Design And Optimization Of Deployable Array Based On Thick Panel Kirigami

The space deployable mechanism is widely used in solar panels,space truss and satellite antenna.Due to the size limitation of space rockets,this kind of mechanism is in the collapse status during launch and be deployed to the working position after entering the space.Therefore,the deployable structure has been attracted more and more attention from researchers with the rapid development of aerospace field.In this paper,a new kind of thick panel kirigami deployable structure has been proposed based on the perspective of the new type deployable structure.Then,the kinematic model,the curve-shape deployable array and the mathematical model to optimize the structure parameters proposed.These researches have provided a new idea and beneficial supplement for the development of new type deployable structure.The main research results are as follows:Firstly,the thick panel kirigami deployable structure has been proposed based on the kirigami folding method and thick panel origami deployable structure.The kinematic model of its equivalent linkage has been built by the Denavit-Hartenberg parameter method,and we demonstrate that the kinematic behaviors of a rigid zerothickness kirigami and its corresponding thick panel model are the same through kinematic analysis.In addition,this study proposed a thickness design method for thick panel kirigami model,by which we built several special cases.Three kinds of thick panel kirigami deployable arrays based on the special cases of the thick panel kirigami model have been proposed.The kinematic analysis for the symmetry thick panel kirigami model have been given by Denavit-Hartenberg parameter method.In addition,the method of degree of freedom analysis for the equivalent linkage assembly has been proposed by screw theory,which proves the single degree of freedom of the thick panel kirigami deployable array.The thick panel kirigami deployable array has been constructed based on the symmetry thick panel kirigami model,and the corresponding geometric,structure and kinematic parameters have been defined.On this basis,the mathematical model of the thick panel kirigami deployable array is established,and the deploy ratio and residual are defined to analyze the influence of the geometric,structure and kinematic parameters on the special aim curve.The design flow has been proposed to design the special curve shape deployable structure and obtain the design parameters.Finally,the basic folding unit of the symmetry thick panel kirigami model have been constructed by considering the aerospace flexible hinge Tape-spring,and the experimental results are obtained by the test are in agreement with the theoretical results.In addition,a parabolic cylindrical solid surface deployable antenna has been built based on the design process of the special curve shape thick panel kirigami deployable structure.The prototype is fabricated by means of 3D printing,the rotation hinges are installed to accomplish the folding process,and the experimental results show that the prototype surface satisfies the aim curve.This paper has provided valuable reference for the development of new type of deployable structure.