Design of the mirror antenna of a spacecraft with the ultralight high precision size-stable reflector

The paper discusses the existing design of mirror antennas used on spacecraft. The requirements are formulated under which the reliable performance of antennas is ensured under operating conditions. Innovative construction of the space high frequency axisymmetric mirror antenna of an ultralight class is presented. Antenna’s body consists of several conjugate carbon fiber shells. Antenna’s design technology which gives an opportunity to create the shell of a reflector with minimal deflection from a full-paraboloid is developed. Using the finite element method, a parametric modal analysis of the antenna is performed. Based on this analysis, geometric parameters were determined that provide optimal mechanical and mass characteristics of the structure. The calculation results were used to create a prototype mirror antenna. It is shown that the created antenna possesses the parameters required for generation of the high-directional electromagnetic emission of Q and V frequency domain. Successful ground experimental perfection of the construction of the antenna is made. It included the stages of mechanical, thermal vacuum, and radio engineering tests. The proposed design can be used to create advanced spacecraft.