Dynamic simulation and application of deployable mechanism of satellite solar panels

The impact of a satellite panel deployment on satellite attitudes was researched and deployment strategies were optimized. A theoretical model for deployment of a single solar panel was established to obtain the analytical solution of the rotation angle changed with time. Combined with the practical application of a satellite project, the ADAMS dynamics of the single solar panel was simulated, and a new ADAMS model approximate to an actual situation and parameter settings were performed. Through deployment test of single solar panel deployment mechanism, the drive moment and resistance moment were obtained to correct the theoretical model and ADAMS model. The correction results show that the difference among theoretical calculation, simulation and test results is within 5%. For a 10.6 kg panel, deployment time has been shorten by 0.4-0.5 s and the impact load augmented about 400 N with each increase of 0.09 N·m of drive moment. The revised ADAMS model can be applied to deployment dynamic analysis of satellite panels and can obtain the effect of different deployment strategies on satellite attitudes. Obtained results provide credible references for selection of deployment patterns and precise controls.