Question
In: Mechanical Engineering
1. Find a picture on the internet that shows the underlying structure of an aircraft wing...
1. Find a picture on the internet that shows the underlying structure of an aircraft wing and discuss how it is similar to the box beam concept.
2.The box beam concept handles bending and torsional loads. Consider and discuss what structural elements we have explored so far in this course that address these loads. Hint: there are two (one for bending and one for torsion). Also, please include the following in the discussion.
Depending on the air vehicle performance requirements a wing’s thickness is different. For example, a lower speed vehicle such as a large transport aircraft (e.g., B-747) will have a thicker wing compared to a fighter aircraft. The reasons for this are beyond the scope of this course.
Consider the I-beam concept we have been exploring in this module. Discuss what happens as the wing thickness changes. For example, what is the variable in the bending equation that is effected as the wing thickness changes?
How could the allowable stress level be managed for the different wing structures (i.e., what happens to the skin thickness, which is the upper part of the box beam)?
Solutions
samet mamat answered 2 years agoRelated Solutions
Draw a sectional diagram of an aircraft wing, showing the structure of the wing and the...
Draw a sectional diagram of an aircraft wing, showing the
structure of the wing and the control surfaces. Then detail the
most appropriate materials used for each of the main parts,
mentioning at least 2 metals, 1 CFC composite, and 1 sandwich
material and expalin why each is used in that application, with
reference to the properties required to withstand the forces
involved.
Delta Wing Aircraft Specifications (do the necessary assumptions if needed) Wing Area: 585 m2 Wing Span:...
Delta Wing Aircraft Specifications
(do the necessary assumptions if needed)
Wing Area: 585 m2
Wing Span: 32 m
Taper ratio: 0.019
Leading Edge Sweep angle: 65.57°
Wing loading: 4070 N/m2
Cruise Mach Number: 3
Cruise altitude: 22.5 km
(L/D) cruise = (L/D) max = 9
Calculate the cruising angle of attack?
Write down the cruising drag polar equation?
Using the drag polar found in (b), calculate
(CL1/2/CD) max and
corresponding Mach number maximizing
(CL1/2/CD).
If a strain gage is placed in the wing of an aircraft where the temperature drops...
If a strain gage is placed in the wing of an aircraft where the
temperature drops by 50 degrees F in flight. How do you configure
the bridge to compensate for the resulting error?
An aircraft firm is considering three different alloys for use in the wing construction of a...
An aircraft firm is considering three different alloys for use
in the wing construction of a new airplane. Each alloy can be
produced in four different thicknesses (1 = thinnest, 4 =
thickest). Two test samples are constructed for each combination of
alloy type and thickness, then each of the 24 test samples is
subjected to a laboratory device the severely flexes it until
failure occurs. For each test sample the number of flexes before
failure is recorded, with the...
An aircraft firm is considering three different alloys for use in the wing construction of a...
An aircraft firm is considering three different alloys for use
in the wing construction of a new airplane. Each alloy can be
produced in four different thicknesses (1 = thinnest, 4 =
thickest). Two test samples are constructed for each combination of
alloy type and thickness, then each of the 24 test samples is
subjected to a laboratory device the severely flexes it until
failure occurs. For each test sample the number of flexes before
failure is recorded, with the...
A model aircraft in a wind tunnel with a wing area of 0.9 square meters and...
A model aircraft in a wind tunnel with a wing area of 0.9 square
meters and a chord of .24 meters is subject to a sea level standard
airflow at 130 m/sec. The zero-lift moment about the
center-of-gravity is measured as – 7.8 N m. At a different angle of
attack, the moment about the center-of-gravity is measured as 13.5
N m with a lift of 2,650 N.
(A)Calculate the value of the moment coefficient about the
aerodynamic center, and...
A wing component on an aircraft is fabricated from an aluminum alloy that has a plane...
A wing component on an aircraft is fabricated from an aluminum
alloy that has a plane strain fracture toughness of 30 MPa (m) 1/2
. It has been determined that fracture results at a stress of 120
MPa when the maximum internal crack length is 8.4 mm. For this same
component and alloy,
Compute the stress level at which fracture will occur for a
critical internal crack length of 5.6 mm?
Describe the structure and function of wing coupling mechanisms in insects.
Describe the structure and function of wing coupling mechanisms
in insects.
When commercial aircraft are inspected, wing cracks are reported as nonexistent, detectable, or critical. The history...
When commercial aircraft are inspected, wing cracks are reported
as nonexistent, detectable, or critical. The history of a
particular fleet indicates that 70% of the planes inspected have no
wing cracks, 25% have detectable wing cracks, and 5% have critical
wing cracks. Five planes are randomly selected.
(a) Find the probability that one has a critical crack, two have
detectable cracks, and two have no cracks.
(b) Find the probability that at least one plane has critical
cracks.
(c) Find...
Two processes are used to produce forgings used in an aircraft wing assembly. Of 200 forgings...
Two processes are used to produce forgings used in an aircraft
wing assembly. Of 200 forgings selected from process 1, 10 do not
conform to the strength specifications, whereas of 300 forgings
selected from process 2, 20 are nonconforming. Test the hypothesis
that the two processes have identical fractions nonconforming. Use
? = 0.05. State your hypothesis and test statistic.
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