Fatigue strength estimates for composite wing panels of prospective supersonic transport aircraft

The results of fatigue strength estimates, required for ensuring durability design goal of composite materials made upper and lower panels of the prospective supersonic transport aircraft (PSTA) wing are presented. Developed estimates of the fatigue properties are based on the approximations gained from published sources. Fatigue strength (S–N) equations for composite panels of the PSTA wing are deduced, which might be followed by procedure of compliance to service design goal. The methods developed are used to compare intact and required fatigue strength of original carbon fiber reinforced plastic (CFRP) and one with modified properties by nanoparticles inclusion. Finally, the sensitivity of the developed fatigue strength estimates to chosen parameters is studied. Developed methodology can be utilized during preliminary strength analysis of the PSTA wing panels.