Question

The wing of a fighter aircraft, carrying a missile at its tip, as shown in Figure 1, can be approximated as an equivalent cantilever beam with EI 15 X 10 N-m about the vertical axis and length L 10m The equivalent mass of the wing, including the mass of the missile and its carriage system, at the tip of the wing is m-2,500 kg. Assume a damper coefficient of 20,000 N-m /s. The load is modeled as shown in Figure 2, where the maximum force is 1,000 N, occurring at the beginning of the 0.1 seconds pulse (linear variation). Determine the following: a) Fundamental natural frequency and fundamental natural period b) Calculate the displacement, velocity, and acceleration of the wing (the mass m) due to the release of the missile for the following time steps as shown in Table 1 for the corresponding initial conditions shown in Table 2. Present all your calculations made by hand and using a calculator. Do not use any computer program or MATLAB. Use five decimal places and scientific notation for each value of Table 1 Bending axis Figure 1. Fighter aircraft real system

Answer 1

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