| Deployable solar arrays are the main power supply equipment of spacecraft,which are folded and fixed in the payload bay of the spacecraft before launch and can acquire the large working face when deployed in the working orbit.In this paper,a novel space deployable structure based on the mid-wing mechanism of the hind wing of the Earwig was designed and applied to the deployment of the solar arrays.The main works of this paper are:1.In order to reveal the function of the mid-wing mechanism of the hind wings in the deployment process,the morphological characteristics and deployment process mechanism of the Earwig’s hind wings was studied.Furthermore,inspired by the mid-wing mechanism,space four-bar linkages were designed and which were transformed into thick panels folding mechanism.2.Based on the new theoretical model of thick panel origami folding mechanism,the problem for the interaction between the thick panels during the deployment process was solved and a new type of thick panels folding mechanism was designed.3.The simulation analysis on rigid-flexible coupling dynamics model was carried out and the kinetic characteristic during deployment process was analyzed using ADAMS software.The simulation results reveal the vibration of the solar panel,which provides a reference for later structure optimization of the solar arrays.4.The modal characteristics of the solar arrays model under folding and unfolding two states were analyzed using ANSYS software to get their natural frequency and modal shapes.The results have shown that its first order frequency was 23.43 HZ,which was greater than the design value 0.3HZ.So,it can avoid resonance with the satellite body.5.The prototype of solar arrays was fabricated and the vibration test experiments(including natural frequencies and modal shapes)were performed.It was shown that the numerical simulation results coincided well with the test results.Finally,after analyzing and comparing various existing microgravity experimental platform,a novel suspending system was developed to compensate the gravity.The deployable performance was tested and the experiment results indicate that this prototype deployed smoothly. |
