中国惯性技术学报
中國慣性技術學報
중국관성기술학보
JOURNAL OF CHINESE INERTIAL TECHNOLOGY
2014年
4期
421-425
,共5页
王彬%翁海娜%汪湛清%张宇飞%胡小毛
王彬%翁海娜%汪湛清%張宇飛%鬍小毛
왕빈%옹해나%왕담청%장우비%호소모
速度阻尼%双轴旋转调制%系统级标定%系泊状态
速度阻尼%雙軸鏇轉調製%繫統級標定%繫泊狀態
속도조니%쌍축선전조제%계통급표정%계박상태
speed damping%two-axis rotation modulation%systematic calibration%mooring base
惯性元件参数的长期稳定决定着惯导系统的精度,目前对于激光陀螺捷联惯导系统(RLG-SINS)主要是采用系统级旋转调制技术来实现高精度导航能力,同时系统级旋转也提高了初始对准精度以及惯性元件误差的可观测性。针对激光陀螺惯导系统惯性元件误差项的特点,同时结合分立式标定与系统级标定各自的优势,设计了一种水平阻尼模式下的 Kalman 滤波方案,利用双轴旋转机构,通过观测导航位置误差来实现初始对准以及部分惯性元件误差参数的标定,可以有效地减小惯性元件逐次启动误差对导航精度的影响。仿真结果表明,系泊状态零速度阻尼模式下工作4 h,可以标定出石英加速度计标度因数误差、零偏与激光陀螺零偏,共计9项误差参数。加速度计零偏估计误差小于2%,陀螺零偏估计误差小于8%,误差估计精度满足高精度惯性导航要求,该方法具备一定的工程实用性。
慣性元件參數的長期穩定決定著慣導繫統的精度,目前對于激光陀螺捷聯慣導繫統(RLG-SINS)主要是採用繫統級鏇轉調製技術來實現高精度導航能力,同時繫統級鏇轉也提高瞭初始對準精度以及慣性元件誤差的可觀測性。針對激光陀螺慣導繫統慣性元件誤差項的特點,同時結閤分立式標定與繫統級標定各自的優勢,設計瞭一種水平阻尼模式下的 Kalman 濾波方案,利用雙軸鏇轉機構,通過觀測導航位置誤差來實現初始對準以及部分慣性元件誤差參數的標定,可以有效地減小慣性元件逐次啟動誤差對導航精度的影響。倣真結果錶明,繫泊狀態零速度阻尼模式下工作4 h,可以標定齣石英加速度計標度因數誤差、零偏與激光陀螺零偏,共計9項誤差參數。加速度計零偏估計誤差小于2%,陀螺零偏估計誤差小于8%,誤差估計精度滿足高精度慣性導航要求,該方法具備一定的工程實用性。
관성원건삼수적장기은정결정착관도계통적정도,목전대우격광타라첩련관도계통(RLG-SINS)주요시채용계통급선전조제기술래실현고정도도항능력,동시계통급선전야제고료초시대준정도이급관성원건오차적가관측성。침대격광타라관도계통관성원건오차항적특점,동시결합분입식표정여계통급표정각자적우세,설계료일충수평조니모식하적 Kalman 려파방안,이용쌍축선전궤구,통과관측도항위치오차래실현초시대준이급부분관성원건오차삼수적표정,가이유효지감소관성원건축차계동오차대도항정도적영향。방진결과표명,계박상태령속도조니모식하공작4 h,가이표정출석영가속도계표도인수오차、령편여격광타라령편,공계9항오차삼수。가속도계령편고계오차소우2%,타라령편고계오차소우8%,오차고계정도만족고정도관성도항요구,해방법구비일정적공정실용성。
The long-term stability of inertial element parameters determines the accuracy of inertial naviga-tion systems, and the present laser gyroscope strapdown inertial navigation system(RLG-SINS) is mainly by means of systematic modulation techniques to achieve the capability of high accuracy navigation or improve the accuracy of initial alignment and the observability of inertial component errors. According to the inertial component error characteristics of RLG-SINS, and combining with the respective advantages of discrete calibration and systematic calibration, a Kalman filter scheme is designed in lever-damp mode to achieve the initial alignment and to calibrate parts of inertial component errors by observing navigation position errors and using two-axis indexing. This scheme can effectively reduce the influence of inertial component’s each startup error on navigation accuracy. The simulation results show that the total nine error parameters (scale factor error and bias of the quartz accelerometer, laser gyroscope bias) can be estimated on mooring base during 4 h operation in zero-speed damping mode. The estimated error for accelerator bias is less than 2%, and the estimated error for gyroscope bias is less than 8%, meeting the demands of high accuracy inertial navigation, and showing that this method has certain engineering practicability.