抄録
Structural health monitoring (SHM) is an important technology for the next generation aerospace vehicles. The key issue is to determine the operational stress in real time which enables us to manage the structural integrity and air-worthiness. In our previous work, we reported a technique to identify distributed load, such as the aerodynamic load, using real time data provided by strain sensors. This technique is based on an inverse interpolation method using results from a Finite Element Model (FEM) analysis. In this work, features of this method and its behavior of solutions on the error in strain measurement were characterized by simulations based on FEM. In addition, the applicability to plate structures was verified by experiments.
