scholarly journals Study of the possibility of using strapdown inertial gauges as part of the topographic location and navigation system of own design

2021 ◽  
Vol 31 (1) ◽  
pp. 28-36
Author(s):  
S. V. Mikhaylov
Keyword(s):  
Navigation System ◽  
Climatic Conditions ◽  
Software Implementation ◽  
Navigation Systems ◽  
Inertial Navigation Systems ◽  
Problem Statement ◽  
Autonomous Mode ◽  
Motion Parameters ◽  
Functional Software ◽  
Practical Implications

Problem statement. During the operation of purchased navigation systems for topographic geodetic referencing and orientation, many shortcomings are revealed, mainly associated with software implementation, the correction of which is not always possible. A way out of this situation is creating own navigation complex from ready-made purchased meters and developed functional software (FSW). In this case, the primary task is to determine the preferable meters as part of the topographic location and navigation system (TLNS).Objective. Conduct a study of strapdown inertial navigation systems (SINS) of various manufacturers for compliance with the declared technical characteristics to determine a suitable meter for TLNS.Results. Information on the practical testing of studies the numerical estimates of standard deviations (SD) of errors in the determination and drift of grid azimuth, roll, and pitch of strapdown inertial meters in various climatic conditions, as well as under the influence of sinusoidal and broadband random vibrations (BRV) is presented. The values deviations of motion parameters from the reference values in autonomous mode as part of the developed navigation complex of mobile land objects of a particular purpose are analyzed. The preferable inertial meter for use in the developed TLNS was determined based on the research carried out.Practical implications. Recommendations are given on the use of SINS as an integral part at the facilities of the proposed base.

Initial Alignment of a Moving Inertial Navigation System

1960 ◽  
Vol 13 (3) ◽  
pp. 301-315
Author(s):  
Richard B. Seeley ◽  
Roy Dale Cole
Keyword(s):  
Navigation System ◽  
Inertial Navigation System ◽  
Local Level ◽  
Inertial Navigation ◽  
Navigation Systems ◽  
Velocity Measurements ◽  
Initial Alignment ◽  
Inertial Navigation Systems ◽  
Error Sources ◽  
China Lake

This paper describes and discusses some of the techniques by which a moving inertial platform may be aligned by using external velocity measurements and also presents some of the major problems and error sources affecting such alignment. It is based upon the results of a 3-year study, of inertial and doppler-inertial navigation at the Naval Ordnance Test Station, China Lake, California, and, in general, applies to inertial navigation systems which erect to either the local level or the mass-attraction vertical. Although rudimentary derivations are made of the alignment techniques, the paper is largely nonmathematical for ease of reading. Emphasis is placed upon the major errors affecting the alignment. This paper describes and discusses some of the techniques by which a moving inertial platform may be aligned by using external velocity measurements and also presents some of the major problems and error sources affecting such alignment. It is based upon the results of a 3-year study, of inertial and doppler-inertial navigation at the Naval Ordnance Test Station, China Lake, California, and, in general, applies to inertial navigation systems which erect to either the local level or the mass-attraction vertical. Although rudimentary derivations are made of the alignment techniques, the paper is largely nonmathematical for ease of reading. Emphasis is placed upon the major errors affecting the alignment.

Problem of the Vertical Deflection in High-Precision Inertial Navigation

2020 ◽  
Vol 28 (4) ◽  
pp. 3-15
Author(s):  
V.G. Peshekhonov ◽  
◽  
Keyword(s):  
Systematic Error ◽  
High Precision ◽  
Navigation System ◽  
Inertial Navigation System ◽  
Inertial Navigation ◽  
Reference Ellipsoid ◽  
Navigation Systems ◽  
Vertical Deflection ◽  
Inertial Navigation Systems ◽  
Output Data

The paper addresses the systematic error of an inertial navigation system, caused by the discrepancy between the plumb line and the normal to the reference ellipsoid surface. The methods of this discrepancy estimation, and their use for correcting the output data of inertial navigation systems are studied.

scholarly journals Analysis and Verification of Rotation Modulation Effects on Inertial Navigation System based on MEMS Sensors

2013 ◽  
Vol 66 (5) ◽  
pp. 751-772 ◽  
Author(s):  
Xueyun Wang ◽  
Jie Wu ◽  
Tao Xu ◽  
Wei Wang
Keyword(s):  
Navigation System ◽  
Inertial Navigation System ◽  
Inertial Sensors ◽  
Inertial Navigation ◽  
Cost Effective ◽  
Navigation Systems ◽  
Inertial Navigation Systems ◽  
Mems Sensors ◽  
Micro Electro Mechanical Systems ◽  
Position Accuracy

