机载光纤捷联惯导系统温度补偿技术
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- 英文论文题名：Temperature compensation technology for airborne FOG SINS
- 论文作者：庞松 ; 杨正 ; 董洁
- 英文论文作者：PANG Song ; YANG Zheng ; DONG Jie ; Tianjin Navigation Instrument Research Institute
- 年：2016
- 作者机构：天津航海仪器研究所;
- 论文关键词：捷联惯性导航系统 ; 光纤陀螺 ; 温度补偿 ; 模糊逻辑
- 英文论文关键词：strap-down inertial navigation system ; fiber optic gyro ; temperature compensation ; fuzzy logic
- 会议召开时间：2016-09-27
- 会议录名称：2016年光学陀螺及系统技术发展与应用研讨会论文集
- 语种：中文
- 分类号：V249.322
- 学会代码：ZGGZ
- 会议名称：2016年光学陀螺及系统技术发展与应用研讨会
- 会议地点：中国江西九江
- 主办单位：中国惯性技术学会
- 学会名称：中国惯性技术学会
- 页数：4
- 文件大小：584k
- 原文格式：D
- 会议级别：全国
摘要
针飞机搭载设备的整个工作过程是由地面快速上升到万米高空,任务完成后降落回地面,飞机的快速升空和降落致使机舱内温度剧烈变化,温度最低达到-40℃。机载光纤捷联惯性导航系统是以光纤陀螺仪作为主要惯性元件的惯性系统,为保证系统整体精度满足使用要求,对系统进行温度补偿是一个有效措施。为适应系统在升空过程中遇到的剧烈温度冲击,结合光纤陀螺自身的温度特性和在系统上特定热平衡条件设计了一种基于模糊逻辑的光纤捷联惯性导航系统温度漂移补偿方案。根据当前众多学者研究得出的光纤陀螺非互易性相位差的结论,设计了一种以陀螺内部温度、温度变化率和系统空间温度梯度为输入的模糊逻辑温度漂移补偿方案。此方案适用于工作在剧烈温变条件下的光纤陀螺捷联惯性导航系统。经过温箱内变温试验验证,在全温范围内陀螺的零偏稳定性从0.1°/h提高到0.03°/h以内。
In order to deal with the rapid changed temperature of airborne FOG SINS in the process of the launch, combining FOG characteristic and INS heat balance, a temperature error compensation model based on fuzzy logic is designed. Based on the conclusion of FOG uninterchangeable phasic error researched by some scholars, the temperature error compensation scheme based on fuzzy logic, which inputs are the temperature of FOG inside, the temperature changing rate of FOG inside and the space grads of FOG temperature. This technique can be used in FOG strapdown inertial navigation system working in the condition with great changed temperature. In testing experiments, the bias stability has been reduced from 0.1°/h to 0.03°/h.
In order to deal with the rapid changed temperature of airborne FOG SINS in the process of the launch, combining FOG characteristic and INS heat balance, a temperature error compensation model based on fuzzy logic is designed. Based on the conclusion of FOG uninterchangeable phasic error researched by some scholars, the temperature error compensation scheme based on fuzzy logic, which inputs are the temperature of FOG inside, the temperature changing rate of FOG inside and the space grads of FOG temperature. This technique can be used in FOG strapdown inertial navigation system working in the condition with great changed temperature. In testing experiments, the bias stability has been reduced from 0.1°/h to 0.03°/h.
引文
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[2]Shupe D M.Thermally induced nonreciprocity in the fiber-optic interferometer[J].Appl.Opt,1980,19(5):654-655.
[3]王巍,张桂才.光纤陀螺敏感线圈的温度特性研究.中国惯性技术学报,1998,6(1):41-45.
[4]卫炎,陆恺,张炎华,等.光纤陀螺温度漂移自适应建模研究[J].上海交通大学学报,1996,30(1):84-88
[5]马小霞,戴世荣,李汉舟,等.基于模糊控制的陀螺温度控制系统研究[J].中国惯性技术学报,2004,12(2):68-71.