Inertial Navigation System(INS)can continuously output the position, velocity, acceleration, heading, attitude for avionics system, weapon system and flight control system in real time in order to realize the flight mission and battle mission of a fighting aircraft. Due to the platform-INS structure features and the influence of assembling, the heading and attitude can be magnified more than 10 arc min instantaneously. Therefore, reflection of the INS performance can be helpful for aircraft. At present, the detection of the output of one time gyro frequency filter can be used to monitor the attitude error technology and realize method, which can quickly solve and detect the instantaneously error and accumulated with the time. The flight indicates the technology meet the pre-designed object and can be applied to many areas with good usage value and social effect.