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agasfer [191]
3 years ago
12

What are some aircraft aging problems? How can you as an Aviation Maintenance Manager monitor problems that relate to aircraft f

atigue? What are some techniques to prolong the lifespan of aircraft? Which section in an airline organization is responsible for reducing aircraft fatigue? Please be specific with your response and share examples as appropriate.
Engineering
1 answer:
julia-pushkina [17]3 years ago
4 0

Answer:

Answered

Explanation:

The two key processes that lead to aircraft ageing are fatigue and corrosion. These processes generally affect the aircraft structure, but can also affect wiring, flight controls, power plants, and other components. Fatigue and corrosion can work independently from one another, or they can interact. The interaction between fatigue and corrosion can increase the rate of ageing to a greater extent than that due to either process alone.

Fatigue predominately takes place in metal components, but it can also affect non-metallic materials. Fatigue occurs through cyclic loading patterns, where a component is repeatedly loaded. Bending a metal paper clip backwards and forwards is an example of fatigue; the paper clip will not break if only bent once, however, if it is repeatedly loaded, it will eventually break. Fatigue failures will often take place at loads much lower than the materials ultimate strength.

Generally, the initiation point for fatigue will be a microscopic crack that forms at a location of high stress, such as a hole, notch, or material imperfection. The crack will then grow as loads are repeatedly applied. If not detected and treated, the crack will eventually grow to a critical size and failure will occur at loads well below the original strength of the material.

The relationship between repetitive loading and fatigue crack growth, creates a link between fatigue related ageing, the number of flight cycles, and the number of flight hours that an aircraft has accumulated.

Aircraft components that are susceptible to fatigue include most structural components such as the wings, the fuselage, and the engine.

During initial manufacturing the research department is responsible for designing the aircraft to withstand fatigue. During operations the fatigue risk management of aviation maintenance will try to rectify the problems due to fatigue.

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A well-insulated rigid vessel contains 3 kg of saturated liquid water at 40oC. The vessel also contains an electrical resistor t
user100 [1]

Answer:

The final temperature is 111.66°C

Explanation:

The given conditions :-

i) Well insulated means no heat loss.

ii) Rigid vessels means volume remains same.

iii) Initial temperature ( T₁ ) = 40°C. = 273 + 40 = 313 K

iv ) Mass of water in vessel = 3 kg.

v) current drawn by resistor ( i ) = 10 ampere.

vi) Voltage applied ( V ) = 50 volts.

vii) The time for which resistor operating ( t ) = 30 minute = 30 * 60 = 1800 seconds.

Now we have to calculate heat developed by resistor in vessel.

Q = V * i * t  = 50 * 10 * 1800 = 900,000 J = 900 KJ.

Since it is a rigid container so the work done is zero.

Q = du    ( du - change in internal energy)

Q = m * C * dT      ( C = 4.186 KJ/KgK )

Q = 3 * 4.186 * (T₂ - T₁ )

900 = 12.558 * ( T₂ - 313 )

T₂ - 313 = 71.6674

T₂ = 384.6674 K

T = 384.6674 - 273 = 111.66°C

So the final temperature is 111.66°C.

3 0
3 years ago
t is desired to produce aligned carbon fiber-epoxy matric composite having a longitudinal tensile strength of 800 MPa. Given (a)
Nesterboy [21]

Answer:

The value of critical length = 3.46 mm

The value of volume of fraction of fibers = 0.43

Explanation:

Given data

\sigma_{T} =  800 M pa

D = 0.017 mm

L = 2.3 mm

\sigma_{f} = 5500 M pa

\sigma_{m} = 18 M pa

\sigma_c = 13.5 M pa

(a) Critical fiber length is given by

L_{c} = \sigma_{f} (\frac{D}{2 \sigma_{c} } )

Put all the values in above equation we get

L_{c} =5500 (\frac{0.017}{(2) (13.5)} )

L_{c} = 3.46 mm

This is the value of critical length.

(b).Since this  critical length is greater than fiber length Than the volume fraction of fibers is given by

V_{f} = \frac{\sigma_T - \sigma_m}{\frac{L\sigma_c}{D} - \sigma_m }

Put all the values in above formula we get

V_{f} = \frac{800-18}{\frac{(2.3)(13.5)}{0.017} - 18 }

V_{f} = 0.43

This is the value of volume of fraction of fibers.

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Answer:

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