Assembly deviation analysis of satellite flexible parts integrating rigid and flexible properties: Modeling and experiment

Abstract

With the advancement of space technology, satellites are assuming an increasingly pivotal role in various fields. Currently, satellite structures incorporate a growing number of thin-walled parts. During the assembly process, the movement and connection of these parts are prone to generating assembly deviations, which seriously affects the overall assembly quality of the satellites. In order to accurately predict assembly deviations before assembly, this paper introduced an assembly deviation analysis model which took rigid and flexible properties into account. Starting from the attitude adjustment of satellite assembly, the transmission law of manufacturing error was established. Then, the assembly deviation analysis model integrating rigid and flexible properties was established. Finally, the assembly experiment was carried out to verify the effectiveness of the proposed model. The results showed that the average absolute error between the measurement results and calculation results was only 0.032 mm and the maximum absolute error was 0.074 mm. The average solving accuracy of the assembly deviation was 94%. The result fully proved the effectiveness of the proposed model.