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Journal articles on the topic 'Inertial navigation systems'

Author: Grafiati

Published: 4 June 2021

Last updated: 30 July 2024

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1

Kortunov, V. I., I. Yu Dybska, G. A. Proskura, and T. Trachsel. "Accuracy Analysis of Strapdown Inertial Navigation Systems." Kosmìčna nauka ì tehnologìâ 13, no. 4 (July 30, 2007): 40–48. http://dx.doi.org/10.15407/knit2007.04.040.

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2

Turygin, Yuri, Pavol Božek, Yuri Nikitin, Ella Sosnovich, and Andrey Abramov. "Enhancing the reliability of mobile robots control process via reverse validation." International Journal of Advanced Robotic Systems 13, no. 6 (December 1, 2016): 172988141668052. http://dx.doi.org/10.1177/1729881416680521.

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The article deals with integrating the inertial navigation unit implemented into the system of controlling the robot. It analyses the dynamic properties of the sensors of the inertial unit, for example, gyroscopes and accelerometers. The implementation of the original system of controlling the mobile robot on the basis of autonomous navigation systems is a dominant part of the article. The integration of navigational information represents the actual issue of reaching higher accuracy of required navigational parameters using more or less accurate navigation systems. The inertial navigation is

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3

Szelmanowski, Andrzej, Mirosław Nowakowski, Zbigniew Jakielaszek, and Piotr Rogala. "Computer-based method for the technical condition evaluation of the Cardan inertial navigation system for the highly maneuverable aircraft." AUTOBUSY – Technika, Eksploatacja, Systemy Transportowe 20, no. 1-2 (February 28, 2019): 344–51. http://dx.doi.org/10.24136/atest.2019.064.

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Paper presents the original computer-based method of the technical condition evaluation of the analog inertial navigation systems on the basis of the calculated inertial speed course analysis. There are presented the mathematical relationships describing the influence of the angular velocity and linear accelerations sensors errors (used in inertial navigation systems on board the military aircraft) with the relation to the discrepancies of the calculated pilot-navigational parameters (such as inertial speed components and navigational position coordinates). On the example of the Cardan navigat

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4

He, Hongyang, Feng Zha, Feng Li, and Qiushuo Wei. "A Combination Scheme of Pure Strapdown and Dual-Axis Rotation Inertial Navigation Systems." Sensors 23, no. 6 (March 14, 2023): 3091. http://dx.doi.org/10.3390/s23063091.

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Compared with the strapdown inertial navigation system (SINS), the rotation strapdown inertial navigation system (RSINS) can effectively improve the accuracy of navigation information, but rotational modulation also leads to an increase in the oscillation frequency of attitude errors. In this paper, a dual-inertial navigation scheme that combines the strapdown inertial navigation system and the dual-axis rotation inertial navigation system is proposed, which can effectively improve the attitude error accuracy in the horizontal direction by using the high-position information of the rotation in

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5

Novikov, P. V., A. A. Sheypak, V. N. Gerdi, V. V. Novikov, and V. N. Enin. "Algorithm for navigation of ground-based transport-technological facilities on the basis of integrated inertial-satellite navigation and odometer data." Izvestiya MGTU MAMI 11, no. 2 (June 15, 2017): 31–39. http://dx.doi.org/10.17816/2074-0530-66895.

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The dynamic development of navigation technologies has led to the emergence of practical applications for the solution of the problem of navigation of ground transport and technological facilities (GTTF). The most promising way of solving the navigation problem of GTTF is the creation of integrated inertial-satellite navigation systems. For a long period of time, the widespread use of navigation systems for transport applications was constrained by their high cost. The appearance of low-cost microelectromechanical (MEMS) inertial sensors on the market of navigation equipment provided the techn

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6

Kovalenko, A. M., and A. A. Shejnikov. "Model of the inertial and optical navigation system of the unmanned aerial vehicle." «System analysis and applied information science», no. 2 (August 18, 2020): 17–25. http://dx.doi.org/10.21122/2309-4923-2020-2-17-25.

