在大量生产的飞机上用于导航的捷联式惯性技术比较关键问题之一是初始校准。基于这个考虑探索了出现希望的二步骤自校准方案。第一或者“粗略地”校准步骤应用了重力和地球转动失量的测量去直接计算有关载机系对参数系的转换矩阵,提出了线性化误差分析。第二个“精确的”校准阶段通过提供补偿角速度信号的基座运动给转换计算机去修正初始转换估算。 One of the more critical issues with strapdown inertial technology used for navigation on mass-produced aircraft is the initial calibration. Based on this consideration, a promising two-step self-calibration scheme was explored. The first or “roughly” calibration step applies a measure of gravity and Earth’s rotational losses to directly calculate the transformation matrix for the vehicle-to-parameter system, and presents a linearized error analysis. The second “accurate” calibration phase modifies the initial conversion estimate by providing a base computer that compensates for the angular velocity signal to the conversion computer.