The STRESS ANALYSIS AND FATIGUE DAMAGE ESTIMATION FOR SEAT SUPPORT ATTACHMENT

Abstract

Aircraft structure is the most obvious example where structural efficiency results in light weight and high operating stresses. Airframe experiences variable loading in service. The paper presents the response of fuselage seat attachment due to cabin pressure and fluctuating load on seat attachment. The stresses developed in the fuselage at the altitude during actual flight condition were simulated by using the FEA software MSC.PATRAN & MSC.NASTRAN. The response of structure for the hoop stress and longitudinal stress developed in the fuselage due to cabin pressurization is studied by using finite element analysis technique. Linear static stress analysis is carried out for the identification of the fatigue critical location. The global and local analysis is carried out. Miner’s rule will be used for fatigue damage calculation with the help of the S-N diagram of the respective material used in the structure.