Consider an airplane wing with a fuel pod mounted at its tip as illustrated in Figure 1. The pod has a mass of 10 kg when it is empty and 1000 kg when it is full. Calculate the change in the natural frequency of vibration of the wing, modeled as in Figure 1, as the airplane uses up the fuel in the wing pod. The estimated physical parameters of the beam are I = X.Y x 105 m², E = Y.Z x 10° N/m², and 1= 2 m Vertical wing vibration E,I Figure 1: Airplane wing. (a) Formulate the equation of motion of the airplane wing. (b) Express the total solution of the airplane wing. (c) Compute the natural frequency of the airplane wing. E x(1) x(0) (d) Identify the type of vibration suppression and the transducer for measuring the vibration effect.
Consider an airplane wing with a fuel pod mounted at its tip as illustrated in Figure 1. The pod has a mass of 10 kg when it is empty and 1000 kg when it is full. Calculate the change in the natural frequency of vibration of the wing, modeled as in Figure 1, as the airplane uses up the fuel in the wing pod. The estimated physical parameters of the beam are I = X.Y x 105 m², E = Y.Z x 10° N/m², and 1= 2 m Vertical wing vibration E,I Figure 1: Airplane wing. (a) Formulate the equation of motion of the airplane wing. (b) Express the total solution of the airplane wing. (c) Compute the natural frequency of the airplane wing. E x(1) x(0) (d) Identify the type of vibration suppression and the transducer for measuring the vibration effect.
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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Question
Let XYZ = 728
Transcribed Image Text:Consider an airplane wing with a fuel pod mounted at its tip as illustrated in Figure 1.
The pod has a mass of 10 kg when it is empty and 1000 kg when it is full. Calculate
the change in the natural frequency of vibration of the wing, modeled as in Figure 1,
as the airplane uses up the fuel in the wing pod. The estimated physical parameters of
the beam are I = X. Y x 10-5 m², E = Y.Zx 10° N/m², and 1= 2 m
Vertical wing vibration
E,I
1
Figure 1: Airplane wing.
(a) Formulate the equation of motion of the airplane wing.
(b) Express the total solution of the airplane wing.
(c) Compute the natural frequency of the airplane wing.
m
x(1)
x(0)
(d) Identify the type of vibration suppression and the transducer for measuring the
vibration effect.
*Important notes: the value of XYZ is obtained from the last 3 digits of your matric
number.
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