Development and Prospects of Long-Endurance Ring Laser Gyro Inertial Navigation System Technology

Ding Li; Xudong Yu; Guo Wei; Baolun Yuan; Chunfeng Gao; Pengfei Zhang; Guocheng Wang; Hui Luo

doi:10.3788/AOS230855

Acta Optica Sinica, Volume. 43, Issue 17, 1714002(2023)

Development and Prospects of Long-Endurance Ring Laser Gyro Inertial Navigation System Technology

Ding Li^1,2, Xudong Yu^1,2、*, Guo Wei^1,2, Baolun Yuan^1,2, Chunfeng Gao^1,2, Pengfei Zhang^1,2, Guocheng Wang^1,2, and Hui Luo^1,2、**

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

show less

Abstract Get PDF(in Chinese)

Figures & Tables(9)

Fig. 1. Structure diagram of mechanically dithered ring laser gyro (RLG)

Download full size

Fig. 2. Diagram of mechanically dithered RLG IMU

Download full size

Fig. 3. Diagram of principle of RLG strapdown inertial navigation system (SINS)

Download full size

Fig. 4. High-precise RLG IMU manufactured by Honeywell

Download full size

Fig. 5. Key technologies of long-endurance RLG inertial navigation system

Download full size

Table 1. Parameters of Honeywell RLG typical products
View table
Table 1. Parameters of Honeywell RLG typical products
Product Bias /［（°）·h^-1］ Random walks /［（°）·h^-1/2］ Scale factor error /10^-6
GG1320 0.002 0.0018 5
GG1342 0.001 0.001 1
GG1389 0.0002 0.00004 0.1

Table 2. Parameters of typical long-endurance RLG SINS abroad

View table

Table 2. Parameters of typical long-endurance RLG SINS abroad

Product	Working mode	Position accuracy	Applied range
AN/WSN-7B	Single-axis	1 n mile/d	Surface vessels and submarines
AN/WSN-7A	Dual-axis	0.071 n mile/d	Surface vessels and submarines
PL/MK4	Strapdown	1 n mile/d	Surface vessels and submarines
LN-100G	Strapdown	0.4 n mile/d	Fighters and unmanned aerial vehicles
H-764G	Strapdown	0.2 n mile/d	Fighters

Table 3. Summary of typical initial alignment methods

View table

Table 3. Summary of typical initial alignment methods

Initial alignment method		Merit	Demerit
Coarse alignment	Analytic alignment	Simple and fast	Static base only，subject to random errors，and motion disturbances
	Inertial frame alignment	Fast and suitable for shaking bases	Weak anti-interference capability
	Optimization-based alignment	Fast and suitable for in-motion alignment	Accuracy is influenced by construction of observation vector
Fine alignment	Linear Kalman filter alignment	Simple and fast	Accuracy degradation or even failure in case of large initial errors
	Nonlinear Kalman filter alignment	Suitable for large initial errors on dynamic bases	Computationally intensive and model flaws exist
	Invariant extended Kalman filter alignment	Suitable for large initial errors of dynamic bases and less calculation	Poor estimation of inertial device errors

Table 4. Summary of typical rotation modulation solutions

View table

Table 4. Summary of typical rotation modulation solutions

Solution	Merit	Demerit
Single-axis	Simple structure，high reliability，and low cost	Low accuracy
Dual-axis	Most errors are modulated by rotation and higher accuracy than that of single-axis	Unable to modulate coupling of Earth rotation with other errors
Tri-axis	Modulated all errors except random errors，complete isolation of vehicles angle movement，and high accuracy	Complex structure and high cost

Tools

Get Citation

Copy Citation Text

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

Download Citation

EndNote(RIS)BibTex Plain Text

Set citation alerts for article

Save article for my favorites