Gust and landing impacts as critical load cases for wings with distributed propulsion

Abstract The integration of distributed electric propulsion and energy storage systems into the wing structure significantly affects mass distribution wing. Compared with conventional aircraft which are designed engines mounted on inner integral fuel tanks, this substantially changes overall loads structure. Assuming a retrofit scenario, paper studies influence transient gust landing impact dynamic behavior structural integrity representative 19-seater commuter CS-23 category retrofitted propulsion. Modal response analyses conducted based beam model idealizing box three designs: reference one main turboprop engine per half-wing, two wings integrated results show for both load cases that section obtained by analysis exceed those predicted equivalent quasi-static calculations. wing, significant increase amplitudes plunge twist deformation consequently higher stresses observed designs. It is concluded critical regard to However, case more than case. These conclusions suggest sizing in particular propulsion, impacts, commonly applied should be accompanied analyses.