Tightly coupled long baseline/ultra-short baseline integrated navigation system

2014 ◽  
Vol 47 (8) ◽  
pp. 1837-1855 ◽  
Author(s):  
Pedro Batista ◽  
Carlos Silvestre ◽  
Paulo Oliveira
Keyword(s):  
Navigation System ◽  
Integrated Navigation ◽  
Short Baseline ◽  
Integrated Navigation System ◽  
Long Baseline ◽  
Tightly Coupled

scholarly journals SINS/BDS Tightly-Coupled Integrated Navigation Algorithm for Hypersonic Vehicle

2021 ◽  
Author(s):  
kai chen ◽  
Sen-sen PEI ◽  
Cheng-zhi ZENG ◽  
Gang DING
Keyword(s):  
Navigation System ◽  
Maximum Velocity ◽  
Field Tests ◽  
Hypersonic Vehicle ◽  
Integrated Navigation ◽  
State Equations ◽  
Integrated Navigation System ◽  
Near Space ◽  
Navigation Algorithm ◽  
Tightly Coupled

Abstract A tightly-coupled integrated navigation system (TCINS) for hypersonic vehicles is proposed when the satellite signals are disturbed. Firstly, the architecture of the integrated navigation system for the hypersonic vehicle is introduced. This system applies fiber SINS, BeiDou satellite receiver (BDS) and SOPC missile-born computer. Subsequently, the SINS mechanization for hypersonic vehicle is presented. The J2 model is employed for the normal gravity of the near space. An algorithm for updating the attitude, velocity and position is designed. State equations and measurement equations of SINS/BDS tightly-coupled integrated navigation for hypersonic vehicle are given, and a scheme of validity for satellite data is designed. Finally, the SINS/BDS tightly-coupled vehicle field tests and hardware-in-the-loop (HWIL) simulation tests are carried out. The vehicle field test and HWIL simulation results show that the heading angle error of tightly-coupled integrated navigation is within 0.2°, the pitch and roll angle errors are within 0.05°, the maximum velocity error is 0.3m/s, and the maximum position error is 10m.

scholarly journals A LiDAR-Aided Indoor Navigation System for UGVs

2014 ◽  
Vol 68 (2) ◽  
pp. 253-273 ◽  
Author(s):  
Shifei Liu ◽  
Mohamed Maher Atia ◽  
Tashfeen B. Karamat ◽  
Aboelmagd Noureldin
Keyword(s):  
Navigation System ◽  
Error Model ◽  
Indoor Navigation ◽  
Navigation Systems ◽  
Integrated Navigation ◽  
Model Errors ◽  
Integrated Navigation System ◽  
Tightly Coupled ◽  
Indoor Navigation System ◽  
Sensor Errors

Autonomous Unmanned Ground Vehicles (UGVs) require a reliable navigation system that works in all environments. However, indoor navigation remains a challenge because the existing satellite-based navigation systems such as the Global Positioning System (GPS) are mostly unavailable indoors. In this paper, a tightly-coupled integrated navigation system that integrates two dimensional (2D) Light Detection and Ranging (LiDAR), Inertial Navigation System (INS), and odometry is introduced. An efficient LiDAR-based line features detection/tracking algorithm is proposed to estimate the relative changes in orientation and displacement of the vehicle. Furthermore, an error model of INS/odometry system is derived. LiDAR-estimated orientation/position changes are fused by an Extended Kalman Filter (EKF) with those predicted by INS/odometry using the developed error model. Errors estimated by EKF are used to correct the position and orientation of the vehicle and to compensate for sensor errors. The proposed system is verified through simulation and real experiment on an UGV equipped with LiDAR, MEMS-based IMU, and encoder. Both simulation and experimental results showed that sensor errors are accurately estimated and the drifts of INS are significantly reduced leading to navigation performance of sub-metre accuracy.

Design and Implementation of the Tightly-Coupled SINS / GPS Integrated Navigation System Based on FPGA for Target Missile

2013 ◽  
Vol 313-314 ◽  
pp. 287-290 ◽  
Author(s):  
Jing Jie Guo ◽  
Xiao Feng Cai ◽  
Chao He
Keyword(s):  
Navigation System ◽  
Integrated Control ◽  
Integrated Navigation ◽  
Integrated Navigation System ◽  
Nios Ii ◽  
Navigation Data ◽  
Design And Implementation ◽  
Control Computer ◽  
Tightly Coupled ◽  
Fpga Chip

A novel architecture of tightly-coupled SINS/ GPS integrated navigation system based on FPGA for target missile is proposed in this paper.The whole system is built on a single single FPGA chip containing a Nios II soft-core processor. In addition, the embedded real-time operating system μC/OS-IIis transplanted to the Nios II processor for managing each module in the system. The system can still provide the high-precision navigation data to integrated control computer of target missile when the number of available satellites is less than 4 by means of processing the pseudorange and pseudorange rate seprately. Therefore, the system has the strong application significance in terms of reducing the route shortcut of target missile.

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