- A The Wing Of A Four Engined Aircraft Is Modelled For The Purposes Of Analysing Its Bending Vibration As A Cantilever B 1 (69.77 KiB) Viewed 36 times
a) The wing of a four-engined aircraft is modelled for the purposes of analysing its bending vibration as a cantilever b
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a) The wing of a four-engined aircraft is modelled for the purposes of analysing its bending vibration as a cantilever b
a) The wing of a four-engined aircraft is modelled for the purposes of analysing its bending vibration as a cantilever beam of mass mw with two attached lumped masses m, and m2 (see Figure 3). The following data exists, E=71GPa, l=5x105m , lz=1m, lz=2m, m2=m2=1500kg, 1=4m, mw=200kg m m,E,1 m; oedoo 7777 1 Figure 3 Modelling an aircraft wing. Determine the equivalent mass of the system referred to the wing tip (i.e. if we replaced the system with an equivalent system consisting of a massless cantilevered beam with single lumped mass placed at the free end, what would be the value of meg?). 4marks b) For the aircraft in question a) above, find the natural frequency of bending vibration 4marks c) Say a reinforcing strut is added to the aircraft in question above, to stiffen the wing, as shown in Figure 4. The strut can be idealised as a cylindrical aluminium tube with E=71GPa, inner radius r1=78mm, outer radius ra=80mm, and length L=0.4m. The strut is attached to the wing 0.3m from the centre line of the aircraft Modelling this as a parallel spring to the wing, re calculate the natural frequency of vibration in bending:
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