| With the deepening of deep space exploration,people’s demand for more high precision,larger-caliber satellite antennas is becoming more and more urgent.This paper takes the basic configuration unit supporting the antenna as the design origin,completes the configuration scheme design and modular expansion design,analyzes the kinematics and dynamics of the mechanism scheme,optimizes the relevant structural parameters of the mechanism,and realizes the complete mechanism structure.The mechanism’s deployment function is verified through experiments.With modular expansion as the core and geometric unit configuration as the basis,this paper proposes three different configuration unit schemes.Taking this as the object of analysis,the specific frequency and specific stiffness indexes were established,and a reasonable configuration unit is selected.Based on the deployment function requirements of the antenna mechanism,the motion pair is configured on the configuration unit to complete the design of the configuration scheme and the design of the modular expansion scheme.After obtaining the configuration of the mechanism,this article focuses on the kinematics and dynamics analysis of the mechanism.The kinematics of the mechanism expresses the smooth deployment of the mechanism while the dynamics of the mechanism expresses whether the deployment process of the mechanism is stable.This article shows that the degree of freedom of the mechanism has been calculated,and the number and position of the drive arrangement of the mechanism have been determined.At the same time,a variety of driving schemes are proposed.In the process of kinematics analysis,by analyzing the displacement,speed and acceleration curves of the mechanism,a suitable driving scheme was optimized,and the kinematics simulation of the mechanism was carried out using ADAMS.As for dynamics of the mechanism,this paper solves the problem of the movement sequence and speed matching of the mechanism through ADAMS.Finally,the drive scheme of the mechanism is determined.In this paper,a modal analysis is carried out on the unfolded state of the mechanism.In order to ensure that the mechanism have better performance after deployment,this paper optimizes the structure parameters of the mechanism.Through sensitivity analysis and response surface fitting,the influence of different types of rod section parameters on mechanism performance is obtained.Finally,the optimization goal is determined,the optimization function is clarified,and the optimization solution of the structural parameters is obtained.The above institutional and structural design work laid the foundation for the subsequent institutional design.In this paper,the drive module,linkage mechanism,locking mechanism,positioning mechanism and various hinge mechanisms of the mechanism are designed in detail,and a scaled down model is made.Using this scaled-down model,this paper has completed the verification test of the unfolding function principle of the spatial triangular prism deployable planar antenna mechanism,and demonstrated the feasibility of the mechanism from the perspective of the function principle.Finally,this paper uses the spin theory to model the single-module single-loop mechanism,and introduces the rod length error and hinge gap error.The closed-loop mechanism is disassembled into multiple kinematic chains,and the single-module singleloop precision model of the mechanism is obtained by using Rodrigues method and other mathematical methods.With the aid of this model for accuracy analysis,the influence of different rod length errors and hinge gap errors on the accuracy of the mechanism is obtained. |
