Design and analysis for development of a wing box static test rig

Abstract

Airplanes are designed to stay aloft with the help of wings on both sides. In operation at cruising speed, the wings are subjected to load as much as the weight of the whole aircraft. However during maneuver, the wings are subjected much higher load and stress and this stress should be sustained by the wings within its limit load without causing permanent deformation to the structure. In order to assess how much stress the wings are subjected to, the wings should be tested on ground which is called static test. To proof that a design is good, a numerical analysis should be verified by experimental analysis. The static test can be done in a test rig. The test rig however should be much stronger than the object to be tested. Therefore, in this paper the design parameter such design configuration, is one of the parameters to be studied in the development of the test rig. In this paper, a finite element analysis was done on the 2D model of the test rig in order to verify the parametric design. Using ANSYS Workbench V12.1, an alteration was made to compare if the initial design was good or can be made better.