During the aircraft flight, especially during the takeoff and landing, the nose gear door is subjected to severe fluctuating pressure vibration environment, and long-term exposure to this fluctuating pressure environment may induce the hatch structure to produce a dramatic dynamic response, which may even lead to structural fatigue damage. This paper combines finite element analysis and random vibration theory to conduct modal analysis and frequency response analysis of the nose gear door. Based on the results of modal analysis and frequency response analysis, the random vibration analysis under fluctuating pressure is carried out for the nose gear door. The main vibration pattern of the nose gear door, the stress extremes under fluctuating pressure and the dangerous areas are calculated. The extreme value of stress on the composite door body appears at the connection between the composite hatch doors and the metal joints, in which the nose gear door is prone to structural damage. In the structural design of nose gear door structure, ground environment test and flight test, the vibration intensity of the connection between the composite hatch doors and the metal joints should also be considered.