• 한국항공우주학회지
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• 제33권11호
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• pp.48-56
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• 2005

Predictive 필터는 Kalman 필터의 단점을 보완하고 모델 오차를 동시에 추정할수 있는 최근에 제시된 기법이다. 한 단계 앞의 추정 오차를 최소화하기 위한 최적화된 필터의 형태가 Predictive 필터이다. 본 필터의 주요 장점은 상태변수와 함께 모델오차를 파악할 수 있다는데 있다. 본 연구에서는 Predictive 필터를 이용한 인공위성의 자세추정 내용을 소개하도록 한다. 기존에 제시된 Predictive 필터 이론을 적용하여 자이로 바이어스 신호를 추정할수 있는 수식을 유도하고 또한 벡터 관측 정보를 이용한 자세추정 결과를 소개하도록 한다. 본 연구결과를 통해 향후 Predictive 필터의 확장 가능성을 예상할 수 있다.

• 한국군사과학기술학회지
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• 제19권4호
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• pp.435-442
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• 2016

For inertial navigation systems, initial information such as position, velocity and attitude is required for navigation. Self-alignment is the process to determine initial attitude on stationary condition using inertial measurements such as accelerations and angular rates. The accuracy of self-alignment is determined by inertial sensor error. As soon as an inertial navigation system is powered on, the temperature of accelerometer rises rapidly until temperature stabilization. It causes acceleration error which is called temperature stabilizing error of accelerometer. Therefore, temperature stabilizing error degrades the alignment accuracy and also increases alignment time. This paper suggests a method to calculate azimuthal attitude using curve fitting of horizontal control angular rate in fixed-gain self-alignment. It is verified by simulation and experiment that the accuracy is improved and the alignment time is reduced using the proposed method under existence of the temperature stabilizing error.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2001년도 ICCAS
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• pp.177.2-177
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• 2001

The asynchronous gyro outputs in the 3-axis navigation system are defined as each of gyros has its own output frequency. In this case, the navigation system has gyro outputs concurrently with the sensor mechanical frequency instead of the attitude frequency. So, there is an asynchronous error between gyro outputs and attitude calculation. In this paper, we analyze the gyro output error caused by the asynchronous gyro and present the high speed sampling technique and the extrapolation and interpolation of gyro outputs for synchronizing the gyro outputs.

• 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.

• 항공우주기술
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• 제13권1호
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• pp.27-36
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• 2014

인공위성은 예측 가능한 데이터를 이용하여 자신의 상태를 스스로 파악하며, 자연적으로 발생할 수 있는 일시적인 문제가 아니거나 오류가 전이되어 더 큰 문제를 발생시킬 수 있다고 판단될 경우를 대비하여 지상국과의 접속이 없는 상태에서도 스스로 고장 관리를 수행할 수 있도록 설계되어 있다. 태양 센서를 이용한 정상상태에서의 자세 오류 감지도 이러한 고장관리 항목 중의 하나로 사용될 수 있다. 본 연구에서는 회전하는 태양전지판에 장착되어 있는 태양 센서 데이터를 이용한 오류 감지 방법을 제안하였다. 태양전지판의 운용 방법에 따라 정상적인 상태에서 발생할 수 있는 태양 센서의 오차를 예측하고 이 예측된 값으로부터 벗어나는 정도를 파악하여 오류를 감지하도록 하였다. 또한, 식구간 존재 시에는 태양센서가 그 출력을 내지 못하므로 오류 감지에 문제가 없도록 보정하였다. 마지막으로 궤도 상 데이터를 이용하여 제안된 방법의 타당성을 검증하였다.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 1996년도 한국자동제어학술회의논문집(국내학술편); 포항공과대학교, 포항; 24-26 Oct. 1996
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• pp.864-866
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• 1996

The attitude error is expressed using four kinds of quaternion errors. And the explicit relation equations between them are derived four kinds of nonlinear error models of SDINS using the their explicit relation are also proposed for a nonlinear filter which may be available for a system in the presence of a large attitude error the concept of the proposed nonlinear error model is applied to the velocity aided SDINS using a linear Kalman filter and an extended Kalman filter the simulation results reveal a improvement of performance using the nonlinear error model.

• International Journal of Control, Automation, and Systems
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• 제1권4호
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• pp.520-526
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• 2003

In the case of a strapdown inertial navigation system (SDINS) with sizeable attitude errors, the uncertainty caused by linearization of the system degrades the performance of the filter. In this paper, a robust filter and various error models for the uncertainty are presented. The analytical characteristics of the proposed filter are also investigated. The results show that the filter does not require the statistical property of the system disturbance and that the region of the estimation error depends on a freedom parameter in the worst case. Then, the uncertainty of the SDINS is derived. Depending on the choice of the reference frame and the attitude error state, several error models are presented. Finally, various in-flight alignment methods are proposed by combining the robust filter with the error models. Simulation results demonstrate that the proposed filter effectively improves the performance.

• 한국정밀공학회:학술대회논문집
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• 한국정밀공학회 2006년도 추계학술대회 논문집
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• pp.85-86
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• 2006

• ETRI Journal
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• 제41권6호
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• pp.838-849
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• 2019

We present a permanent magnet-based spherical wheel motor that can be used in omnidirectional mobility applications. The proposed motor consists of a ball-shaped rotor with a magnetic dipole and a hemispherical shell with circumferential air-core coils attached to the outer surface acting as a stator. Based on the rotational symmetry of the rotor poles and stator coils, we are able to model the rotor poles and stator coils as dipoles. A simple physical model constructed based on a torque model enables fast numerical simulations of motor dynamics. Based on these numerical simulations, we test various control schemes that enable constant-speed rotation along arbitrary axes with small rotational attitude error. Torque analysis reveals that the back electromotive force induced in the coils can be used to construct a control scheme that achieves the desired results. Numerical simulations of trajectories confirm that even without explicit methods for correcting the rotational attitude error, it is possible to drive the motor with a low attitude error (<5°) using the proposed control scheme.

• 대한전기학회:학술대회논문집
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• 대한전기학회 2001년도 하계학술대회 논문집 D
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• pp.2075-2077
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• 2001

For precise positioning, GPS carrier measurements are often used. In this case, accurate position having mm${\sim}$cm error can be obtained. For 3D positioning, in CDGPS, more than five carrier phase measurements are required. When GPS signals are blocked or carrier phase measurements are insufficient, it cannot provide positioning solution. By integrating CDGPS with INS, continuity of positioning solution can be guaranteed. However, when a vehicle moves in low speed or in stationary, the CDGPS/INS integrated system is difficult to compensate INS attitude errors because GPS velocity error become relatively lange. In this paper, we used the 3D attitude GPS receiver to compensate the INS attitude error. By field experiments, it is shown that the proposed integration system maintains the navigation performance even when a vehicle is in low speed or GPS signal is blocked for a period of time.