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In article approaches to creation of the complex inertial and optical navigation system of the short-range tactical unmanned aerial vehicle are considered. Algorithms constant and periodic (in intermediate points of a route) are offered correction of the platformless onboard inertial navigation system. At integration of information on parameters of the movement of the unmanned aerial vehicle (received from the considered systems) the invariant loosely coupled scheme of data processing on the basis of the expanded filter of Kallman was used that allowed to lower significantly a systematic compo

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7

Ushaq, Muhammad, and Jian Cheng Fang. "An Improved and Efficient Algorithm for SINS/GPS/Doppler Integrated Navigation Systems." Applied Mechanics and Materials 245 (December 2012): 323–29. http://dx.doi.org/10.4028/www.scientific.net/amm.245.323.

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Inertial navigation systems exhibit position errors that tend to grow with time in an unbounded mode. This degradation is due, in part, to errors in the initialization of the inertial measurement unit and inertial sensor imperfections such as accelerometer biases and gyroscope drifts. Mitigation to this growth and bounding the errors is to update the inertial navigation system periodically with external position (and/or velocity, attitude) fixes. The synergistic effect is obtained through external measurements updating the inertial navigation system using Kalman filter algorithm. It is a natur

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8

E, Topolskov, Beljaevskiy L. L, and Serdjuke A. "IMPROVEMENT OF NAVIGATION SYSTEMS OF VEHICLES BY MEANS OF INERTIAL SENSORS AND INFORMATION PROCESSING USING PROBABILITY-GEOMETRIC METHODS." National Transport University Bulletin 1, no. 46 (2020): 353–64. http://dx.doi.org/10.33744/2308-6645-2020-1-46-353-364.

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Providing high accuracy of the coordinates and trajectories of objects by measurements conducted in navigation systems and complexes is an urgent task, which improves safety and efficiency of different modes of transport. However difficult environmental conditions, where vehicles are commonly used, stipulate influence of different factors on performance of onboard satellite navigation receivers, which are used as basic navigation devices for ground vehicle nowadays. Setting on cars used for common purposes additional navigation devices, which provide better performance, in most cases is econom

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9

Vaispacher, Tomáš, Róbert Bréda, and František Adamčík. "Error Analysis of Inertial Navigation Systems Using Test Algorithms." Naše more 62, SI (October 2015): 204–8. http://dx.doi.org/10.17818/nm/2015/si21.

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10

Bodhare, Hemant Gautam, and Asst Prof Gauri Ansurkar. "LEO based Satellite Navigation and Anti-Theft Tracking System for Automobiles." International Journal for Research in Applied Science and Engineering Technology 10, no. 4 (April 30, 2022): 557–63. http://dx.doi.org/10.22214/ijraset.2022.41316.

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Abstract: GPS and Inertial Navigation Systems (INS) are used today in automobile navigation and tracking systems to locate themselves in Four Dimensions (latitude, longitude, altitude, time). However, GNSS or GPS still has its own bottleneck, such as the long initialization period of Precise Point Positioning (PPP) without dense reference network. For navigation, a number of selected LEO satellites can be equipped with a transmitter to transmit similar navigation signals to land users, so they can act like GNSS satellites but with much faster geometric change to enhance GNSS capability, which

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11

Liu, Tianhao, Tianshang Zhao, Huijun Zhao, and Chenguang Wang. "Adaptive Cubature Kalman Filter for Inertial/Geomagnetic Integrated Navigation System Based on Long Short-Term Memory Network." Applied Sciences 14, no. 13 (July 5, 2024): 5905. http://dx.doi.org/10.3390/app14135905.

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Inertial navigation systems experience error accumulation over time, leading to the use of integrated navigation as a classical solution to mitigate inertial drift. This provides a novel approach to navigation and positioning by using the combined advantages of inertial and geomagnetic navigation systems. However, inertial/geomagnetic navigation is affected by significant magnetic interference in practical scenarios, resulting in reduced navigation accuracy. This research introduces a new neural network-assisted integrated inertial–geomagnetic navigation method (IM-NN), and utilizes the adapti

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12

Smith, S. G. "Developments in Inertial Navigation." Journal of Navigation 39, no. 3 (September 1986): 401–15. http://dx.doi.org/10.1017/s0373463300000874.