Inertial Navigation Systems (INS) were large, heavy and expensive until the development of cost-effective inertial sensors constructed with Micro-electro-mechanical systems (MEMS). However, the large errors and poor error repeatability of MEMS sensors make them inadequate for application in many situations even with frequent calibration. To solve this problem, a systematic error auto-compensation method, Rotation Modulation (RM) is introduced and detailed. RM does no damage to autonomy, which is one of the most important characteristics of an INS. In this paper, the RM effects on navigation performance are analysed and different forms of rotation schemes are discussed. A MEMS-based INS with the RM technique applied is developed and specific calibrations related to rotation are investigated. Experiments on the developed system are conducted and results verify that RM can significantly improve navigation performance of MEMS-based INS. The attitude accuracy is improved by a factor of 5, and velocity/position accuracy by a factor of 10.

scholarly journals A Novel Information Fusion Method for Redundant Rotational Inertial Navigation Systems Based on Reduced-Order Kalman Filter

2018 ◽  
Vol 160 ◽  
pp. 07005
Author(s):  
Lin Wang ◽  
Wenqi Wu ◽  
Guo Wei ◽  
Jinlong Li ◽  
Ruihang Yu
Keyword(s):  
Kalman Filter ◽  
Information Fusion ◽  
Navigation System ◽  
Inertial Navigation System ◽  
High Reliability ◽  
Inertial Navigation ◽  
Position Error ◽  
Navigation Systems ◽  
Inertial Navigation Systems ◽  
Reduced Order

The redundant rotational inertial navigation systems can satisfy not only the high-accuracy but also the high-reliability demands of underwater vehicle on navigation system. However, different systems are usually independent, and lack of information fusion. A reduced-order Kalman filter is designed to fuse the navigation information output of redundant rotational navigation systems which usually include a dual-axis rotational inertial navigation system being master system and a single-axis rotational inertial navigation system being hot-backup system. The azimuth gyro drift of single-axis rotational inertial navigation system can be estimated by the designed filter, whereby the position error caused by that can be compensated with the aid of designed position error prediction model. As a result, the improved performance of single-axis rotational inertial navigation system can guarantee the position accuracy in the case of dual-axis system failure. Semi-physical simulation and experiment verify the effectiveness of the proposed method.

Loran-Inertial Navigation Systems for Long-Range Use

1965 ◽  
Vol 18 (3) ◽  
pp. 319-329
Author(s):  
Loren E. De Groot
Keyword(s):  
Long Range ◽  
Navigation System ◽  
Inertial Navigation ◽  
Navigation Systems ◽  
Inertial Navigation Systems ◽  
Paper Briefly ◽  
Flight Testing ◽  
Successful Development ◽  
Range Use

Loran C, a long-range hyperbolic navigation system, is currently used in transoceanic aircraft only to provide periodic position up-dating of primary self-contained navigation systems. The successful development and flight testing of an automatic coordinate converter has recently shown that the potential of the Loran system of navigation is vastly greater than past utilization has indicated. This paper briefly discusses the advantages of combining an increased capability Loran sub-system and an unsophisticated inertial sub-system within the framework provided by a heavy logistics support aircraft.

scholarly journals Identification of the noise structure of micromechanical inertial transducers of motion parameters

2019 ◽  
Vol 29 (2) ◽  
pp. 69-75
Author(s):  
A. M. Lestev ◽  
M. V. Fedorov ◽  
S. D. Evstafiev
Keyword(s):  
Flicker Noise ◽  
Angular Rate ◽  
Linear Acceleration ◽  
Climatic Conditions ◽  
Allan Variance ◽  
Quantization Noise ◽  
Navigation Systems ◽  
Noise Characteristics ◽  
Noise Structure ◽  
Motion Parameters

The article presents the results of the analysis of the noise structure of micromechanical transducers of motion parameters – micromechanical gyroscopes (MMG) and micromechanical accelerometers (MMA) of an experimental measuring unit of strapdown inertial position navigation systems. The unit is manufactured and developed at JSC «GYROOPTICS» (St. Petersburg). It consists of a LL–MMG triad with measuring ranges of ±400°/s and an axial-type MMA triad with measuring ranges of ± 50 g. Micromechanical gyroscopes and accelerometers manufactured using modern microelectronics technologies are among the most promising microsystem technology devices that are widely used as sensors of the primary information of strapdown inertial orientation and navigation systems. The accuracy of the functioning of the inertial orientation and navigation inertial systems is significantly affected by the noise structure of the output signals of the inertial motion parameters sensors. For this reason, the urgent task of identifying the noise of micromechanical gyroscopes and accelerometers. The noise structure of the angular rate and linear acceleration transducers of the tested SINS block was identified by the Allan variance method. The output signals of the transducers were recorded in normal climatic conditions, the sampling interval was 1.0 ms, and the recording duration was 90 minutes. The processing of the output signals of the transducers was carried out on the basis of special software using the AlaVar 5.2 program. It has been established that the predominant noise components of the transducers are the random walk of the output signal – white noise and the instability of the zero signal – flicker noise. No quantization noise was detected in the output signals of the transducers. The values of the noise characteristics in Allan variance of the output signals of the angular rate transducers and the linear acceleration of the test block are compared with the noise characteristics of the most advanced modules produced by foreign companies.

