• Convergence Security Journal
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• v.8 no.2
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• pp.87-94
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• 2008

In this paper, a study on the inertial navigation system technology in guided weapon system development. Navigation devices are being used more commonly in places. Inertial navigation devices attached to them are used as weapons systems have a lot of interest in the development of devices for research and development accelerated. Therefore, this paper will encourage the development of weapon systems Inertial navigation device trends, features and configuration, type, techniques for research work.

• Journal of Advanced Navigation Technology
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• v.22 no.6
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• pp.500-506
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• 2018

In this paper, we considered the one-shot alignment using master inertial navigation system (MINS) and slave inertial navigation system (SINS) in the missile to find the exact posture of a missile. In order to perform one-shot alignment, the tilt angle between MINS and SINS must be obtained, which can be compensated by obtaining the tilt angle between missile round and SINS. The tilt angle was calculated by using the roll rotation of missile round, jig for rotating the missile round and interface structure to measure the horizontal state by using a horizontal angle meter were constructed. As a result of the tilt angle save (TAS) inspection, the tilt angle ${\alpha}$, ${\beta}$, ${\gamma}$ is normal range and it is possible to perform one-shot alignment by compensating this value.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.47 no.1
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• pp.41-48
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• 2019

This paper deals with a method of aligning an aircraft fuselage and an inertial navigation sensor using three-dimensional coordinates obtained by an optical method. In order to verify the feasibility, we introduce the method to accurately align the coordinate system of the inertial navigation sensor and the aircraft reference coordinate system. It is verified through simulation that reflects the error level of the measuring device. In addition, optimization method based alignment algorithm is proposed for connection between optical sensor and inertial navigation sensor.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.39 no.8
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• pp.788-795
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• 2011

In this paper, we present the requirements specification to develop the small ring laser gyroscope(RLG) which is applicable to the medium-grade inertial navigation system(INS) widely used as a main navigation system. To this end, first we analyse the performance specifications of RLG which is needed to configure the medium-grade INS and then we present the design results of RLG to meet the performance specifications, based on the overseas technology survey and the theoretical analysis. It is also shown in this paper what technology is required to develop a small RLG.

• Journal of the Institute of Electronics and Information Engineers
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• v.49 no.11
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• pp.159-166
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• 2012

There are several ways such as GPS(Global Positioning System) and INS (Inertial Navigation System) to track the location of moving vehicle. The GPS has the advantages of having non-accumulative error even if it brings about errors. In order to obtain the position information, we need to receive at least 3 satellites information. But, the weak point is that GPS is not useful when the 혠 signal is weak or it is in the incommunicable region such as tunnel. In the case of INS, the information of the position and posture of mobile with several Hz~several hundreds Hz data speed is recorded for velocity, direction. INS shows a very precise navigational performance for a short period, but it has the disadvantage of increasing velocity components because of the accumulated error during integration over time. In this paper, sensor fusion algorithm is applied to both of INS and GPS for the position information to overcome the drawbacks. The proposed system gets an accurate position information from experiment using SVD in a non-accessible GPS terrain.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.5
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• pp.502-510
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• 2009

Laser Inertial Navigation System(LINS) consists of Ring Laser Gyroscopes(RLG) and accelerometers. RLG has a lock-in region in which there is zero output for input angular rates less than 0.1deg/sec. The lock-in region is generated by the imperfect mirrors in RLG. To avoid the lock-in region, sinusoidal motion which is called dither motion is applied on RLG. Therefore without the fault in LINS, the dither motion must be measured by RLG/accelerometer. In this paper, we propose the method to detect the fault of LINS through checking out whether or not the dither motion is always measured by RLG/accelerometer using the Fast Fourier Transformation(FFT) on the real time. The feasibility of the fault detection method proposed in this paper is verified through the stationary and van test.

• 한국항공운항학회:학술대회논문집
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• 2005.11a
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• pp.132-135
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• 2005

이체 쿼터니언(dual quaternion)은 선형 미분방정식으로 계산하는 쿼터니언을 회전운동과 병진운동을 동시에 취급하는 이체수(dual numbers)체계로 표현한 형태이다. 성능향상을 위해 이체 쿼터니언을 관성항법 알고리즘에 적용시킨 논문이 새로이 소개되었다. 기존 알고리즘과 새로운 알고리즘을 MATLAB으로 시뮬레이터를 작성하였으며, 정확도와 실행 속도 측면에서 성능을 평가하고자 한다.

• Journal of Advanced Navigation Technology
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• v.23 no.3
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• pp.245-250
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• 2019

Inertial navigation system has navigation errors because of the error of inertial measurement unit (IMU) and misalignment over time. In order to solve this problem, aided navigation system is performed using global navigation satellite system (GNSS), speedometer, etc. The inertial navigation system equipped with underwater vehicle mainly uses speedometer and performed aided navigation because satellite signals do not pass through underwater. There are DVL, EM-Log, and RPM in the speedometer, and the sensors are applied according to the system environment. This paper describes velocity aided navigation using RPM of inertial navigation system operating in high speed and deep water environment. In addition, we proposes an algorithm to compensate the limit of RPM with straight direction and the current velocity error. There are results of monte-calo simulation to prove performance of the proposed algorithm.

• 전기의세계
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• v.33 no.8
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• pp.479-486
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• 1984

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.1
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• pp.81-88
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• 2006

In this paper, we analyze a noncommutativity error that is not able to be compensated with integrating gyro outputs in RLG-based INS. The system can suffer from some motion known as RLG dithering motion, coning motion, ISA motion derived by an AV mount and vehicle real dynamic motion. So these motions are a cause of the noncommutativity error, the system error derived by each motion has to be analyzed. For the analysis, a relation between rotation vector and gyro outputs is introduced and applied to define the coordinate transformation matrix and the angular vector.