scholarly journals An Improved Version of the Fluxgate Compass Module

10.14311/954 ◽  
2007 ◽  
Vol 47 (4-5) ◽  
Author(s):  
V. Petrucha
Keyword(s):  
Error Compensation ◽  
Critical Parameter ◽  
Target Area ◽  
Navigation Systems ◽  
Digital Output ◽  
Typical Application ◽  
Tilt Error ◽  
Satellite Signal ◽  
Marine Navigation ◽  
Electronic Compass

Satellite based navigation systems (GPS) are widely used for ground, air and marine navigation. In the case of a malfunction or satellite signal inaccessibility, some back-up navigation system is needed. An electronic compass can provide this function. The compass module described in this paper is designed for precise navigation purposes. The compass module is equipped with electronic tilt error compensation, and includes everything in one package – electronics with digital output, sensors. A typical application of this compass is in underground drilling. A critical parameter in this application is heading accuracy. A reading error of 1 degree can cause a displacement of 1.8 metres in the target area (length of tunnel 100 m). This is not acceptable in an urban conglomeration, and therefore a more accurate heading sensing device must be used. An improved version of this electronic compass is being finished. 

scholarly journals Design and Real-Time Implementation of a 3-Stage CnW Heading System on an Ubuntu Linux-Embedded Board

2019 ◽  
Vol 2019 ◽  
pp. 1-13
Author(s):  
Felipe P. Vista IV ◽  
Kil To Chong
Keyword(s):  
Kalman Filter ◽  
Real Time ◽  
Extended Kalman Filter ◽  
Measurement Unit ◽  
Navigation Systems ◽  
Maritime Navigation ◽  
Stage 1 ◽  
Marine Navigation ◽  
Electronic Compass ◽  
Marine Navigation System

This paper describes the design and real-time implementation of a proposed algorithm for deriving an accurate heading system by fusing data from various inexpensive sensor devices that is comparable to more expensive maritime navigation systems. The proposed algorithm is a 3-Stage Classification N’ Weighing (CnW) Heading System with forward azimuth (FAz) and extended Kalman filter (EKF). Data from three Global Positioning System devices, an inertial measurement unit, and an electronic compass were fed into the algorithm that can be generally described as Classification N’ Weighing-Stage 1 → forward azimuth → Classification N’ Weighing-Stage 2 → extended Kalman filter → Classification N’ Weighing-Stage 3. The proposed algorithm is shown to be comparably accurate as an expensive marine navigation system, and it has less processing time compared to our previous work. The Qt-anywhere-based system developed on a Linux desktop was successfully downloaded onto an Ubuntu Linux-embedded board for real-time implementation. Important notes related to device naming problems when deploying the system on a Linux-embedded board are also given as reference for those interested to address it.

REVIEW OF SATELLITE-FREE NAVIGATION SYSTEMS

2018 ◽  
pp. 20-24
Author(s):  
M. K. Savkin ◽  
A. R. Filatov
Keyword(s):  
Satellite Navigation ◽  
Navigation Systems ◽  
Military Operations ◽  
Advantages And Disadvantages ◽  
Working Principle ◽  
Satellite Signal ◽  
Satellite Navigation Systems ◽  
Insufficient Number

Nowadays majority of navigation methods, used in unmanned flying vehicles, are based on satellite navigation systems, such as GPS or GLONASS, or are amplified with them. But hardware, that uses such systems, can’t work in difficult conditions, for example causes by relief: with insufficient number of satellites or at low satellite signal. Satellite navigation systems are vulnerable for methods of radio defense: satellite signal can be deadened or replaced. That is why such systems usage is unacceptable while critical missions during military operations, emergency or reconnaissance. The article briefly describes components used for building alternative satellite-free navigation systems for flying vehicles. For each component its purpose and brief description of working principle are given, advantages and disadvantages are considered.

scholarly journals Design of Accurate Navigation System by Integrating INS and GPS modules

2019 ◽  
Vol 11 (4) ◽  
pp. 139-154
Author(s):  
M. RAJA ◽  
Gaurav ASTHANA ◽  
Ajay SINGH ◽  
Ashna SINGHAL ◽  
Pallavi LAKRA
Keyword(s):  
Navigation System ◽  
Inertial Navigation System ◽  
External Information ◽  
Navigation Systems ◽  
Final Solution ◽  
Long Term Stability ◽  
Noise Characteristics ◽  
Aircraft Navigation ◽  
Satellite Signal

