• 제목/요약/키워드: SDINS

검색결과 98건 처리시간 0.048초

적응필터를 사용한 수직상태 SDINS 전달정렬 (SDINS Transfer Alignment using Adaptive Filter for Vertical Launcher)

  • 박찬주;이상정
    • 한국군사과학기술학회지
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    • 제10권1호
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    • pp.14-21
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    • 2007
  • This paper proposes SDINS(strapdown inertial navigation system) transfer alignment method for vertical launcher using an adaptive filter in the ship. First, the velocity and attitude matching transfer alignment method is designed to align SDINS for vertical launcher. Second, the adaptive filter is employed to estimate measurement noise variance in real time using the residual of measurements. Because it is difficult to decide measurement noise variance when noise properties of the ship SDINS are changed. To verify its performance, it is compared with the EKF(Extended Kalman filter) using uncorrect measurement variance. The monte carlo simulation results show that proposed method is more effective in estimating attitude angle than EKF.

자이로 컴파스 얼라인먼트 오차특성을 고려한 스트랩다운 관성항법장치의 상호분산해석 (Covariance analysis of strapdown INS considering characteristics of gyrocompass alignment errors)

  • 박흥원;박찬국;이장규
    • 제어로봇시스템학회:학술대회논문집
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    • 제어로봇시스템학회 1993년도 한국자동제어학술회의논문집(국내학술편); Seoul National University, Seoul; 20-22 Oct. 1993
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    • pp.34-39
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    • 1993
  • Presented in this paper is a complete error covariance analysis for strapdown inertial navigation system(SDINS). We have found that in SDINS the cross-coupling terms in gyrocompass alignment errors can significantly influence the SDINS error propagation. Initial heading error has a close correlation with the east component of gyro bias erro, while initial level tilt errors are closely related to accelerometer bias errors. In addition, pseudo-state variables are introduced in covariance analysis for SDINS utilizing the characteristics of gyrocompass alignment errors. This approach simplifies the covariance analysis because it makes the initial error covariance matrix to a diagonal form. Thus a real implementation becomes easier. The approach is conformed by comparing the results for a simplified case with the covariance analysis obtained from the conventional SDINS error model.

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바이어스 분리 칼만필터를 이용한 속도보정 SDINS의 측정오차 추정 (Measurement of error estimation for velocity-aided SDINS using separate-bias Kalman filter)

  • 전창배;유준
    • 제어로봇시스템학회논문지
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    • 제4권1호
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    • pp.56-61
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    • 1998
  • The velocity measurement error in the velocity-aided SDINS on the maneuvering vehicle is unavoidable and degrades the performance of the SDINS. The characteristics of the velocity measurement error can be modeled as a random bias. This paper proposes a new method for estimating the velocity measurement error in the SDINS. The generalized likelihood ratio test is used for detecting the error and a modified separate-bias Kalman filter in the feedback configuration is suggested for estimating the magnitude of the velocity measurement error.

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뱅크턴하는 항체에 대한 GPS를 이용한 SDINS의 자세 오차 추정 향상 (Performance improvement of SDINS attitude error estimation using GPS for bank-to-turn flight vehicle)

  • 유해성;유기정;김현석;이윤선;박흥원
    • 한국항공우주학회지
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    • 제39권2호
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    • pp.128-136
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    • 2011
  • 뱅크턴을 수행하는 항공기에 운용되는 관성항법장치의 특정 자이로 비정렬 오차가 수직축 자세오차를 연속적으로 증가시키는 현상에 대해서 분석을 수행하고, 이 자이로 비정렬 오차를 제거하기 위해 GPS을 결합한 INS/GPS 시스템에 대해서 새로운 비정렬 모델링 방법을 제시하고, 그 성능 향상을 시뮬레이션을 통해 제시한다.

링레이저 자이로 기반 관성항법장치와 위성항법장치의 강결합 방식 시스템 구현 (The Implementation of Tightly coupled SDINS/GPS System based on the Ring Laser Gyro)

  • 유해성;박상은;정진섭;박흥원
    • 한국항공우주학회지
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    • 제41권2호
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    • pp.134-141
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    • 2013
  • 항공기에 탑재되어 운용되는 링레이저 자이로 기반 스트랩다운 관성항법장치(SDINS)와 위성항법장치(GPS)의 결합 시스템의 실시간 구현에 있어서 설계시 고려해야할 문제에 대해서 살펴본다. SDINS/GPS 결합 시스템의 실시간 구현시, 레버암, 측정치 획득 및 오차 보상 외에, 링 레이저 자이로 기반의 SDINS의 특성을 고려해야만 한다. 뱅크턴을 반복적으로 수행하는 항공기에서 발생하는 누적 수직축 자세 오차를 추정하기 위해, 자이로의 비정렬이 모델링된 모델을 구현한다. 항공기 탑재 시험을 통해 수직축 자세 오차의 누적문제 및 실시간 구현 상의 문제를 해결하고, 자세 오차 추정 성능 향상 결과를 살펴본다.

