Abstract:Strain electrical measuring method is one of the most commonly used methods in aircraft flight load test. The method of fiber reinforced laminated composite vertical tail load test was studied in this paper. Firstly, finite element model of composite vertical tail was established, and the surface strain distribution of vertical tail under uniform load was calculated. Secondly, according to the strain distribution of finite element simulation, strain gauges were placed and load test bridge were designed, which should avoid stress concentration area, calibration experiment should be carried out to measure the flight load of vertical tail. Finally, models of same ply number with different stacking sequence were stimulated, micromechanical study and comparison of the strain at the position of strain gauges was conducted to analysis the influence of stacking sequence on surface strain of composite structure. The results showed that the ply angle of surface composite layer had a great influence on strain test results. The stacking sequence of composite should be taken into account when testing the strain of composite structures, however, the influence could leave out of account during load testing experiment.