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Inertial navigation systems represent the ideal in automatic navigation. They operate entirely without external assistance, other than information as to their starting conditions, which makes them of great interest to both military and civil operators.

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13

Chernyak, Mykola, and Vadym Kolesnyk. "Improving Strapdown Inertial Navigation System Performance by Self-Compensation of Inertial Sensor Errors." Transactions on Aerospace Research 2023, no. 4 (December 1, 2023): 41–51. http://dx.doi.org/10.2478/tar-2023-0022.

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Abstract Microelectromechanical systems (MEMS)-based strapdown navigation systems offer advantages such as small size, low cost and minimal power consumption. However, MEMS sensors are prone to significant low-frequency noise and poor bias repeatability, which can lead to navigational errors over time. These errors make them unsuitable for autonomous navigation applications, even with frequent recalibration. One way in which to solve this problem is by using the rotation modulation (RM) method. This approach is widely recognised but has only been successful with precise laser and fiber optic g

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14

Qian, Kun, Jian-Guo Wang, and Baoxin Hu. "Novel Integration Strategy for GNSS-Aided Inertial Integrated Navigation." GEOMATICA 69, no. 2 (June 2015): 217–30. http://dx.doi.org/10.5623/cig2015-205.

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The conventional integration mechanism in GNSS (Global Navigation Satellite Systems) aided inertial integrated positioning and navigation system is mainly based on the continuous outputs of the navigation mechanization, the associated error models for navigation parameters, the biases of the inertial measurement units (IMU), and the error measurements. Its strong dependence on the a priori error characteristics of inertial sensors may suffer with the low-cost IMUs, e.g. the MEMS IMUs due to their low and unstable performance. This paper strives for a significant breakthrough in a compact and g

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15

Wang, Lin, Wenqi Wu, Guo Wei, Jinlong Li, and Ruihang Yu. "A Novel Information Fusion Method for Redundant Rotational Inertial Navigation Systems Based on Reduced-Order Kalman Filter." MATEC Web of Conferences 160 (2018): 07005. http://dx.doi.org/10.1051/matecconf/201816007005.

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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 rota

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16

Karachun, V. V., Ya F. Kayuk, and V. N. Mel'nik. "Wave tasks of inertial navigation systems." Kosmìčna nauka ì tehnologìâ 13, no. 6 (November 30, 2007): 39–45. http://dx.doi.org/10.15407/knit2007.06.039.

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17

Barshan, B., and H. F. Durrant-Whyte. "Inertial navigation systems for mobile robots." IEEE Transactions on Robotics and Automation 11, no. 3 (June 1995): 328–42. http://dx.doi.org/10.1109/70.388775.

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18

Abo El Soud, M., E. Zakzouk, A. Hamad, and M. El-Dakiky. "ERROR ANALYSIS OF INERTIAL NAVIGATION SYSTEMS." International Conference on Aerospace Sciences and Aviation Technology 2, CONFERENCE (April 1, 1987): 1–9. http://dx.doi.org/10.21608/asat.1987.26201.

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19

Trifonov-Bogdanov, Peter, Anastasia Zhiravetska, Tatjana Trifonova-Bogdanova, and Vladimir Shestakov. "MECHANISMS OF ERROR DEVELOPMENT IN INERTIAL NAVIGATION SYSTEMS." Aviation 16, no. 2 (June 29, 2012): 33–37. http://dx.doi.org/10.3846/16487788.2012.701872.

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The processes of error development in an inertial navigation system are analysed. With this aim, the standard structures of error development were extracted in the inertial system. Error development was defined in the standard structures. Error development in the inertial navigation system is concluded according to the results obtained in the work.

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20

Chi Vi, Nguyen, Le Ngoc Giang, and Nguyen Văn Thong. "Research and calculate flight navigation parameters using data from the angular speed sensor and long acceleration sensor." International Journal of Multidisciplinary Research and Growth Evaluation 4, no. 1 (2023): 347–51. http://dx.doi.org/10.54660/.ijmrge.2023.4.1.347-351.

