• Acta Optica Sinica
  • Vol. 43, Issue 17, 1714002 (2023)
Ding Li1、2, Xudong Yu1、2、*, Guo Wei1、2, Baolun Yuan1、2, Chunfeng Gao1、2, Pengfei Zhang1、2, Guocheng Wang1、2, and Hui Luo1、2、**
Author Affiliations
  • 1College of Advanced Interdisciplinary Studies, National University of Defense Technology, Changsha 410073, Hunan, China
  • 2Nanhu Laser Laboratory, National University of Defense Technology, Changsha 410073, Hunan, China
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    DOI: 10.3788/AOS230855 Cite this Article Set citation alerts
    Ding Li, Xudong Yu, Guo Wei, Baolun Yuan, Chunfeng Gao, Pengfei Zhang, Guocheng Wang, Hui Luo. Development and Prospects of Long-Endurance Ring Laser Gyro Inertial Navigation System Technology[J]. Acta Optica Sinica, 2023, 43(17): 1714002 Copy Citation Text show less
    Structure diagram of mechanically dithered ring laser gyro (RLG)
    Fig. 1. Structure diagram of mechanically dithered ring laser gyro (RLG)
    Diagram of mechanically dithered RLG IMU
    Fig. 2. Diagram of mechanically dithered RLG IMU
    Diagram of principle of RLG strapdown inertial navigation system (SINS)
    Fig. 3. Diagram of principle of RLG strapdown inertial navigation system (SINS)
    High-precise RLG IMU manufactured by Honeywell
    Fig. 4. High-precise RLG IMU manufactured by Honeywell
    Key technologies of long-endurance RLG inertial navigation system
    Fig. 5. Key technologies of long-endurance RLG inertial navigation system
    ProductBias /[(°)·h-1Random walks /[(°)·h-1/2Scale factor error /10-6
    GG13200.0020.00185
    GG13420.0010.0011
    GG13890.00020.000040.1
    Table 1. Parameters of Honeywell RLG typical products
    ProductWorking modePosition accuracyApplied range
    AN/WSN-7BSingle-axis1 n mile/dSurface vessels and submarines
    AN/WSN-7ADual-axis0.071 n mile/dSurface vessels and submarines
    PL/MK4Strapdown1 n mile/dSurface vessels and submarines
    LN-100GStrapdown0.4 n mile/dFighters and unmanned aerial vehicles
    H-764GStrapdown0.2 n mile/dFighters
    Table 2. Parameters of typical long-endurance RLG SINS abroad
    Initial alignment methodMeritDemerit
    Coarse alignmentAnalytic alignmentSimple and fastStatic base only,subject to random errors,and motion disturbances
    Inertial frame alignmentFast and suitable for shaking basesWeak anti-interference capability
    Optimization-based alignmentFast and suitable for in-motion alignmentAccuracy is influenced by construction of observation vector
    Fine alignmentLinear Kalman filter alignmentSimple and fastAccuracy degradation or even failure in case of large initial errors
    Nonlinear Kalman filter alignmentSuitable for large initial errors on dynamic basesComputationally intensive and model flaws exist
    Invariant extended Kalman filter alignmentSuitable for large initial errors of dynamic bases and less calculationPoor estimation of inertial device errors
    Table 3. Summary of typical initial alignment methods
    SolutionMeritDemerit
    Single-axisSimple structure,high reliability,and low costLow accuracy
    Dual-axisMost errors are modulated by rotation and higher accuracy than that of single-axisUnable to modulate coupling of Earth rotation with other errors
    Tri-axisModulated all errors except random errors,complete isolation of vehicles angle movement,and high accuracyComplex structure and high cost
    Table 4. Summary of typical rotation modulation solutions
    Ding Li, Xudong Yu, Guo Wei, Baolun Yuan, Chunfeng Gao, Pengfei Zhang, Guocheng Wang, Hui Luo. Development and Prospects of Long-Endurance Ring Laser Gyro Inertial Navigation System Technology[J]. Acta Optica Sinica, 2023, 43(17): 1714002
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