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作为研究人造卫星运载火箭惯导系统的一部分,试制了捷联式惯性测量装置用加速度计,用于惯导系统实时模拟综合评价实验,本加速度计与以前试制的液浮磁悬浮摆式加速度计是同一类型,属于单自由度力矩平衡式液浮磁悬浮摆式加速度计。它既具有火箭惯导控制所必须的基本性能(分辨率为7×10~(-7)G,非线性误差系数为1.06×10~(-4)G/G~2,稳定性为±1.3×10~(-5)G),同时又可以利用其内部设置的指令力矩器产生模拟加速度输入。本报告将介绍惯性测量装置用加速度计的主要性能及模拟加速度输入输出的特性试验及其结果。
As part of the study of artificial satellite launch vehicle inertial navigation system, a accelerometer for strapdown inertial measurement device was trialled for the real-time simulation of inertial navigation system. The accelerometer was compared with the previous prototype liquid crystal magnetic suspension pendulum accelerometer The same type, belonging to a single degree of freedom torque balance magnetic floating pendulum accelerometer. It not only has the basic performance of rocket inertial control (resolution of 7 × 10 -7 G, nonlinear error coefficient of 1.06 × 10 -4 G / G ~ 2, the stability of ± 1.3 × 10 ~ (-5) G), at the same time, it can use its internal set command torque to generate analog acceleration input. This report describes the main features of accelerometers used in inertial measurement devices and the characteristics of simulated acceleration inputs and outputs and their results.