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A Robust Method of Vehicle Stability Accurate Measurement Using GPS and INS

Multimedia Signal Processing, 6 (5), 1029-1042. [13] Yang, F., Li, Y., Ku, H., Rong, X., Song, R. (2010). Attached to real-time estimation of coefficient of extended state observer based on the pavement. Journal of Agricultural Machinery, 41 (8), 6-9. [14] Yu, M., Qian, L. (2005). Vehicle movement measurement based on RTK five wheels. Automotive Engineering, 27 (1), 54-56. [15] Zhang, S. (2006) Research on algorithm for vehicle state testing system based on INS and GPS. Thesis, Jilin University, China. [16

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H filter for flexure deformation and lever arm effect compensation in M/S INS integration

-18. Huang, K., Shan, F.L. and Yang, G.L., 2005. Angular rate matching method for shipboard transfer alignment. Journal of Chinese Inertial Technology, 13(4), pp.1-5. Hong, S., Lee, M.H., Chun, H.H., Kwon, S.H., Speyer, J.L., 2006. Experimental study on the estimation of lever arm in GPS/INS. IEEE Transaction on Vehicular Technology, 55 (2), pp.431-448. Lim, Y.C. and Lyou, J., 2002. Transfer alignment error compensator design using H∞ filter. Proceedings of the American Control Conference, Anchorage, AK, United states, 8 May 2002, pp.1460

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Integrated Attitude and Navigation System for Small Airplane

References [1] Diskhit, V., Mahapatra, P., Medium-Coupled Bus-Based INS-GPS Sensor Fusion for Accurate and Reliable Positioning, Digital Communications – Enhanced Surveillance of Aircraft and Vehicles, 2008. [2] Jwo, D., Development of a Strapdown Inertial Navigation System Simulation Platform , Journal of Marine Science and Technology, Vol. 22, No. 3, pp. 381-391, 2014. [3] Leutenegger, S., Siegwart, R., A Low-Cost and Fail-Safe Inertial Navigation System for Airplanes, IEEE International Conference on Robotics and Automation, pp. 612

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Synergetic Concept of Algorithms Autonomous Inertial Navigation Systems

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).

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Kalman Filter Realization for Orientation and Position Estimation on Dedicated Processor

Wiley & Sons. 5. Caron F., Duflos E., Pomorski D., Vanheegho P. (2006), GPS/IMU Data Fusion using Multisensor Kalman Filtering: Introduction of Contextual Aspects, Information Fusion , 7, 221-230. 6. Chen T., Xu S. (2010), Double Line-of-sight Measuring Relative Navigation for Spacecraft Autonomous Rendezvous, Acta Astro-nautica , 67, 122-134. 7. Franca Junior J. A., Morgado J. A. (2010), Real Time Implementation of a Low-Cost INS/GPS System using xPC Target, Journal of Aerospace Engineering, Sciences and Applications , Vol. 2, No. 3 8. Gibbs B. P

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In Vitro Investigation of Potential Anti-Diabetic Activity of the Corm Extract of Hypoxis Argentea Harv. Ex Baker

berberine, J. Enzyme Inhib. Med. Chem. 24 (2009) 1061-1066; https://doi.org/10.1080/14756360802610761 18. S. Schmidt, M. Jakab, S. Jav, D. Streif, A. Pitchmann, M. Zehl, S. Purevsuren, S. Glasl and M. Ritter, Extracts from Leonurus sibiricus L. increase insulin secretion and proliferation of rat INS-1E insulinoma cells, J. Ethnopharmacol. 150 (2013) 85-94; https://doi.org/10.1016/j.jep.2013.08.013 19. D. Liu, W. Zhen, Z. Yang, J. D. Carter, H. Si and K. A. Reynolds, Genistein acutely stimulates insulin secretion in pancreatic β cells

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The Location GNSS Modules for the Components of Proteus System

The Location GNSS Modules for the Components of Proteus System

The Proteus system - the Integrated Mobile System for Counterterrorism and Rescue Operations is a complex innovative project. To assure the best possible localization of mobile components of the system, many different Global Navigation Satellite System (GNSS) modules were taken into account. In order to chose the best solution many types of tests were done. Full results and conclusions are presented in this paper.

The idea of measurements was to test modules in GPS Standard Positioning Service (SPS) with EGNOS system specification according to certain algorithms. The tests had to answer the question: what type of GNSS modules should be used on different components with respect to specific usage of Proteus system. The second goal of tests was to check the solution quality of integrated GNSS/INS (Inertial Navigation System) and its possible usage in some Proteus system components.

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Safety Evaluation of Ship's Maneuvers Carried Out on the Basis of Integrated Navigation Systems (INS) Indications

Safety Evaluation of Ship's Maneuvers Carried Out on the Basis of Integrated Navigation Systems (INS) Indications

In the safety evaluation of maneuvers carried out on the basis of INS indications, the real ship's dimensions are used to determine navigation safety level. The paper presents a new approach to this problem. The ship's maneuvering area and collision probability were calculated incorporating uncertainty areas of ship's plan geometry at given probability level for typical configuration of navigational equipment applied in existing pilot systems. The widening coefficients of safety factors for each configuration set were determined and discussed.

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Układ Sterowania Bombą Lotniczą

Układ Sterowania Bombą Lotniczą

W artykule przedstawiony został model sterowania aerodynamicznego bombą. Do symulacji przyjęto ogólny model bomby lotniczej. Założenie to pozwala na zbudowanie uniwersalnego układu sterowania, który można zaimplementować do dowolnego rodzaju bomby sterowanej aerodynamicznie. Ważnym elementem adaptacji układu do bomby jest określenie jej wymiarów geometrycznych, z których za pomocą metod numerycznych lub doświadczalnych należy określić współczynniki aerodynamiczne. Sterowanie bombą po zadanym torze lotu jest korygowane i kontrolowane przez INS/GPS.

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Development of an Integrated Digital Elevation Model for Safe Takeoff and Landing of the Aircraft

ABSTRACT

The article describes preliminary results of the augmentation of Global Navigation Satellite System/Inertial Navigation System positioning (GNSS/INS) by Digital Elevation Model (DEM) based on the data from the Shuttle Radar Topography Mission (SRTM) and data from field survey.

The prototype software is developed to refer the position of the aircraft to DEM and informs the user about the current relevant flight parameters. The number of the parameters may be arbitrarily increased, however, currently we investigate the altitude above the terrain and the aircraft position relative to the descent path and airfield.

The study provides some information on the local SRTM accuracy in relation to the field survey of the airfield "Dajtki" - Aeroclub of Warmia and Mazury in Olsztyn.

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