Improvement of CEP Accuracy for Vehicles Re-entry Using INS/GPS/GNSS Integrated System
EL- Hennawy, H., Arafa, I., Fekry, A. (2017). Improvement of CEP Accuracy for Vehicles Re-entry Using INS/GPS/GNSS Integrated System. EKB Journal Management System, 17(AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT - 17 – April 11 - 13, 2017), 1-11. doi: 10.21608/asat.2017.22458
Hadia M. S. EL- Hennawy; Ibrahim I. Arafa; Alaa M. Fekry. "Improvement of CEP Accuracy for Vehicles Re-entry Using INS/GPS/GNSS Integrated System". EKB Journal Management System, 17, AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT - 17 – April 11 - 13, 2017, 2017, 1-11. doi: 10.21608/asat.2017.22458
EL- Hennawy, H., Arafa, I., Fekry, A. (2017). 'Improvement of CEP Accuracy for Vehicles Re-entry Using INS/GPS/GNSS Integrated System', EKB Journal Management System, 17(AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT - 17 – April 11 - 13, 2017), pp. 1-11. doi: 10.21608/asat.2017.22458
EL- Hennawy, H., Arafa, I., Fekry, A. Improvement of CEP Accuracy for Vehicles Re-entry Using INS/GPS/GNSS Integrated System. EKB Journal Management System, 2017; 17(AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT - 17 – April 11 - 13, 2017): 1-11. doi: 10.21608/asat.2017.22458

Improvement of CEP Accuracy for Vehicles Re-entry Using INS/GPS/GNSS Integrated System

International Conference on Aerospace Sciences and Aviation Technology
Article 32, Volume 17, AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT - 17 – April 11 - 13, 2017, April 2017, Page 1-11  XML PDF (737.43 K)
Document Type: Original Article
DOI: 10.21608/asat.2017.22458
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Authors
Hadia M. S. EL- Hennawy1; Ibrahim I. Arafa2; Alaa M. Fekry2
1Ain Shams University, Cairo, Egypt.
2Egyptian Armed Forces, Egypt.
Abstract
This paper describes the theoretical and practical stages through development to testing of an integrated navigation system, specifically composed of an Inertial Navigation System (INS), and Global Positioning System (GPS). Among various INS/GPS integration strategies, our aim is to construct a mathematical model of INS and GPS systems. A Kalman filter is designed and implemented depending upon these models. Besides these, the performance of the developed system is evaluated with real data recorded by the sensors. A comparison with a reference system and also with a loosely coupled system is done to show the Superiority of the tightly coupled structure. The strap down inertial navigation system (SINS) uses (ENU) frame and the integrated system uses position and velocity as measurements. The system model of the integrated system for Kalman filtering are derived and modeled as 27-states. These states estimation system showed clearly the application of fundamental modeling and filtering techniques. The simulation is built on the integrated system INS/GPS/GNSS and the trajectory generator data for flight simulation to be used as a base line algorithm contributing for design, analysis and develop a guidance and control strategy which compensates for the effects of the uncertainties accompanying the navigation systems produced by INS alignment.
Keywords
Inertial Navigation Systems and Kalman Filtering; GPS; Initial Alignment
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