对线加速度计辅助惯性姿态角测量的误差分析表明，测量误差由加速度计噪声、二次积分离散化、信标噪声和加速度计频率特性误差组成。
The error analysis shows that the measurement error is caused by the noise of the accelerometer, discrete double integration, noise of beacon and frequency characteristic error.
给出了最大动压、一二级分离前和分离后三种工况下卫星结构的加速度响应历程。
The acceleration time response graphs at desired positions were presented under three load conditions: the maximum dynamic pressure, before separation, after separation.
加速度 表是飞行器的重要传感器之一 ，使用前需进行动态测试、误差分离和补偿。
Objective To provide the basis for medical evaluation of spacecraft, and to measure the impact acceleration of return-cabin of spacecraft.
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