A non-contact aircraft landing impact test spatial attitude and deformation measurement and analysis method

This paper designs the system structure to meet the impact test of aircraft landing, and utilizes finite element calculation to derive the maximum impact stress of the impact platform and the maximum bearing stress.Analyze the attitude combination measurement system, based on the coordinate transformation theory to build a digital level, attitude probe and inclination sensor combination of attitude measurement model, the horizontal attitude angle of the object to solve the calculation.And the robustness overall least squares method is applied for plane fitting.The overall flow of the attitude measurement experiment is designed to analyze the stability and accuracy of the spatial attitude measurement system based on the combination of multi-sensors, and analyze the measurement error of the measured target in different states (translation or deflection).Different attitude solving algorithms are used to measure the attitude angle of the dynamic simulation experiment, and the measurement errors of the roll angle, pitch angle, heading angle and the root-mean-square error are compared.The RMS errors of the roll angle, pitch angle and heading angle measured by the attitude solution model in this paper are 0.2982, 0.2214 and 1.0333, respectively.Comparing with the data in the charts and graphs, it can be seen that the measurement errors and RMS errors of the attitude solution algorithm used in this paper are smaller, which are more in line with the requirements of the target spatial attitude measurement.