抄録
A method is described that selects reflector modes in predicting the frequency of deployable satellite antennas in the deployed configuration. Deployable satellite antennas are modeled as a coupled system; the reflector (an elastic body) is supported by a mechanism (a coil spring). The displacement of the reflector in the system is expressed as the sum of the elastic displacement and the rigid-body displacement due to spring rotation. The system vibration equation is obtained by substituting kinetic and potential energies into Lagrange's Equation. Natural frequencies of deployable satellite antennas depend on a parameter that is calculated using elastic and rigid-body modes. This parameter represents the magnitude of the relative contribution of the i-th mode to overall structural behavior. Therefore, we can predict the frequency of deployable satellite antennas accurately by considering modes for which the parameter has a large value. A numerical example is given to show the effectiveness of the method.
