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激光捷联惯导系统中传感器由于直接与载体固联,同时还存在激光陀螺抖动振动,使系统误差特性较平台式系统更复杂,振动对系统动态误差影响更大。针对某型激光惯导系统随载机试飞中长航时精度超差的问题,分析了振动诱导误差的形成机理,查明了长航时精度超差的原因是由于惯导部件与其安装支架连接后的产品谐振频率与飞机螺旋桨叶通过频率耦合所致,为此提出了降低惯导部件内减振器带宽、提高载机惯导部件安装支架刚度的改进措施。经完善激光惯导系统算法,实施改进措施后,试飞考核,系统精度达标,从而验证了措施的正确性。
Due to the direct coupling with the carrier and the vibration and vibration of the laser gyro, the sensor error in the laser strapdown inertial navigation system makes the system error characteristics more complicated than the platform system, and the vibration has more influence on the system dynamic error. Aiming at the problem that the precision of a certain type of laser inertial navigation system during the flight test of long-range laser inertial navigation system is too high, the forming mechanism of vibration induced error is analyzed. It is found that the precision tolerance of long-range navigation is due to the connection of inertial navigation components with its mounting brackets After the resonant frequency of the product and the aircraft propeller blade through the frequency coupling, this paper put forward to reduce the inertial vibration damper bandwidth, improve the rigidity of the inertial navigation unit mounting bracket improvements. After the improvement of laser inertial navigation system algorithm, the implementation of improved measures, flight test, system accuracy standards, which verified the correctness of the measures.