Aeronautical electronic equipment is used for data collection during flight, usually fixed to the nose radome using mounting brackets, studying the stiffness and first-order frequency performance of the mounting brackets to avoid plastic deformation and resonance during flight, which is of great engineering significance for improving flight stability. The static strength and modal analysis of the mounting bracket under inertial load show that the bracket has good Bending stiffness, but the first order frequency is low. Using a sensitivity analysis method to determine the design variables of the installation bracket, with the goal of minimizing the total weight of the structure as the optimization objective, the thickness of each component of the bracket is optimized while ensuring the stiffness and first-order modal performance of the installation bracket. Vibration tests are conducted on the optimized installation bracket structure, and the test frequency values and finite element calculation values are in good agreement, verifying the accuracy of the finite element modal analysis method. The results show that the stiffness of the optimized installation bracket structure remains basically unchanged, with an increase of 18.09% in first-order frequency and a weight reduction of 19.33%. The improved design meets the equipment installation requirements.