The aircraft shown in Fig. 13.6 has a moment of inertia of 5,460 kNs^2m and an all-up weight of 430 kN. During landing the aerodynamic lift is equal to 90 percent of its all-up weight and it is subjected to the ground loads shown. Determine (a) the limit load factor at its center of gravity, (b)

Question

The aircraft shown in Fig. 13.6 has a moment of inertia of 5,460 [latex]kNs ^{2} m[/latex] and an all-up weight of 430 kN. During landing the aerodynamic lift is equal to 90 percent of its all-up weight and it is subjected to the ground loads shown. Determine (a) the limit load factor at its center of gravity, (b) the limit pitching acceleration.

Accepted Answer

(a) Wing lift [latex]=0.9 imes 430=387 kN[/latex]. Resolving vertically, the total vertical load on the aircraft [latex]=387+1,112.5 - 430= 1,069.5 kN.[/latex] Therefore the limit load factor [latex]=(1,069.5 / 430)+1=3.5[/latex]

(b) Taking moments about the CG,

[latex]3.81 L_{W}+222.5 imes 2.54+1,112.5 imes 2.54=I_{ O } \alpha=5460 \alpha[/latex]

from which

[latex]\alpha=0.89 rad / s ^{2}[/latex]

Question 13.3: The aircraft shown in Fig. 13.6 has a moment of inertia of 5...

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