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Today, along with the development of science and technology, inertial navigation systems are applied with precision sensors and high-speed specialized digital computers. With the advantages of compactness and ease of integration and installation on aircraft, this type of navigation system is effectively applied to small and medium-sized unmanned aerial vehicles. When combined with other systems of the same function, such as satellite navigation systems, radio altimeter systems, barometric altimeter systems, etc., this system allows for the provision of angle and position information with high

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21

Fariz, Outamazirt, Muhammad Ushaq, Yan Lin, and Fu Li. "Enhanced Accuracy Navigation Solutions Realized through SINS/GPS Integrated Navigation System." Applied Mechanics and Materials 332 (July 2013): 79–85. http://dx.doi.org/10.4028/www.scientific.net/amm.332.79.

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Strapdown Inertial Navigation Systems (SINS) displays position errors which grow with time in an unbounded manner. This degradation is due to the errors in the initialization of the inertial measurement unit, and inertial sensor imperfections such as accelerometer biases and gyroscope drifts. Improvement to this unbounded growth in errors can be made by updating the inertial navigation system solutions periodically with external position fixes, velocity fixes, attitude fixes or any combination of these fixes. The increased accuracy is obtained through external measurements updating inertial na

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22

Chen, Danhe, Konstantin Neusypin, Maria Selezneva, and Zhongcheng Mu. "New Algorithms for Autonomous Inertial Navigation Systems Correction with Precession Angle Sensors in Aircrafts." Sensors 19, no. 22 (November 17, 2019): 5016. http://dx.doi.org/10.3390/s19225016.

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This paper presents new algorithmic methods for accuracy improvement of autonomous inertial navigation systems of aircrafts. Firstly, an inertial navigation system platform and its nonlinear error model are considered, and the correction schemes are presented for autonomous inertial navigation systems using internal information. Next, a correction algorithm is proposed based on signals from precession angle sensors. A vector of reduced measurements for the estimation algorithm is formulated using the information about the angles of precession. Finally, the accuracy of the developed correction

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23

He, Qinyuan, Huapeng Yu, Dalei Liang, and Xiaozhuo Yang. "Enhancing Pure Inertial Navigation Accuracy through a Redundant High-Precision Accelerometer-Based Method Utilizing Neural Networks." Sensors 24, no. 8 (April 17, 2024): 2566. http://dx.doi.org/10.3390/s24082566.

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The pure inertial navigation system, crucial for autonomous navigation in GPS-denied environments, faces challenges of error accumulation over time, impacting its effectiveness for prolonged missions. Traditional methods to enhance accuracy have focused on improving instrumentation and algorithms but face limitations due to complexity and costs. This study introduces a novel device-level redundant inertial navigation framework using high-precision accelerometers combined with a neural network-based method to refine navigation accuracy. Experimental validation confirms that this integration sig

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24

Zhuravlev, V. Ph. "The New Type of Inertial Navigation Systems." Прикладная математика и механика 87, no. 4 (July 1, 2023): 513–18. http://dx.doi.org/10.31857/s0032823523040161.

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An inertial system of a new type has the smallest possible dimension. It differs from the already known inertial systems, platform and strapdown, in that it allows you to do without gyroscopes and blocks for integrating Poisson’s equations, simultaneously combining the functions of an apparent acceleration sensor.

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25

Guan, Bofan, Zhongping Liu, Dong Wei, and Qiangwen Fu. "Design of a Multi-Position Alignment Scheme." Sensors 24, no. 6 (March 18, 2024): 1938. http://dx.doi.org/10.3390/s24061938.

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The current new type of inertial navigation system, including rotating inertial navigation systems and three-autonomy inertial navigation systems, has been increasingly widely applied. Benefited by the rotating mechanisms of these inertial navigation systems, alignment accuracy can be significantly enhanced by implementing IMU (Inertial Measurement Unit) rotation during the alignment process. The principle of suppressing initial alignment errors using rotational modulation technology was investigated, and the impact of various component error terms on alignment accuracy of IMU during rotation

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26

Lin, Boyu, and Hutao Cui. "Research on A Low Computational Cost Vision-aided Inertial Navigation Method for Precision Landing on Asteroid." Journal of Physics: Conference Series 2203, no. 1 (February 1, 2022): 012020. http://dx.doi.org/10.1088/1742-6596/2203/1/012020.

