Figure 2 shows the flight envelope at sea-level for an aircraft of wing span 27.

Question

Figure 2 shows the flight envelope at sea-level for an aircraft of wing span 27.5 m, average wing chord 3.05 m and total weight 196,000 N. The aerodynamic center is 0.915 m forward of the CG and the center of lift for the tail unit is 16.7 m aft of the CG. The pitching moment coefficient is CM = 0.0638 (nose-up positive) Both CM and the position of the aerodynamic center are specified for the complete aircraft less tail unit. For steady cruising flight at sea level, the fuselage bending moment at the CG is 600,000 Nm. Calculate the maximum value of this bending moment for the given flight envelope. For this purpose, it may be assumed that the aerodynamic loadings on the fuselage itself can be neglected, that is, the only loads on the fuselage structure aft of the CG are those due to the tail lift and the inertia of the fuselage.

Explanation / Answer

the primary factors to consider in aircraft structures are strength weight and reliability. these factors determined the requirements to be met by any material used to construct or repair the aircraft. airframes must be strong and light in weight. an aircraft built so heavy that it coudnt support more than a few hundred pounds of additional weight would be useless. all materials used to construct an aircraft must be reliable. reliability minimizes th possibility of dangerous and unexpected failures. many forces and structural stresses act on an aircraft when it is flying and when it is static, the force of gravity produces weight, which is supported by the landing gear. the landing gear absorbs the forces imposed on the aircraft by takeoffs and landing.

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