Consider a simple model of an airplane wing given in the figure. The wing is approximated as vibrating back and forth in its plane, massless compared to the missile carriage system (of mass m). The modulus and moment of inertia of the wing are approximated by E and I, respectively, and L 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 apprroximated by the impulse function FS(t). Calculate the response and plot your results for the case of an aluminum wing 4 m long with m=1000 kg, z=0.01, and I=0.5 m^4. Model F as 1000 N lasting over 10^-2 s.

Consider a simple model of an airplane wing given in the figure. The wing is approximated as vibrating back and forth in its plane, massless compared to the missile carriage system (of mass m). The modulus and moment of inertia of the wing are approximated by E and I, respectively, and L 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 apprroximated by the impulse function FS(t). Calculate the response and plot your results for the case of an aluminum wing 4 m long with m=1000 kg, z=0.01, and I=0.5 m^4. Model F as 1000 N lasting over 10^-2 s.

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Consider a simple model of an airplane wing given in the figure. The wing is approximated as vibrating back and forth in its plane, massless compared to the missile carriage system (of mass m). The modulus and moment of inertia of the wing are approximated by E and I, respectively, and L 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 apprroximated by the impulse function FS(t). Calculate the response and plot your results for the case of an aluminum wing 4 m long with m=1000 kg, z=0.01, and I=0.5 m^4. Model F as 1000 N lasting over 10^-2 s.

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