The wing of a fighter aircraft, carrying a missile at its tip, as shown in Fig. 4.57, can be approximated as an equivalent cantilever beam with \(E I=15 \times 10^{9} \mathrm{~N}-\mathrm{m}^{2}\) about the vertical axis and length \(l=10 \mathrm{~m}\). If the equivalent mass of the wing, including the mass of the missile and its carriage system, at the tip of the wing is \(m=2500 \mathrm{~kg}\), determine the vibration response of the wing (of \(m\) ) due to the release of the missile. Assume that the force on \(m\) due to the release of the missile can be approximated as an impulse function of magnitude \(F=50 \mathrm{~N}\)-s.

Figure 4.57:-

Transcribed Image Text:

Bending axis (a) Real system FIGURE 4.57 Motion of fighter aircraft wing.