Abstract: As an auxiliary display device and backup display device, the airborne micro display is crucial for the flight safety and mission execution of aircraft. Vibration, as one of the main causes of failure in airborne electronic equipment, should be given special attention in the structural design of airborne micro displays. In this paper, taking the airborne micro display as the research object, the maximum stress and fatigue life of the structure during the vibration process are obtained through random vibration simulation and fatigue analysis. Then topology optimization of the main frame of the micro display is carried out with mass fraction as the constraint and maximum stiffness as the objective function. With a mass gain of 1.2 g, the maximum stress of the main frame vibrating in X, Y and Z directions is reduced by 70.3%, 68.6% and 64.6% respectively. The fatigue life of the main frame is increased by 3 101% in X direction and 1 797% in Y direction. Ultimately the airborne micro display meets the design requirements.