A Simplified Model of Inertial Navigation System for Underground Pipeline Track Instrument

Based on the analysis of the basic principle of traditional inertial navigation technology, this paper puts forward a kind of simplified model of the track measurement which applies to underground pipeline. The model using structures of half-strap-down stable platform that composes of a single axis gyro, two accelerometers and pulse taximeter, by measuring angular velocity of pipeline azimuth, pitching angle, platform rolling angle and pipeline length, combined with self-actuated research space track, work out the mathematics model, eventually work out the space track of the underground pipeline. The experiment proves that the underground pipeline track measurement instrument which is designed based on the simplified model, can meet the accuracy requirement of the no-dig project on track measurement, and the equipment’s operation is stable and reliable.

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Simulating Gyro of Strapdown Inertial Navigation System Based on Star Sensor

Applied Mechanics and Materials ◽

10.4028/www.scientific.net/amm.182-183.1090 ◽

2012 ◽

Vol 182-183 ◽

pp. 1090-1094

Author(s):

Wei Gao ◽

Lei Zhang

Keyword(s):

Angular Velocity ◽

Real Time ◽

Navigation System ◽

Inertial Navigation System ◽

Inertial Navigation ◽

Strapdown Inertial Navigation System ◽

Star Sensor ◽

Measuring Instrument ◽

Priori Information ◽

Strapdown Inertial Navigation

In inertial navigation system, gyro is used to measure the angular velocity of carrier relative to inertial space for achieve attitude matrix updated in real time. Gyro difficult to eliminate the error, results in strapdown inertial navigation system precision decrease with time. Star sensor is a high-precision attitude measuring instrument and don’t require any priori information, the attitude date can be provided by star sensor. Thus, gyro is simulated by star sensor in order to improve the precision of strapdown inertial navigation system.

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Research on In-Flight Alignment for Micro Inertial Navigation System Based on Changing Acceleration using Exponential Function

Micromachines ◽

10.3390/mi10010024 ◽

2018 ◽

Vol 10 (1) ◽

pp. 24 ◽

Cited By ~ 1

Author(s):

Yun Xu ◽

Tong Zhou

Keyword(s):

Exponential Function ◽

Navigation System ◽

Inertial Navigation System ◽

Field Experiments ◽

Inertial Navigation ◽

Rolling Angle ◽

Attitude Error ◽

Heading Angle ◽

Initial Attitude ◽

The Stability

In order to guarantee the stable flight of a guided projectile, it is difficult to realize in-flight alignment for the micro inertial navigation system (MINS) during its short flight time. In this paper, a method based on changing acceleration using exponential function is proposed. First, double-vector observations were derived. Then the initial attitude for the guided projectiles was estimated by the regressive quaternion estimation (QUEST) algorithm. Further, the estimated errors were analyzed, and the reason for using the changing acceleration for the in-flight alignment was explained. A simulation and semi-physical experiment was performed to show the effectiveness of the proposed method. The results showed that the initial attitude error for the rolling angle was about 0.35°, the pitch angle was about 0.1° and the heading angle was about 0.6°, in which the initial shooting angle was between 15° and 55°. In future studies, the field experiments will be carried out to test the stability of the proposed in-flight alignment for guided projectiles.

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The Design for Twelve-Accelerometer Gravity Gradiometer

Key Engineering Materials ◽

10.4028/www.scientific.net/kem.419-420.221 ◽

2009 ◽

Vol 419-420 ◽

pp. 221-224

Author(s):

Lin Zhao ◽

Feng Ming Liu ◽

Hai Jing Yuan ◽

Hong Bin Zhao

Keyword(s):

Angular Velocity ◽

Navigation System ◽

Inertial Navigation System ◽

Inertial Navigation ◽

Gravity Gradient ◽

Gravity Gradiometer ◽

Mathematical Relationship ◽

New Type ◽

Design And Manufacture

The design and manufacture for GGI are different and only several countries have the ability to produce it. Devising the feasible scheme for gravity gradiometer is the primary question.In this paper, a new type of GGI is designed using twelve accelerometers. First, the mathematical relationship between the accelerometer and GGI is derived and the method to separate the angular velocity and gravity gradient is disscussed. Second, the model of twelve-accelerometer gravity gradiometer is provided. Third, the estimation of angular velocity is analyzed when the GGI is installed in the form of strapdown or stabilized state. Finally, it is concluded that a new type of inertial navigation system using gravity gradiometers will be configured when it becomes possible to precisely measure gravity gradient.

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On Building of Inertial Navigation System in the Condition of Presence of Considerable g-Load and Angular Velocity in Preferential Direction

Kosmičeskaâ tehnika. Raketnoe vooruženie ◽

10.33136/stma2018.01.031 ◽

2018 ◽

Vol 2018 (1) ◽

pp. 31-38

Author(s):

Е. А. Degtyareva ◽

А. N. Lapko ◽

А. А. Meleshko ◽

Y. V. Chucha

Keyword(s):

Angular Velocity ◽

Navigation System ◽

Inertial Navigation System ◽

Inertial Navigation ◽

Preferential Direction

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Analysis of the Strapdown Inertial Navigation System (SINS) Error Genesis

Transport and Aerospace Engineering ◽

10.2478/tae-2018-0006 ◽

2018 ◽

Vol 6 (1) ◽

pp. 44-54

Author(s):

Pjotrs Trifonovs-Bogdanovs ◽

Anvar Zabirov

Keyword(s):

Angular Velocity ◽

Navigation System ◽

Velocity Measurement ◽

Inertial Navigation System ◽

Inertial Navigation ◽

Strapdown Inertial Navigation System ◽

Critical Element ◽

Velocity Sensor ◽

Strapdown Inertial Navigation

Abstract Analysis and simulation of the Strapdown Inertial Navigation System (SINS) error genesis revealed that the East Feedback Contour has the greatest influence on the development of an error in this model, and angular velocity sensor Δω𝒚 is the critical element. In order to prevent the development of an error, structural correction in the East Feedback Contour, and elements that are more critical, namely in angular velocity measurement sensors is the best option.

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