• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2001년도 ICCAS
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• pp.125.2-125
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• 2001

Inertial navigation error is the major source of miss distance when only the inertial navigation system is used for guidance, and tend to monotonically increase if the flight time is small compared to the Schuler period. Miss distance due to these inertial navigation errors, therefore, can be minimized when a missile has the minimum time trajectory. Moreover, vertical component of navigation error becomes null if he impact angle to a surface target approaches to 90 degrees. In this paper, the minimum time trajectories with the steep terminal impact angle constraint are obtained by using CFSQP 2.5, and their properties are analyzed to give a guideline for he construction of an effective guidance algorithm for short range tactical surface-to-surface missiles.

• Nonlinear Functional Analysis and Applications
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• 제27권1호
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• pp.203-221
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• 2022

In this paper, we introduce new hybrid inertial contraction projection algorithms for solving variational inequality problems over the intersection of the fixed point sets of demicontractive mappings in a real Hilbert space. The proposed algorithms are based on the hybrid steepest-descent method for variational inequality problems and the inertial techniques for finding fixed points of nonexpansive mappings. Strong convergence of the iterative algorithms is proved. Several fundamental experiments are provided to illustrate computational efficiency of the given algorithm and comparison with other known algorithms

• Journal of Electrical Engineering and Technology
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• 제8권5호
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• pp.1021-1028
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• 2013

The frequency of a power system should be kept within limits to produce high-quality electricity. For a power system with a high penetration of wind generators (WGs), difficulties might arise in maintaining the frequency, because modern variable speed WGs operate based on the maximum power point tracking control scheme. On the other hand, the wind speed that arrives at a downstream WG is decreased after having passed one WG due to the wake effect. The rotor speed of each WG may be different from others. This paper proposes an algorithm for assigning the droop of each WG in a wind power plant (WPP) based on the rotor speed for the virtual inertial control considering the wake effect. It assumes that each WG in the WPP has two auxiliary loops for the virtual inertial control, i.e. the frequency deviation loop and the rate of change of frequency (ROCOF) loop. To release more kinetic energy, the proposed algorithm assigns the droop of each WG, which is the gain of the frequency deviation loop, depending on the rotor speed of each WG, while the gains for the ROCOF loop of all WGs are set to be equal. The performance of the algorithm is investigated for a model system with five synchronous generators and a WPP, which consists of 15 doubly-fed induction generators, by varying the wind direction as well as the wind speed. The results clearly indicate that the algorithm successfully reduces the frequency nadir as a WG with high wind speed releases more kinetic energy for the virtual inertial control. The algorithm might help maximize the contribution of the WPP to the frequency support.

• 전기학회논문지
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• 제62권7호
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• pp.918-924
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• 2013

In a conventional power system, the frequency is recovered to the nominal value by the inertial, primary, and secondary responses of the synchronous generators (SGs) after a large disturbance such as a generator tripping. For a power system with high wind penetration, the system inertia is significantly reduced due to the maximum power point tracking control based operation of the variable speed wind generators (WGs). This paper proposes a virtual inertial control for a wind power plant (WPP) based on the maximum rate of change of frequency to release more kinetic energy stored in the WGs. The performance of the proposed algorithm is investigated in a model system, which consists of a doubly fed induction generator-based WPP and SGs using an EMTP-RV simulator. The results indicate that the proposed algorithm can improve the frequency nadir after a generator tripping. In addition, the algorithm can lead the instant of a frequency rebound and help frequency recovery after the frequency rebound.

• 제어로봇시스템학회논문지
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• 제16권12호
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• pp.1167-1175
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• 2010

This paper presents the use of the inertial measurement unit information and the infrared sector information for getting the position of an object. Travel distance is usually calculated from the double integration of the accelerometer output with respect to time; however, the accumulated errors due to the drift are inevitable. The orientation change of the accelerometer also causes error because the gravity is added to the measured acceleration. Unless three axis orientations are completely identified, the accelerometer alone does not provide correct acceleration for estimating the travel distance. We propose a way of minimizing the error due to the change of the orientation. In order to reduce the accumulated error, the infrared sector information is fused with the inertial measurement unit information. Infrared sector information has highly deterministic characteristics, different from RFID. By putting several infrared emitters on the ceiling, the floor is divided into many different sectors and each sector is set to have a unique identification. Infrared light based sector information tells the sector the object is in, but the size of the uncertainty is too large if only the sector information is used. This paper presents an algorithm which combines both the inertial measurement unit information and the sector information so that the size of the uncertainty becomes smaller. It also introduces a framework which can be used with other types of the artificial landmarks. The characteristics of the developed infrared light based sector and the proposed algorithm are verified from the experiments.

