Safe fatigue crack for landing gear structures F/H

Job description

Traditionally, landing gear are safe life structures with no crack initiation or propagation allowed during the full life cycles of the aircraft. This is not the case for many other “fail-safe” aircraft components such as wing and fuselage skins or engines and exhausts parts. Here, cracks are monitored by (in-shop and in-service) inspections routines supported by qualified design repair processes. In addition, damage tolerance methods & tools are used to demonstrate that the crack initiation and growth remain safe for the structural integrity of the parts.

The objective of the internship work is to develop a methodology for assessing safe fatigue crack growth on landing gears. The proposed work will involve identifying the gear parts and locations where fail-safe criteria/philosophy can be applied. Fatigue crack growth analyses will be performed by using ABAQUS/Ansys-Zset/DARWIN/NASGRO solvers. Geometry factors and stress intensity factors will be computed, initially, for standard crack types.

The obtained data will be compared to that of industry standard finite element software (Abaqus, Ansys, …). Then, the fatigue crack growth of some selected landing gear parts will be analyzed and discussed. Mathématiques / fissuration / Simulations / Codage Elève-ingénieur pour un stage de fin d'études (grande) école