The stiffness study of the electronic components and thin plate coupling system in
spacecraft is a key factor in understanding the mechanical properties and vibration
characteristics of such composite structures. A simplified model of an elastic circular
plate system with peripheral fixations was established for the circular plate composite
structure carrying cylindrical electronic components in spacecraft. The average
moment of inertia of different sections of the composite structure was solved, and
the formula for the bending stiffness of the system was derived based on
the relative proportions of these sections in the system. Based on elastic
thin plate theory, the analytical solutions of the center deflection of the
system with different parameters were calculated. By comparing the finite
element simulation results, the accuracy of the stiffness formula was verified. In
order to reflect the influence of each parameter on the system stiffness more
directly, the corresponding values of each parameter and the system stiffness
were fitted into mapping relationships, and the coefficients of the stiffness
formula of the circular plate was modified. The conclusion of this paper
is that it is important to study the mechanical properties and vibration
characteristics of space composite structures more accurately. The optimization
suggestions of the system are given from the two perspectives of physical
parameters and dimension parameters, which can provide a theoretical basis
and optimization scheme for the design and research of space composite
structures.
Keywords
spatial composite structure, bending stiffness, finite
element simulation, parameter optimization