Zhang Chunxi, Wang Xin, Song Lailiang, Ran Longjun
School of Instrumentation and Optoelectronic Engineering, Beihang University, Beijing 100191, China.
Sensors (Basel). 2021 Jan 4;21(1):294. doi: 10.3390/s21010294.
Strap-down inertial navigation systems (INSs) with quartz flexible accelerometers (QFAs) are widely used in many conditions, particularly in aerial vehicles. Temperature is one of the significant issues impacting the performance of INS. The variation and the gradient of temperature are complex under aerial conditions, which severely degrades the navigation performance of INS. Previous work has indicated that parts of navigation errors could be restrained by simple temperature compensation of QFA. However, the temperature hysteresis of the accelerometer is seldom considered in INS. In this paper, the temperature hysteresis mechanism of QFA and the compensation method would be analyzed. Based on the fundamental model, a comprehensive temperature hysteresis model is proposed and the parameters in this model were derived through a temperature cycling test. Furthermore, the comparative experiments in the laboratory were executed to refine the temperature hysteresis model and to verify the effectiveness of the new compensation method. Applying the temperature hysteresis compensation in flight condition, the result shows that the position error (CEP) is restrained from 1.54 nmile/h to 1.29 nmile/h. The proposed temperature hysteresis compensation method improves the performance of INS effectively and feasibly, which could be promoted to other applications of INS in similar temperature changing environment correspondingly.
带有石英挠性加速度计（QFA）的捷联惯性导航系统（INS）在许多情况下都有广泛应用，尤其是在飞行器中。温度是影响惯性导航系统性能的重要问题之一。在飞行条件下，温度的变化和梯度很复杂，这严重降低了惯性导航系统的导航性能。先前的工作表明，通过对石英挠性加速度计进行简单的温度补偿，可以抑制部分导航误差。然而，在惯性导航系统中很少考虑加速度计的温度滞后现象。本文将分析石英挠性加速度计的温度滞后机理及补偿方法。基于基本模型，提出了一个综合温度滞后模型，并通过温度循环试验推导了该模型中的参数。此外，在实验室进行了对比实验，以完善温度滞后模型并验证新补偿方法的有效性。在飞行条件下应用温度滞后补偿，结果表明位置误差（CEP）从1.54海里/小时降低到了1.29海里/小时。所提出的温度滞后补偿方法有效且可行地提高了惯性导航系统的性能，相应地可推广到惯性导航系统在类似温度变化环境中的其他应用。