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Abstract Asteroid exploration missions demand more autonomous navigation system that are precise and in real-time. Visual-aided inertial navigation systems combine the advantages of autonomy of inertial navigation systems and accuracy of visual navigation systems. However, both increase the computational burden for the information processing. With the goal of decreasing the computational load, this paper proposes a low cost vision-aided inertial navigation method which can calculate increment position, velocity and attitude directly in inertial frame by pre-integrating IMU measurements. For vi

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27

Cai, Yunpiao, Weixing Qian, Jiaqi Zhao, Jiayi Dong, and Tianxiao Shen. "Visual–Inertial Navigation System Based on Virtual Inertial Sensors." Applied Sciences 13, no. 12 (June 17, 2023): 7248. http://dx.doi.org/10.3390/app13127248.

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In this paper, we propose a novel visual–inertial simultaneous localization and mapping (SLAM) method for intelligent navigation systems that aims to overcome the challenges posed by dynamic or large-scale outdoor environments. Our approach constructs a visual–inertial navigation system by utilizing virtual inertial sensor components that are mapped to the torso IMU under different gait patterns through gait classification. We apply a zero-velocity update (ZUPT) to initialize the system with the original visual–inertial information. The pose information is then iteratively updated through nonl

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28

Novikov, P. V., A. A. Sheypak, V. N. Gerdi, and V. V. Novikov. "Increase of the accuracy and reliability of output parameters determination of vehicle Integrated Navigation Systems." Izvestiya MGTU MAMI 10, no. 4 (December 15, 2016): 50–56. http://dx.doi.org/10.17816/2074-0530-66919.

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Dynamic development of navigation technologies opens up possibilities for the successful solution of a wide range of navigation tasks of mobile objects. For a long time the extension of the scope of navigation systems for transport applications was constrained by their high cost. The emergence of a small cheap inertial sensors, based on MEMS technology have resulted in integrated navigation systems, including the inertial and satellite GPS/GLONASS inertial modules. For solving problems of navigation of ground vehicles the integrated system is combinated with odometer. Nowadays a number of car

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29

Rahimi, Hossein, and Amir Ali Nikkhah. "Improving the speed of initial alignment for marine strapdown inertial navigation systems using heading control signal feedback in extended Kalman filter." International Journal of Advanced Robotic Systems 17, no. 1 (January 1, 2020): 172988141989484. http://dx.doi.org/10.1177/1729881419894849.

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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

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30

Sokolov, S. V., D. V. Marshakov, and E. G. Chub. "Stable solution to the problem of autonomous navigation of moving objects on analytical trajectory intervals based on the results of inertial measurements." Izmeritel`naya Tekhnika, no. 4 (June 10, 2024): 4–15. http://dx.doi.org/10.32446/0368-1025it.2024-4-4-15.

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Provision of solution of the problem of autonomous navigation on a long time interval is considered. The main problem when using inertial navigation systems is caused by the accumulation of positioning and angular orientation errors. It is shown that this problem can be solved by combining methods of nonlinear filtering in processing the results of inertial measurements of platform-free inertial navigation systems and methods of reducing the dimensionality of the vector of navigation parameters on trajectory sections described by analytical models. Orthodromic (shortest) and circular intervals

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31

Napier, M. "Integration of Satellite and Inertial Positioning Systems." Journal of Navigation 43, no. 1 (January 1990): 48–57. http://dx.doi.org/10.1017/s0373463300013813.

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The Global Positioning System (GPS) offers an absolute positioning accuracy of 15 to 100 metres. Inertial navigation complements GPS in that it provides relative positioning and is totally self-contained. These two positioning sensors are ideally suited for system integration for although there is not necessarily an improvement in accuracy, the integration of GPS with inertial navigation systems (INS) does enable an increase in system performance.

