Analysis Of The Structure And Motion Characteristics Of A Space Deployable Solar Wing Based On Linear Drive

With the rapid development of aeronautics and astronautics technology,different kinds of artificial satellites with various functions play an important role,such as communication navigation,scientific detection,weather forecast and so on.As an important energy supply equipment of the satellite,the deployable solar wing,which is used to provide energy guarantee for the continuous work of the satellite,must ensure two stable states named contraction/deployment during the launch.In this paper,a new type of spacial deployable solar wing mechanism is proposed by combining the kite-shaped straight-line mechanism and origami mechanism,and the following related research is carried out:Based on the particularity of the shape and size of kites,a special seven bar mechanism of kite-shaped is designed by using abstract thinking.Firstly,the geometry proof method is used to verify the correctness of the designed kite-shaped seven bar mechanism,which lays a foundation for further research.Secondly,by introducing the parallel constraint,we can design many kinds of single DOF kite-shaped straight-line mechanisms,and construct the developable unit based on the kite-shaped straight-line mechanism.The principle and process of modular composition of kite-shaped straight-line developable mechanism are described,which provides a variety of configuration forms for its practical engineering application.Finally,on the basis of kinematic analysis of kite-shaped deployable mechanism,the whole dynamic equation of the mechanism is established by Lagrange method,and compared with the dynamic simulation results of virtual prototype of mechanism built by Solid Works,the correctness of the dynamic equation is verified,which lays a theoretical foundation for the practical engineering application of kite-shaped straight-line mechanism.A new type of spatial deployable mechanism is abstracted from the origami method proposed by Miura K Professor.On the basis of modular analysis,according to the geometric characteristics of motion and face symmetry,the virtual model of the whole spatial deployable mechanism is established after it is driven by the kite-shaped mechanism between fold and unfold states.And any four plates of origami mechanism are taken as a module to study the kinematic characteristics.The kinematic equation of the unit module is established by using the spatial coordinate transformationmethod.On this basis,the kinematic characteristics,interference and expandability of the space deployable solar wing are studied respectively,which provides a theoretical basis for the in-depth study of the space solar wing mechanism.The technical route of the modal analysis of the space deployable solar wing mechanism is determined,and the virtual prototype model of the whole solar wing mechanism is established.The monomer modal of this mechanism is further extracted,which is imported into ANSYS-Workbench for union simulation and the analysis is carried out.By getting the natural frequency and modal parameters of the first 10 rigid body modes of the solar wing mechanism,the vibration of the model under theoretical simulation is obtained.