中文摘要：

研制的无驱动结构微机械陀螺可同时敏感高速旋转飞行体滚动角速度、输入角速度（俯仰和偏航角速合成的角速度）信息。为了将合角速度分解成偏航角速度和俯仰角速度，利用加速度计建立了空间基准，通过陀螺和加速度计输出信号的相位差，可确定飞行体空间偏转方向。阐明了该方法原理，分析了误差因素，对主要误差因素滚动角速度与合速度影响建立了复合影响数学模型，并进行了补偿。结果表明：通过该方法可以确定飞行体空间偏转方向，从而可将俯仰和偏航角速度分解出来。

英文摘要：

The non-driven structure micromachined gyroscope can not only sense the angular rate of rotating but also sense input angular rate（ pieth and yaw angular rate） at the same time of high-speed-rotating airframe. In order to demodulate yaw and pitch angular rate, the space benchmark is set up based on accelerometer. The deflexion orientation of the rotating airframe is ascertained according to the difference of phase between gyroscope and accelerometer output signals. The principle of this method is illustrated and the error is analyzed. Moreover, the composite math model of main effect of rotating angular rate and input on phase-difference is set up to compensate the error. The results show that the method can determine the deflexion orientation of the rotating airframe, so the yaw and pictch angular rate can be demodulated.