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32

Ibrahim, M. A., and V. V. Luk'yanov. "Algorithms and Configuration for a Moving Object Attitude Control System Based on Microelectromechanical Sensors." Herald of the Bauman Moscow State Technical University. Series Instrument Engineering, no. 2 (131) (June 2020): 44–58. http://dx.doi.org/10.18698/0236-3933-2020-2-44-58.

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Inertial systems for attitude control, stabilisation and navigation of moving objects boast a range of unique qualities, the most important of which are autonomy and interference immunity. At present, strap-down inertial navigation systems using inexpensive and compact microelectromechanical sensors are popular. The biggest disadvantage of the attitude control systems utilising microelectromechanical sensors is rapid error accumulation over time. The main error sources in strap-down inertial navigation systems are the errors of angular velocity sensors and accelerometers. Currently the accurac

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33

Szelmanowski, Andrzej. "Feasibility to Diagnose Inertial Navigation Systems Through Analysis of Schuler Errors." Research Works of Air Force Institute of Technology 33, no. 1 (January 1, 2013): 173–86. http://dx.doi.org/10.2478/afit-2013-0010.

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Abstract The paper is intended to discuss errors in measurements of angular velocity and linear acceleration by means of electronic inertial sensors incorporated into the Attitude and Heading Reference Systems (AHRS) as well as Inertial Navigation Systems (INS). The mathematical equations are found out to establish how these errors affect deviations of flight parameters (such as linear speed and coordinates of the aircraft position indicated by navigation systems) that are calculated from the measurements and imaged e.g. in helmetmounted cueing systems. Some issues related to diagnostics of in

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34

Vasilyuk, Nikolay N. "Integrated GNSS antenna with an embedded inertial measurement unit." Izmeritel`naya Tekhnika, no. 3 (2020): 16–23. http://dx.doi.org/10.32446/0368-1025it.2020-3-16-23.

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When constructing inertial/GNSS navigation systems, it is necessary to determine coordinates of a GNSS antenna relative to an inertial measurement unit. It is proposed to solve this problem by integrating of the inertial unit and GNSS antenna’s element into a common structure called an integrated antenna. This approach allows to determine the required coordinates in factory conditions, during a manufacturing of the integrated antenna. Operation principles of design modules of the integrated antenna and ways to use this antenna in the inertial/GNSS navigation systems have been described. Design

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35

Shcherban’, I. V., and O. G. Shcherban’. "Algorithm for integrated inertial-satellite navigation systems." Automatic Control and Computer Sciences 48, no. 6 (November 2014): 368–74. http://dx.doi.org/10.3103/s014641161406008x.

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36

Bar-Itzhack, I. Y., and N. Berman. "Control theoretic approach to inertial navigation systems." Journal of Guidance, Control, and Dynamics 11, no. 3 (May 1988): 237–45. http://dx.doi.org/10.2514/3.20299.

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37

Prokhorov, Y. G. "Observability of gravimeter-aided inertial navigation systems." Journal of Guidance, Control, and Dynamics 18, no. 6 (November 1995): 1416–19. http://dx.doi.org/10.2514/3.21562.

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38

LEE, Man Hyung, Won Chul PARK, Kil Soo LEE, Sinpyo HONG, Hyung Gyu PARK, Ho Hwan CHUN, and Fumio HARASHIMA. "Observability Analysis Techniques on Inertial Navigation Systems." Journal of System Design and Dynamics 6, no. 1 (2012): 28–44. http://dx.doi.org/10.1299/jsdd.6.28.

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39

C.-W. Tan and S. Park. "Design of Accelerometer-Based Inertial Navigation Systems." IEEE Transactions on Instrumentation and Measurement 54, no. 6 (December 2005): 2520–30. http://dx.doi.org/10.1109/tim.2005.858129.

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40

Ghasemzadeh, Vahid, and Mohammad M. Arefi. "Design, modeling, and simulation of an INS system using an asymmetric structure of six accelerometers and its error analysis in the ECEF frame." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 231, no. 13 (August 11, 2016): 2345–61. http://dx.doi.org/10.1177/0954410016662059.

