惯性系统姿态误差精确诊断技术

Technology for Real-Time Monitor Attitude Error of INS

通过研究提出采用对陀螺一倍频滤波器输出信号的检测可实时精确诊断姿态误差技术和实现途径,从而解决快速识别这种瞬间产生且随时间积累姿态误差慢变的过程。飞行使用结果表明,本文提出的诊断技术达到了预期的目的,具有极为广泛地使用价值和社会效益。

Inertial Navigation System （INS）can continuously output the position, velocity, acceleration, heading, attitude for avionics system, weapon system and flightcontrol 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.