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Time filter

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Hanyang, South Korea

Koo M.S.,Chungnam National University | Ji H.-M.,Chungnam National University | Lim D.W.,Korea Aerospace Research Institute | Oh S.H.,Hanyang Navicom Co. | Hwang D.-H.,Chungnam National University
International Conference on Control, Automation and Systems | Year: 2011

In the ultra-tightly coupled GPS/INS integrated navigation system, the integrated Kalman filter plays the role of the signal tracking loop filters. This type of integration system is known to provide better navigation performance than other types of integration systems. In the ultra-tightly coupled system, the NCO commands are generated from the compensated SDINS output and calculated satellite position and velocity. In this paper, a method for generating NCO command is presented. In order to show the validity of the presented method a simulation system for an ultra-tightly coupled integrated navigation system was configured, in which a discriminator was used. © 2011 ICROS.


Park D.-B.,Agency for Defense Development | Shin D.-H.,Agency for Defense Development | Oh S.-H.,Hanyang Navicom Co. | Kim H.S.,Chungnam National University
IEEE Aerospace and Electronic Systems Magazine | Year: 2012

A GPS/INS system was designed with dual-coupled method for the GPS Adapter Kit (GAK). The navigation system has dual-coupled methods due to the installation configuration of the GAK. Before the GGB jettison, GGB is navigated in loosely-coupled GPS/INS navigation, while a tightly-coupled GPS/INS navigation is used after jettison. For this GAK project, the tactical-grade (gyro bias of 50°/hr) SiIMU02 MEMS IMU (Atlantic Inertial Systems) was selected. After the GGB jettison, the navigation software carries out a tightly-coupled GPS/INS navigation with the pseudo-range and the pseudo-range rate. The interruption of POU data shows no communication interruption during the test. The flight test results show that the navigation system meets the performance requirements for position.


Oh S.H.,Chungbuk National University | Hwang D.-H.,Hanyang Navicom Co. | Park C.,Hanyang Navicom Co. | Lee S.J.,Hanyang Navicom Co.
Journal of Electrical Engineering and Technology | Year: 2012

GPS attitude outputs or carrier phase observables can be effectively utilized to compensate the attitude error of the strapdown inertial navigation system. However, when the integer ambiguity is not correctly resolved and/or a cycle slip occurs, an erroneous GPS output can be obtained. If the erroneous GPS output is applied to the attitude determination GPS/INS (ADGPS/INS) integrated navigation system, the performance of the system can be degraded. This paper proposes an ADGPS/INS integration system using the triple difference carrier phase observables. The proposed integration system contains a cycle slip detection algorithm, in which the inertial information is combined. Computer simulations and flight test were performed to verify effectiveness of the proposed navigation system. Results show that the proposed system gives an accurate and reliable navigation solution even when the integer ambiguity is not correctly resolved and the cycle slip occurs.

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