• 대한기계학회논문집A
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• 제39권2호
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• pp.179-185
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• 2015

가속도계의 신호는 운동체의 가속도와 다르며, 운동체의 자세가 변화하는 경우 가속도계 단독으로 센서가속도를 계측할 수 없다. 본 논문에서는 3 축 가속도계와 3 축 자이로스코프로 구성된 6 축관성센서 신호를 바탕으로 운동체의 자세가 지속적으로 변화하는 가운데 가속도를 정확히 추정할 수 있는 칼만필터를 제안한다. 제안하는 알고리즘은 센서의 자세뿐 아니라 센서가속도가 상태벡터의 일부로 설정되어 있는 새로운 구조의 칼만필터로써, 센서 가속도를 명시적으로 정확히 구할 수 있다. 제안된 필터는 다양한 조건하에서 광학모션캡쳐시스템을 이용하여 그 정확성이 검증되었는데, 최신 Xsens MTw 센서와 동등수준의 성능이었다. 제안된 알고리즘은 6 축 관성센서를 바탕으로 운동체의 가속도 추정이 필요한 다양한 모션센서 응용분야에 적용될 수 있다.

• 한국해양공학회지
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• 제17권6호
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• pp.83-90
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• 2003

This paper presents an underwater hybrid navigation system for a semi-autonomous underwater vehicle (SAUV). The navigation system consists of an inertial measurement unit (IMU), and a Doppler velocity log (DVL), accompanied by a magnetic compass. The errors of inertial measurement units increase with time, due to the bias errors of gyros and accelerometers. A navigational system model is derived, to include the scale effect and bias errors of the DVL, of which the state equation composed of the navigation states and sensor parameters is 20. The conventional extended Kalman filter was used to propagate the error covariance, update the measurement errors, and correct the state equation when the measurements are available. Simulation was performed with the 6-d.o,f equations of motion of SAUV, using a lawn-mowing survey mode. The hybrid underwater navigation system shows good tracking performance, by updating the error covariance and correcting the system's states with the measurement errors from a DVL, a magnetic compass, and a depth sensor. The error of the estimated position still slowly drifts in the horizontal plane, about 3.5m for 500 seconds, which could be eliminated with the help of additional USBL information.

• 한국항공우주학회지
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• 제47권1호
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• pp.41-48
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• 2019

본 논문은 광학적인 방법을 통해 얻은 3차원 좌표들을 이용하여 항공기 동체와 관성항법센서를 정렬하는 방법에 대하여 다루고 있다. 기존에 가공되어 있는 마운트 홀의 제작 정확도를 신뢰하고 장착하던 관행에서 나아가 관성항법센서의 좌표계와 항공기 동체의 기준좌표계를 보다 정확하게 정렬하기 위한 방법에 대해 소개하고 있으며, 실현가능성을 검증하기 위해 실제 3차원 좌표측정장치의 오차 수준을 반영한 시뮬레이션을 통해 정렬 성능을 검증하였다. 또한 광학센서와 관성항법센서의 최적화 기법 기반 정렬 방법을 기술하였다.

• International Journal of Aeronautical and Space Sciences
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• 제11권3호
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• pp.184-192
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• 2010

In this paper, an initial fine alignment algorithm, which is developed for the strap-down inertial navigation systems of satellite launch vehicles, is considered. For fast and accurate alignment, a simple closed-loop estimation algorithm using a proportional-integral controller is introduced. Through computer simulation for the sway condition in the launch pad, it is shown that a simple filter structure can guarantee fast computational speed that is adequate for real-time implementation as well as the required alignment accuracy and robustness. In addition, its implementation results are presented for the Naro-1 flight test.

• 대한교통학회지
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• 제25권2호
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• pp.157-165
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• 2007

본 연구에서는 GPS(Global Positioning System), INS(Inertial Navigation System), DMI(Distance Measuring Unit) 등 각종 센서를 장착한 차량을 이용하여 차량의 위치정보와 자세정보를 취득하고, 취득된 차량의 주행정보를 이용하여 도로 종단선형을 분석할 수 있는 알고리즘을 개발하였다. 개발된 종단선형 분석 알고리즘은 도로의 종단경사, 종단곡선 시종점 및 도로 종단곡선 길이 등을 분석할 수 있고, 종단경사와 종단곡선을 모형화하였다. 또 개발한 알고리즘의 현장 적용성을 검증하기 위하여, 실제 도로에서 취득한 데이터를 이용하여 종단선형을 분석하였고, 이 결과를 도면과 비교하였다.