Abstract: For designing helicopter-borne electronic equipment vibration isolators, it is essential to account for both attenuation of high-frequency vibration and shock-induced deformation to ensure reliability. This study proposes an optimal design methodology for such systems. First, dynamic equations under base excitation are derived. The helicopter vibration spectrum is converted into narrow-band random vibration to analyze stochastic response. Shock response is then simulated numerically using the Newmark-β method. A multi-objective optimization model is subsequently developed. Finally, the method is validated through a case study on a vibration isolator for a MEMS-based inertial navigation system onboard the TD550 coaxial unmanned helicopter.