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The inertial navigation system is one of the most important and common methods of navigation. In this system, accelerometers and gyroscopes are used to measure linear accelerations and angular velocities, respectively. Accelerometers have simpler manufacture techniques, lower cost, and smaller volume and weight in comparison with gyroscopes. Therefore, in some application of navigation systems, non-gyro inertial navigation systems based on accelerometers are used. In this paper, an asymmetric structure of six accelerometers is proposed. Then dynamic relations of this structure are extracted. T

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41

Wei, Qiushuo, Feng Zha, Hongyang He, and Bao Li. "An Improved System-Level Calibration Scheme for Rotational Inertial Navigation Systems." Sensors 22, no. 19 (October 7, 2022): 7610. http://dx.doi.org/10.3390/s22197610.

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The system-level calibration technology of rotational inertial navigation is one of the main methods to improve the accuracy of inertial navigation, and the design of the calibration scheme is the key to calibration technology. By the establishment of the error model of inertial navigation system, a 30-position calibration scheme is designed in this study. Based on the 30-dimensional Kalman filter, the constant errors, scale factor errors and installation error of gyroscope and accelerometer are identified. Comparing the traditional schemes and the 30-position scheme with the simulation experi

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42

Yu, Dongming, and Hong Liu. "Relative positioning method for unmanned aerial vehicles in complex electromagnetic environment." Journal of Physics: Conference Series 2764, no. 1 (May 1, 2024): 012100. http://dx.doi.org/10.1088/1742-6596/2764/1/012100.

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Abstract In view of the problem that satellite navigation and positioning systems may fail or be unreliable in complex electromagnetic environments, which may lead to divergence of UAV positioning, the inertial navigation systems working for a long time may lead to increasing errors. This paper adopts a relative navigation algorithm that combines airborne inertial navigation systems and inter-aircraft relative information measurement. The algorithm requires each UAV to load relative navigation equipment and inertial navigation systems and acquire and fuse relative navigation information throug

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Mohamed, H. A., J. M. Hansen, M. M. Elhabiby, N. El-Sheimy, and A. B. Sesay. "PERFORMANCE CHARACTERISTIC MEMS-BASED IMUs FOR UAVs NAVIGATION." ISPRS - International Archives of the Photogrammetry, Remote Sensing and Spatial Information Sciences XL-1/W4 (August 26, 2015): 337–43. http://dx.doi.org/10.5194/isprsarchives-xl-1-w4-337-2015.

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Accurate 3D reconstruction has become essential for non-traditional mapping applications such as urban planning, mining industry, environmental monitoring, navigation, surveillance, pipeline inspection, infrastructure monitoring, landslide hazard analysis, indoor localization, and military simulation. The needs of these applications cannot be satisfied by traditional mapping, which is based on dedicated data acquisition systems designed for mapping purposes. Recent advances in hardware and software development have made it possible to conduct accurate 3D mapping without using costly and high-e

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Zharkov, Maksim, Konstantin Veremeenko, Ivan Kuznetsov, and Andrei Pronkin. "Global Navigation Satellite System Spoofing Detection in Inertial Satellite Navigation Systems." Inventions 8, no. 6 (December 16, 2023): 158. http://dx.doi.org/10.3390/inventions8060158.

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The susceptibility of global navigation satellite systems (GNSSs) to interference significantly limits the possibility of their use. From the standpoint of possible consequences, the most dangerous interference is the so-called spoofing. Simultaneously, in most cases of GNSS use, an inertial navigation system (INS) or an attitude and heading reference system (AHRS) is also present on the board of mobile objects. In this regard, the research goal is to assess the possibility of detecting GNSS spoofing in inertial satellite navigation systems. This paper examines the method for detecting GNSS sp

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Seo, Yeong-Bin, Haesung Yu, Kyungdon Ryu, Inseop Lee, Juhyun Oh, Cheonjoong Kim, Sang Jeong Lee, and Chansik Park. "Analysis of Gyro Bias Depending on the Position of Inertial Measurement Unit in Rotational Inertial Navigation Systems." Sensors 22, no. 21 (October 31, 2022): 8355. http://dx.doi.org/10.3390/s22218355.

