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Consider a simple model of an airplane wing given in figure below. The wing is approximated as vibrating back and forth in its plane and is massless compared to the missile carriage system (of mass m). The modulus and the moment of inertia of the wing are approximated by E and I, respectively, and / is the length of the wing. The wing is modeled as a simple cantilever for the purpose of estimating the vibration resulting from the release of the missile, which is approximated by the impulse function Fa), Calculate the response and plot your results for the

Consider a simple model of an airplane wing given in figure below. The wing is approximated as vibrating back and forth in its plane and is massless compared to the missile carriage system (of mass m). The modulus and the moment of inertia of the wing are approximated by E and I, respectively, and / is the length of the wing. The wing is modeled as a simple cantilever for the purpose of estimating the vibration resulting from the release of the missile, which is approximated by the impulse function Fa), Calculate the response and plot your results for the

Elements Of Electromagnetics
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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Consider a simple model of an airplane wing given in figure below. The wing is approximated as vibrating back and forth in its plane and is massless compared to the missile carriage system (of mass m). The modulus and the moment of inertia of the wing are approximated by E and I, respectively, and / is the length of the wing. The wing is modeled as a simple cantilever for the purpose of estimating the vibration resulting from the release of the missile, which is approximated by the impulse function FO), Calculate the response and plot your results for the case of an aluminum wing 2-m long with m=1000 kg, z-0.01, and I-0.5 m'. Model F as 1000 N lasting for 10 s. Bp view At with miss (a) (b) Flay Simplified beam mdel Vilration modd Need detailed solutions for these question 8.png 4.png Submit th.
Transcribed Image Text:Consider a simple model of an airplane wing given in figure below. The wing is approximated as vibrating back and forth in its plane and is massless compared to the missile carriage system (of mass m). The modulus and the moment of inertia of the wing are approximated by E and I, respectively, and / is the length of the wing. The wing is modeled as a simple cantilever for the purpose of estimating the vibration resulting from the release of the missile, which is approximated by the impulse function FO), Calculate the response and plot your results for the case of an aluminum wing 2-m long with m=1000 kg, z-0.01, and I-0.5 m'. Model F as 1000 N lasting for 10 s. Bp view At with miss (a) (b) Flay Simplified beam mdel Vilration modd Need detailed solutions for these question 8.png 4.png Submit th.
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