In order to meet the requirements of high precision and light weight of reflectors in the field of satellite communications

the ABAQUS finite element was used to simulate the thermal deformation of the composite reflector and the RMS value of the profile accuracy was calculated by the least squares against the background of a geosynchronous orbit meteorological satellite reflector. The full composite grid reflector structure was designed by using the in-plane thermal expansion coefficient of the M55 carbon fiber composite laminate. Under the same working conditions

the industrial three-dimensional measurement method was used to test the thermal deformation of the grid reflector structure and the root mean square RMS value of the deformation of the working face was used to characterize the profile accuracy. It shows that the test value was approximately equal to the simulated value. Finally

factors affecting the RMS value of the profile accuracy were analyzed

such as assembly error

bonding method

thickness of glue layer

layup angle of skin and ribs. Results show that the bonding method and the thickness of the glue layer were the most important factors affecting the profile accuracy of the full composite grid reflector

and point bonding was more suitable for the bonding of the skin and the grid structure. At the same time

with the increase of the thickness of the glue layer and the assembly error

the profile accuracy showed a nonlinear growth trend. Compared with the carbon fiber aluminum honeycomb sandwich structure reflector

the profile accuracy of the full composite grid structure reflector was only 0.455 μm under the same working conditions and the same macroscopic structure size

which was increased by an order of magnitude. It provides a reliable design for high precision deep space exploration and signal transmission.