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In this paper, a calibration method for gyro bias that changes depending on the position of the IMU (inertial measurement unit) is proposed to improve the navigation performance of RLG-based RINS (ring-laser-gyro-based rotational inertial navigation system). RINS is a navigation device that compensates for the inertial sensor errors by utilizing the rotation of the IMU. In previous studies, the rotation scheme of the IMU is designed assuming that inertial sensor errors are not affected by position of the IMU. However, changes in temperature distribution, direction of gravity, and dithering acc

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Duan, Yabo, Huaizhan Li, Suqin Wu, and Kefei Zhang. "INS Error Estimation Based on an ANFIS and Its Application in Complex and Covert Surroundings." ISPRS International Journal of Geo-Information 10, no. 6 (June 4, 2021): 388. http://dx.doi.org/10.3390/ijgi10060388.

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Inertial navigation is a crucial part of vehicle navigation systems in complex and covert surroundings. To address the low accuracy of vehicle inertial navigation in multifaced and covert surroundings, in this study, we proposed an inertial navigation error estimation based on an adaptive neuro fuzzy inference system (ANFIS) which can quickly and accurately output the position error of a vehicle end-to-end. The new system was tested using both single-sequence and multi-sequence data collected from a vehicle by the KITTI dataset. The results were compared with an inertial navigation system (INS

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Capuano, Vincenzo, Liangchun Xu, and Jose Estrada Benavides. "Smartphone MEMS Accelerometer and Gyroscope Measurement Errors: Laboratory Testing and Analysis of the Effects on Positioning Performance." Sensors 23, no. 17 (September 1, 2023): 7609. http://dx.doi.org/10.3390/s23177609.

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Embedding various sensors with powerful computing and storage capabilities in a small communication device, smartphones have become a prominent platform for navigation. With the increasing popularity of Apple CarPlay and Android Auto, smartphones are quickly replacing built-in automotive navigation solutions. On the other hand, smartphones are equipped with low-performance Micro Electro Mechanical Systems (MEMS) sensors to enhance their navigation performance in Global Navigation Satellite System (GNSS)-degraded or -denied environments. Compared with higher-grade inertial navigation systems (I

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Son, Jae-Hoon, Sang-Heon Oh, and Dong-Hwan Hwang. "Performance Improvement of Global Positioning System/Gyro-Free Inertial Navigation System Integrated Navigation Systems Using Gyroscopes." Journal of Institute of Control, Robotics and Systems 29, no. 6 (June 30, 2023): 510–20. http://dx.doi.org/10.5302/j.icros.2023.23.0010.

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Kwon, Jay Hyoun, and Christopher Jekeli. "Gravity Requirements for Compensation of Ultra-Precise Inertial Navigation." Journal of Navigation 58, no. 3 (August 19, 2005): 479–92. http://dx.doi.org/10.1017/s0373463305003395.

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Precision inertial navigation depends not only on the quality of the inertial sensors (accelerometers and gyros), but also on the accuracy of the gravity compensation. With a view toward the next-generation inertial navigation systems, based on sensors whose errors contribute as little as a few metres per hour to the navigation error budget, we have analyzed the required quality of gravity compensation to the navigation solution. The investigation considered a standard compensation method using ground data to predict the gravity vector at altitude for aircraft free-inertial navigation. The nav

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Moussa, M., A. Moussa, M. Elhabiby, and N. El-Sheimy. "INVESTIGATION OF DIFFERENT LOW-COST LAND VEHICLE NAVIGATION SYSTEMS BASED ON CPD SENSORS AND VEHICLE INFORMATION." ISPRS Annals of Photogrammetry, Remote Sensing and Spatial Information Sciences V-1-2020 (August 3, 2020): 189–97. http://dx.doi.org/10.5194/isprs-annals-v-1-2020-189-2020.

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Abstract. Recently, many companies and research centres have been working on research and development of navigation technologies for self-driving cars. Many navigation technologies were developed based on the fusion of various sensors. However, most of these techniques used expensive sensors and consequently increase the overall cost of such cars. Therefore, low-cost sensors are now a rich research topic in land vehicle navigation. Consumer Portable Devices (CPDs) such as smartphones and tablets are being widely used and contain many sensors (e.g. cameras, barometers, magnetometers, accelerome

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