스트랩다운 관성항법시스템 성능평가 시험

  • 이상종;유창선;심요한;김종철
    • 항공우주기술
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    • 제1권1호
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    • pp.28-41
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    • 2002
  • 본 논문의 목적은 실제 관성항법센서를 사용하여 개발된 스트랩다운형 관성항법시스템 및 이용 알고리즘에 대한 성능 및 오차를 평가하는 것이다. 시험은 관성항법센서의 조합을 두가지로 나누어 수행하였는데, 서로 다른 바이어스를 갖는 중급의 가속도계와 저급의 가 속도계가 사용되었으며, 자이로의 경우는 FOG(Fiber Optic Gyro)를 사용하였다(SDINS-1, SDINS-2). 관성항법시스템의 성능을 평가하기 위해서 두가지의 시험이 수행되었으며, 3축 운동 시험대를 이용한 지상정지시험과 차량을 이용한 단거리 주행시험을 수행하였다. 단거 리 주행시험의 결과는 정확도 20 mm를 갖는 DGPS(Differential GPS)의 시험결과와 비교 하였으며, 결과 및 오차를 나타내었다.

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A Multistage In-flight Alignment with No Initial Attitude References for Strapdown Inertial Navigation Systems

  • Hong, WoonSeon;Park, Chan Gook
    • International Journal of Aeronautical and Space Sciences
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    • 제18권3호
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    • pp.565-573
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    • 2017
  • This paper presents a multistage in-flight alignment (MIFA) method for a strapdown inertial navigation system (SDINS) suitable for moving vehicles with no initial attitude references. A SDINS mounted on a moving vehicle frequently loses attitude information for many reasons, and it makes solving navigation equations impossible because the true motion is coupled with an undefined vehicle attitude. To determine the attitude in such a situation, MIFA consists of three stages: a coarse horizontal attitude, coarse heading, and fine attitude with adaptive Kalman navigation filter (AKNF) in order. In the coarse horizontal alignment, the pitch and roll are coarsely estimated from the second order damping loop with an input of acceleration differences between the SDINS and GPS. To enhance estimation accuracy, the acceleration is smoothed by a scalar filter to reflect the true dynamics of a vehicle, and the effects of the scalar filter gains are analyzed. Then the coarse heading is determined from the GPS tracking angle and yaw increment of the SDINS. The attitude from these two stages is fed back to the initial values of the AKNF. To reduce the estimated bias errors of inertial sensors, special emphasis is given to the timing synchronization effects for the measurement of AKNF. With various real flight tests using an UH60 helicopter, it is proved that MIFA provides a dramatic position error improvement compared to the conventional gyro compass alignment.

스트랩다운 관성항법장치에 대한 가관측성 분석 (Analysis of observability for strapdown inertial navigation system)

  • 정태호;박흥원;이상정
    • 제어로봇시스템학회:학술대회논문집
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    • 제어로봇시스템학회 1989년도 한국자동제어학술회의논문집; Seoul, Korea; 27-28 Oct. 1989
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    • pp.45-49
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    • 1989
  • The observability of an strapdown inertial navigation system(SDINS) is investigated. The piece-wise constant systems are defined and the stepped observability matrix scheme is applied to observability analysis of SDINS theoretically, the results are compared with that of covariance simulation. It is found that SDINS is more observable than gimballed inertial navigation system (GINS) in the case of the variation of vehicle attitude, and is found that the stepped observability matrix theory is simple and useful for the analysis of the system observability but the results are not completely same as that of covariance simulation.

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자이로 콤파스 좌표측 정렬에 의한 SDINS 오차특성 (Error propagation of SDINS aligned by gyrocompass)

  • 문홍기;박흥원;오문수
    • 제어로봇시스템학회:학술대회논문집
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    • 제어로봇시스템학회 1987년도 한국자동제어학술회의논문집; 한국과학기술대학, 충남; 16-17 Oct. 1987
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    • pp.513-518
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    • 1987
  • In this paper the error equations of the SDINS aligned by the gyrocompass are derived considering that the alignment errors are correlated to the sensor errors. Also the navigation errors due to the correlated errors are simulated by this error equations. The simulations are performed by the covariance analysis method, assumed all the sensor errors are random constants. The simulation results show that while the INS maintains the alignment attitude the cancellation takes place between the correlated errors, but once the INS changes attitude this cancellation effect is perturbed.

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전자-광학센서를 이용한 스트랩다운 관성항법장치의 보정기법 (A SDINS Compensation Scheme Using Electro-Optical Sensor)

  • 임정빈;임유철;유준
    • 제어로봇시스템학회논문지
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    • 제12권5호
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    • pp.509-515
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    • 2006
  • This paper presents a navigation error compensation scheme for Strap-Down Inertial Navigation System(SDINS) using electro-optical sensor. The proposed scheme uses the position or the attitude information from the sensor. For each case, Kalman filter model is derived and implemented. To show the effectiveness of the present compensation scheme, computer simulations have been carried out resulting in the boundedness of position and attitude errors.