scholarly journals Synergetic Concept of Algorithms Autonomous Inertial Navigation Systems

2012 ◽  
Vol 19 (2) ◽  
pp. 185-197
Author(s):  
Sergey Yakushin
Keyword(s):  
Positive Feedback ◽  
Navigation System ◽  
Inertial Navigation System ◽  
Inertial Navigation ◽  
Feedback Effect ◽  
Navigation Systems ◽  
Inertial Navigation Systems ◽  
System Errors ◽  
The Impact ◽  
Positive Feedback Effect

Abstract Errors of INS output parameters lead to a positive feedback effect of errors and eventually to an even more dramatic increase in system errors. To reduce the impact of this problem on the error output parameters of INS, in this paper, we propose and study a new concept of constructing algorithms for autonomous INS, which is called as synergetic concept. In the paper the synergetic concept of inertial system’s algorithm is presented and investigated by implementing its into strapdown inertial navigation system (SDINS).

scholarly journals Evaluation of permissible amplitudes of external impact on free-of-platform inertial navigation systems

2021 ◽  
pp. 38-43
Author(s):  
Sergii Pogorilov ◽  
Valerij Havin
Keyword(s):  
Navigation System ◽  
Ring Laser ◽  
Inertial Navigation System ◽  
Fiber Optic ◽  
Natural Frequencies ◽  
Inertial Navigation ◽  
Strapdown Inertial Navigation System ◽  
Navigation Systems ◽  
Inertial Navigation Systems ◽  
Strapdown Inertial Navigation

In modern aerospace technology, strapdown inertial navigation systems (SINS) are widely used, using fiber-optic (FOG) or ring laser (CLG) gyroscopes. During the operation of such systems, the sensitivity axes are rotated relative to the basic coordinate system. The resulting angles between the axes of the base coordinate system and the axes of sensitivity of the navigation system (non-orthogonality) are one of the factors leading to an increase in the measurement errors of the device, which affects the measurement accuracy. During operation, the system is affected by vibrations of various nature, the impact of which can contribute to the appearance of non-orthogonality. The purpose of this work is to determine the maximum permissible vibration amplitudes affecting the SINS body according to the permissible values ​​of the deviation of the FOG sensitivity axes for two variants of the SINS layout. An approach to determining the permissible amplitudes of an external harmonic impact on the unit of a strapdown inertial navigation system based on fiber-optic or ring laser gyroscopes is considered. A design scheme, mathematical and finite element models for calculating natural frequencies and forced oscillations of a strapdown inertial navigation system unit have been developed. In various frequency ranges, numerical calculations have determined the boundary values ​​of the amplitudes of the external harmonic impact on the base of specific configurations of the SINS assembly. It has been established that dangerous states take place in the region of the 1st natural frequency of the system, as well as near higher frequencies. Comparison of the results for design options 1 and 2 allows us to conclude that in order to weaken the effect of vibrations on the accuracy of the SINS unit, it is advisable that the lowest natural vibration frequencies for the SINS assembly be as high as possible (more than 1000 Hz). Key words: vibration; fiber optic gyroscope; strapdown inertial navigation system; finite element method; natural frequencies and modes of vibration.

scholarly journals Improving the speed of initial alignment for marine strapdown inertial navigation systems using heading control signal feedback in extended Kalman filter

2020 ◽  
Vol 17 (1) ◽  
pp. 172988141989484 ◽  
Author(s):  
Hossein Rahimi ◽  
Amir Ali Nikkhah
Keyword(s):  
Kalman Filter ◽  
Extended Kalman Filter ◽  
Navigation System ◽  
Inertial Navigation ◽  
Control Signal ◽  
Navigation Systems ◽  
Alignment Method ◽  
Initial Alignment ◽  
Inertial Navigation Systems ◽  
Strapdown Inertial Navigation

In this article, a method was proposed for strapdown inertial navigation systems initial alignment by drawing on the conventional alignment method for stable platform navigation systems. When a vessel is moored, the strapdown inertial navigation system contributes to the disturbing motion. Moreover, the conventional methods of accurate alignment fail to succeed within an acceptable period of time due to the slow convergence of the heading channel in the mooring conditions. In this work, the heading was adjusted using the velocity bias resulting from the component of the angular velocity of the Earth on the east channel on the strapdown inertial navigation systems analytic platform plane to accelerate convergence in the initial alignment of navigation system. To this end, an extended Kalman filter with control signal feedback was used. The heading error was calculated using the north channel residual velocity of the strapdown inertial navigation systems analytic platform plane and was entered into an extended Kalman filter. Simulation and turntable experimental tests were indicative of the ability of the proposed alignment method to increase heading converge speed in mooring conditions.

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