Design And Shape Control Method Of Deployable Rigid Rib Mesh Reflector Antenna

As the requirements for the aperture of the antenna gradually become larger,the expandable mesh antenna with light weight,high storage ratio,and large size structure,has gradually become the first choice.The rigid rib expandable mesh antenna has the characteristics of simple form,stable structure and high deployment reliability.It is one of the main forms of antennas used in orbiting satellites in the world,and domestic research on such antennas is still less.In this paper,the radial ribbed mesh antenna is deeply studied,and it is mainly analyzed from the following aspects:First of all,this paper proposes a structural design scheme for a radial ribbed mesh antenna.Referring to the structural form of the surrounding truss type mesh antenna,a radial rib type mesh antenna composed of a radial rib,a reflective surface mesh and a back tension mesh system is designed.The mesh of the reflective surface cable and the back mesh is designed by the method of minimum root mean square value.Considering the particularity of the boundary conditions of the radial ribbed mesh antenna,the boundary cable system is designed to ensure the structure of the mesh.Uniform force.In order to stabilize the node of the mesh antenna in the design position,this paper studies the pre-tightening force design method of the radial rib mesh antenna based on the minimal norm method,and combines the variable interval stepwise search method with the constraint.The optimization method finds a set of feasible solutions that enable the antenna to maintain its mechanical stability.Due to the lack of symmetry of the reflective rib net and the back mesh of the radial ribbed mesh antenna,the design result is not ideal.Therefore,the hybrid seek force analysis method is used to re-plan the nodes of the back cable of the antenna,according to the nonlinear programming method.Solve the antenna back mesh configuration and the most uniform set of cable forces that keep the antenna stable.Because the mesh structure has the characteristics of geometric nonlinearity and constitutive nonlinearity of different modulus of tension and compression,this paper combines the parametric variable principle and uses the two-node isoparametric element method to model the finite element of the mesh antenna.The problem of mesh relaxation analysis.When the mesh antenna is in orbit,it will be interfered by many external environmental factors.The huge temperature difference will seriously affect the profile accuracy of the antenna's reflective surface.In this paper,based on the space system thermal module,the in-orbit thermodynamic analysis of the mesh antenna is carried out.Combined with the finite element algorithm,the characteristics of the thermal load variation of the mesh antenna structure during the orbit operation and its structure to the mesh are analyzed influences.In order to ensure that the antenna is in the orbital operation process,it can maintain the high accuracy of the cable surface of the mesh under the influence of many external environmental factors.This paper proposes an active MFC actuator on the lower surface of the radial rib.Control plan.By adjusting the driving voltage of the actuator to control the deformation of the radial rib structure of the mesh antenna,the precision of the control surface of the mesh is controlled.The influence coefficient matrix method is used to establish the active control optimization model of the mesh antenna reflection surface with the minimum mean square error.The optimal control law for solving the actuator driving voltage is designed by the constrained linear programming method.The feasibility of an active control scheme based on MFC actuators is further verified.