• Journal of Advanced Navigation Technology
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• v.4 no.2
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• pp.132-142
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• 2000

This paper includes a study on the performance analysis of SDINS by a simulator using Matlab/Simulink. The performance model is considered gravity and Coriolis force, and a barometer is included to damp down diversity of a perpendicular axis error. Using the simulator, the performance included gyro sensor errors was analyzed in various maneuvering patterns. Also, the performance is virtually presented for the variation of error parameters of gyro and accelerometer under GUI.

• KSII Transactions on Internet and Information Systems (TIIS)
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• v.16 no.12
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• pp.4081-4098
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• 2022

With the aim of tackling the contradiction between computation intensive industrial applications and resource-weak Edge Devices (EDs) in Industrial Internet of Things (IIoT), a novel computation task offloading scheme in SDIN-enabled MEC based IIoT is proposed in this paper. With the aim of reducing the task accomplished latency and energy consumption of EDs, a joint optimization method is proposed for optimizing the local CPU-cycle frequency, offloading decision, and wireless and computation resources allocation jointly. Based on the optimization, the task offloading problem is formulated into a Mixed Integer Nonlinear Programming (MINLP) problem which is a large-scale NP-hard problem. In order to solve this problem in an accessible time complexity, a sub-optimal algorithm GPCOA, which is based on hybrid evolutionary computation, is proposed. Outcomes of emulation revel that the proposed method outperforms other baseline methods, and the optimization result shows that the latency-related weight is efficient for reducing the task execution delay and improving the energy efficiency.

• 제어로봇시스템학회:학술대회논문집
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• 1986.10a
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• pp.295-297
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• 1986

In this study, the strap down INS on an earth satellite launch vehicle is simulated with different computing cycles between processing the IMU signals and the navigation computation. At the time of separation of booster, error are discussed. The acceptable computing cycles can be determined by simulation.

• Proceedings of the KIEE Conference
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• 1987.07a
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• pp.165-168
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• 1987

• 제어로봇시스템학회:학술대회논문집
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• 1988.10a
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• pp.633-638
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• 1988

In this paper, a zero-velocity update technique to improve navigation accuracy of a SDINS(Strapdown Inertial Navigation System) has been studied. An indirect feedback Kalman filter which includes SDINS error equations based on a quaternion between body-fixed frame and local level navigation frame is employed for processing zero-velocity updates in an on-board navigation filter. Simulation results for land-mobile vehicle show that the zerovelocity update technique make a significant contribution to improving SDINS performance without any external aids.

• 제어로봇시스템학회:학술대회논문집
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• 1989.10a
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• pp.39-44
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• 1989

This Paper addressed to some aspects of a multirate filtered strapdown INS which is aided by a tracking radar. A new method to determine the sample periods of a multirate filter has been described. The Monte Carlo simulation has been conducted with the optimum sample periods to determine the estimation precision capabilities in a realistic environment. The multirate filtered strapdown navigation system has advantages when the computation time is severely restricted.

• 제어로봇시스템학회:학술대회논문집
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• 1986.10a
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• pp.290-294
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• 1986

Initial alignment of gimballed INS is accomplished by the gyrocompassing techniques. These cannot be used in the case of strapdown system where the inertial instruments are directly strapped down to a vehicle frame. The basic objective of this paper is the development of digital methods performing the initial alignment of a SDINS from vibration and sway currupted data on the launch pad.

• Proceedings of the KIEE Conference
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• 2000.07d
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• pp.2362-2364
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• 2000

본 논문에서는 자세결정 GPS 수신기에서 출력되는 자세정보와 영속도 정보를 이용하여 SDINS의 새로운 초기정렬 알고리즘을 제안하였다. GPS 수신기의 자세정보와 영속도 정보를 이응하기 위해 새롭게 측정모델을 도출하였으며 가관측성을 조사하여 피치각이 90도가 아닌 경우에 시스템이 완전가관측함을 보였다. Monte-Carlo 시뮬레이션을 통하여 SDINS 오차가 빠르게 영으로 수렴함을 보였다.

• Journal of the Korean Society for Precision Engineering
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• v.4 no.4
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• pp.56-71
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• 1987

Determination of navigation variables (latitude, longitude, and altitude) near the earth's surface is termed 'Terrestrial Navigation'. The quantities that are measured inertially are the total acceleration (or the integral fo this acceleration over a fixed time interval) and the total angular rate (or the integral of this angular rate over the same time interval). These measurements when suitably compensated can be manipulated to yield the navigation variables. Hence, it is essential that the initial values of position, orientation and velocity are accurately set up during the initial alignment process. Initial alignment of gimballed inertial navigation system ( GINS) is accomplished by gyrocompassing techniques. These cannot be used, in the case of strapdown inertial navigation system(SDINS), where the inertial instruments are directly strapped down to a vehicle frame. The basic objective of this paper is the development of digital method for the determination of the initial axes erection of a SDINS from vibration and sway currupted data on the launch pad.

• Journal of the Korea Institute of Military Science and Technology
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• v.9 no.3
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• pp.132-140
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• 2006

In this paper, a new fault detection method for the extended Kalman filter, which uses a N-step predictor, is proposed. The N-step predictor performs the only time propagations for N-step intervals without measurement updates and its output is used as a monitoring signal for the fault detection. A consistency between the extended Kalman filter and the N-step predictor is tested to detect a fault. A test statistic is defined by the difference between the extended Kalman filter and the N-step predictor. The proposed method is applied to strapdown inertial navigation system (SDINS). By computer simulation, it is shown that the proposed method detects a fault effectively.