DAMAGE REPAIR ANALYSIS FOR INTEGRAL WING PANEL OF AN AIRCRAFT

On the basis of thefinite element model of a whole aircraft, the paper simulates a crackwith a length of 150mm in a place betweenNo.2 and No.3 walls of the upper wing panel before and after it isrepaired. The results give a quantitativerelationship between rivet rows and residual load factor, and theinfluences of the damaged stringer, before and after it is repaired, on theforce-bearing ability of aircraft structure are compared. The resultscan be used in a rapid assessment of a battle-damaged aircraft repairand as a reference for the usual repair of aircraft.