DAMAGE REPAIR ANALYSIS FOR INTEGRAL WING PANEL OF AN AIRCRAFT
某飞机机翼整体壁板损伤修理的有限元分析

On the basis of the finite element model of a whole aircraft, the paper simulates a crack with a length of 150 mm in a place between No.2 and No.3 walls of the upper wing panel before and after it is repaired. The results give a quantitative relationship between rivet rows and residual load factor, and the influences of the damaged stringer, before and after it is repaired, on the force-bearing ability of aircraft structure are compared. The results can be used in a rapid assessment of a battle-damaged aircraft repair and as a reference for the usual repair of aircraft.