2. 98.52%
Explanation:
1. The modulus of elasticity of carbon-epoxy composite is calculated using the following formula:
Ec = VmEm + VfEf
where Vm: volume of Epoxy
Em: modulus of the elasticity of the epoxy
Vf: volume of carbon fiber
Ef: modulus of the elasticity of the carbon fiber
Given that :
Vm = 0.6
Em = 3.5 GPa
Vf = 0.4
Ef: 350 Gpa
Therefore Ec = (0.6 × 3.5 GPa + (0.4 × 350 GPa)
Ec = 142.1 GPa
The modulus of elasticity of carbon-epoxy composite is 142.1 GPa
2. Percentage of load carried by the carbon fibers is given by the following equation: Ff/Fc = (Ef/Ec)×Vf
where Ff is the force carried by carbon fibers, Fc is the force applied to the composite, Ec is the modulus of elasticity of the composite, Ef is the modulus of the elasticity of the carbon fiber and Vf the volume of carbon fiber.
Given that:
EF = 350 Gpa
Ec = 142.1 GPa
Vf = 0.4
Substituting the above values into the equation:
Ff/Fc = (350 GPa/142.1 GPa)×0.4 = 0.9852 = 98.52%
The percentage of load carried by the carbon fibers is there 98.52%
Answer:
A) 88.42 ohms
c) 0.5145 and - 5.77 db
Explanation:
A) Value of cut-off frequency = 12 kHz
capacitance of capacitor =0.15 microF
formula for cut-off frequency of a low-pass filter
making R the subject of the formula in other to get the resistance of the low pass filter resistor
R = 
= 88.42 OHMS
attached is the solution for B and C
The answer is 1. Hopefully it helps!
Answer:
The additive drag at flight condition will be found by the following equation
Area = A1 = 6m2
Da = Additive drag
Cda = Additive drag coefficient
P = prassure at altitude of 12Km
Po = Prassure at sea level
\gamma = Ratio of specific heat capacity
The formula of additive drag is given below
D = Cda q A
q = Dynamic prassure , A = cross sectional area
q =( \gamma/ 2) P0 M02
D = Cda ( \gamma/2) po Mo2 A
Cda=0.32
\gamma=1.4
M=0.8
p0= 101325pa
D = 0.32 (1.4/2)(101325pa)(0.6)2 6
D = 49025N
Explanation:
The additive drag at the flight conditions will be D= 49025N
Answer:
B. 2.3mm
Explanation:
The correct answer for the given question is B. 2.3mm. Some aircraft are made are fabricated from aluminium which has plane stain fracture toughness. In the given scenario the plane stain toughness is
Ktc = 40 [ MPa 
]
When the Ktc increases the fracture will appear on the aircraft. In this case the maximum crack until the fracture failure is 2.5mm.