Navigation has a huge application in aviation and aircraft automatic approach. Two widely used navigation systems are Global position System (GPS) and Inertial Navigation System (INS). Triangulation method used to determine the aircrafts location by GPS, speed whereas an INS, with the aid of gyroscope and accelerometer, estimates the location, velocity and alignment of an aircraft. Aircraft navigation is a complex task and using only one of the above navigation systems results in inaccurate and insufficient data. GPS stops working when satellite signal is not received, susceptible to interfere occasionally has high noise content, and has a low bandwidth, INS system requires external information for initialization has long-term drift errors. Certain errors like ionosphere interference, clock error, orbital error, position error, etc. might arise and disrupt the navigation process. In order to outrun the limitations of the above two systems and counter the errors, both INS and GPS can be integrated and used to attain more smooth, accurate and faster aircraft attitude estimates, as they have complementary strengths and limitations. GPS is stable for a long period and can act as an independent navigation system whereas INS is not susceptible to interference and signal losses has high radio bandwidth and works well for short intervals of time. In order to get accurate and precise attitude estimation, calculation of the parameters at different altitude using both systems is done; furthermore the comparison and contrast between the results is performed, measured quantities are transformed between various frames like longitudinal to rolling, calculation and elimination of errors is done producing the final solution. Because of integrated GPS and INS, the navigation system exhibits robustness, higher bandwidth, better noise characteristics, and long-term stability.

Studies of the integrated navigation system correction in the absence of a satellite signal

2021 ◽  
Author(s):  
Keyword(s):  
Kalman Filter ◽  
Navigation System ◽  
Operation Mode ◽  
Satellite System ◽  
Navigation Systems ◽  
Integrated Navigation ◽  
Integrated Navigation System ◽  
Correction Signal ◽  
Satellite Signal ◽  
Navigation Information

The schemes of navigation systems correction are considered. The operation mode of the aircraft during navigation is analyzed. An adaptive modification of the linear Kalman filter is used to correct the navigation information. An algorithm for predicting a correction signal based on a neural network in the event of a loss of a SNS correction signal is formed. Experimental results show the effectiveness of the algorithm. Keywords aircraft; inertial navigation system; satellite system; Kalman filter; neural networks; genetic algorithm

The Design and Error Compensation Research of 3-Axis Electronic Compass Installed in Small Muti-Rotors Unmanned Aerial Vehicle

2012 ◽  
Vol 256-259 ◽  
pp. 2270-2273
Author(s):  
Song Wei Fan ◽  
Hong Wei Bian
Keyword(s):  
Unmanned Aerial Vehicle ◽  
Error Compensation ◽  
Zero Bias ◽  
Unmanned Vehicle ◽  
Bias Adjustment ◽  
Self Calibration ◽  
Aerial Vehicle ◽  
Electronic Compass

A 3-axis electronic compass is designed for small multi-rotors unmanned vehicle. The STM32F103 is used as E-compass’ CPU, and ADXL345 and MAG3110 is used as the acceleration and geomagnetic sensor. The E-compass’ software is programmed by using IAR EWARM. For outdoor applications, the ellipsoid assumption theory is simply proved and used for E-compass’ self-calibration. By using the zero-bias adjustment for pre-calibration and the fitellipsoid compensation for precise calibration, the E-compass’ precision is nearly 1 degree.

Coordinate Conversion Techniques in Microprocessor-based Receivers for Hyperbolic Radio-navigation Systems

1987 ◽  
Vol 40 (1) ◽  
pp. 81-95 ◽  
Author(s):  
David Last ◽  
Christopher Scholefield
Keyword(s):  
Low Cost ◽  
Low Frequency ◽  
Navigation Systems ◽  
Radio Navigation ◽  
Display Position ◽  
Coordinate Conversion ◽  
Marine Navigation

Traditional receivers for the low-frequency, hyperbolic radio-navigation systems – Loran-C, Decca Navigator and Omega – are expensive and are operated manually. They either display position fixes in hyperbolic coordinates for plotting by hand on navigation charts printed with hyperbolic overlays or they plot tracks automatically, often on distorted charts. Recently, low-cost receivers have been developed for marine navigation which operate wholly or largely automatically and which display position measurements in geographical coordinates – latitude and longitude – or as headings and distances to waypoints which are entered by the navigator in geographical coordinates.

Low Cost GPS/INS Navigation Systems with Error Compensation by Artificial Neural Networks

2012 ◽  
Vol 10 (4) ◽  
pp. 227-241
Author(s):  
Edmundo Alberto Marques Filho ◽  
Atair Rios Neto ◽  
Helio Koiti Kuga
Keyword(s):  
Neural Networks ◽  
Artificial Neural Networks ◽  
Error Compensation ◽  
Low Cost ◽  
Navigation Systems ◽  
Artificial Neural
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