• Journal of Astronomy and Space Sciences
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• 제10권1호
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• pp.1-16
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• 1993

Three typer of spin-axis attitude determination program for the geosynchronous transfer orbit spacecraft are developed. Deterministic closed-from algorithm, batch least-square algorithm and stabilized Kalman filter algorithm are used for implemetation of three programs. EUROSTAR bus model from British Aerospace is used for attitude sensor modelling. Attitude determinations using three programs are performed for the simulated sensor data according to INMARSAT 2-F1 prelaunch mission analysis.

• 한국항공우주학회지
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• 제43권5호
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• pp.405-412
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• 2015

본 논문은 회전안정성을 갖는 탄도수정탄의 대기속도 추정을 위한 필터 설계에 대하여 설명한다. 대상 시스템은 운용상의 제약(공간, 파워)으로 인하여, 대기속도 측정을 위한 센서를 사용할 수 없다. 따라서 한정된 센서를 이용한 대기속도 추정이 필요하다. 따라서 본 연구에서는 IMU(가속도계, 자이로)에서 측정하는 3축 가속도와 각속도 데이터만 이용하여, 대기속도 추정을 위한 필터를 설계하였다. 대상 시스템의 경우, 넓은 속도, 고도의 운용범위를 커버하기 위한 추정 필터가 필요하므로 본 연구에서는 확장 칼만필터를 설계하여 기존의 연구와의 차별성을 두었다. 확장 칼만필터 설계를 위한 자코비안 행렬은 NRF(No-roll frame)에서의 간략화된 선형모델을 이용하여 구성하였다. 최종적으로 센서 오차와 바람 모델을 포함한 시뮬레이션을 통해 그 성능을 검토하였다. 이때, 시뮬레이션은 설계한 대기속도와 각속도 모델 오차의 영향을 분석하기 위하여 네 가지 경우의 프로세스 공분산 행렬 값에 대한 영향을 분석하였다.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2000년도 제15차 학술회의논문집
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• pp.342-342
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• 2000

We present 3-axis stabilized spacecraft attitude determination algorithm using the magnetometer. The magnetometer has been used as a reliable, light-weight and inexpensive sensor in attitude determination and reaction wheel momentum dumping system. Recent studies have attempted to use the magnetometer when other attitude sensor, such as star tracker, fails. The differences between the measured and computed the Earth's magnetic field components are spacecraft attitude errors. In this paper, we propose extended Kalman filter(EKF) to determine spacecraft attitude with the magnetometer data and gyro-measured body rates. We develop and simulate this algorithm using MATLAB/SIMULINK. This algorithm can be used as a backup attitude determination system.

• 전기학회논문지
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• 제58권11호
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• pp.2299-2301
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• 2009

The adaptive IIR filters for active noise control systems are more effective when acoustic feedback exists, but the adaptive IIR filters could be unstable when the filter algorithm is not yet converged. In this paper, auto-secondary path estimation techniques and a stabilizing process for adaptive Multi-Channel Recursive LMS (MCRLMS) filters are developed to improve the stability of multi-channel active noise control systems. Experiments using a TMS320VC33 digital signal processor in a three dimensional enclosure have performed to show the effectiveness of the proposed algorithm.

• Nuclear Engineering and Technology
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• 제56권4호
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• pp.1441-1453
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• 2024

The yield stability of the neutron generator directly affects the accuracy of elemental analysis. This paper presents an industrial fully automatic neutron generator with a 48 mm neutron tube based on PLC to improve the stability and reliability of the neutron generator in industrial applications. By integrating a Kalman Filter with the PID algorithm in a PLC, the neutron yield of the generator is remarkably stabilized, achieving 1 × 10⁸n/s. The neutron generator has been employed for industrial online elemental analysis. The results demonstrate that only a slight fluctuation of ±0.82 % exists in the neutron yield, and the reproducibility of the generator holds at a significant level of 0.05. This improved neutron generator can be applied to the online bulk analysis of carbon in coal-fired power stations and absolute measurement of neutron source emission rate.

• International Journal of Aeronautical and Space Sciences
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• 제14권4호
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• pp.369-378
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• 2013

This paper presents a vision/LiDAR integrated navigation system that provides accurate relative navigation performance on a general ground surface, in GNSS-denied environments. The considered ground surface during flight is approximated as a piecewise continuous model, with flat and slope surface profiles. In its implementation, the presented system consists of a strapdown IMU, and an aided sensor block, consisting of a vision sensor and a LiDAR on a stabilized gimbal platform. Thus, two-dimensional optical flow vectors from the vision sensor, and range information from LiDAR to ground are used to overcome the performance limit of the tactical grade inertial navigation solution without GNSS signal. In filter realization, the INS error model is employed, with measurement vectors containing two-dimensional velocity errors, and one differenced altitude in the navigation frame. In computing the altitude difference, the ground slope angle is estimated in a novel way, through two bisectional LiDAR signals, with a practical assumption representing a general ground profile. Finally, the overall integrated system is implemented, based on the extended Kalman filter framework, and the performance is demonstrated through a simulation study, with an aircraft flight trajectory scenario.

• 대한임베디드공학회논문지
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• 제13권1호
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• pp.17-24
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• 2018

Military camera equipment has a problem that observability is inferior due to various shaking factors. In this paper, we propose an image stabilization algorithm considering performance and execution time to solve this problem and implemented it in Zynq SoC. We stabilized both the simple shaking in the fixed observation position and the sudden shaking in the moving observation position. The feature of the input image is extracted by the Sobel edge algorithm, the subblock with the large edge data is selected, and the motion vector, which is the compensation reference, is calculated through template matching using the 3-step search algorithm of the region of interest. In addition, the proposed algorithm can distinguish the shaking caused by the simple shaking and the movement by using the Kalman filter, and the stabilized image can be obtained by minimizing the loss of image information. To demonstrate the effectiveness of the proposed algorithm, experiments on various images were performed. In comparison, PSNR is improved in the range of 2.6725~3.1629 (dB) and image loss is reduced from 41% to 15%. On the other hand, we implemented the hardware-software integrated design using HLS of Xilinx SDSoC tool and confirmed that it operates at 32 fps on the Zynq board, and realized SoC that operates with real-time processing.

• 반도체디스플레이기술학회지
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• 제13권1호
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• pp.27-33
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• 2014

Video from unmanned aerial vehicle (UAV) is influenced by natural environments due to the light-weight UAV, specifically by winds. Thus UAV's shaking movements make the video shaking. Objective of this paper is making a stabilized video by removing shakiness of video acquired by UAV. Stabilizer estimates camera's motion from calculation of optical flow between two successive frames. Estimated camera's movements have intended movements as well as unintended movements of shaking. Unintended movements are eliminated by smoothing process. Experimental results showed that our proposed method performs almost as good as the other off-line based stabilizer. However estimation of camera's movements, i.e., calculation of optical flow, becomes a bottleneck to the real-time stabilization. To solve this problem, we make parallel stabilizer making average 30 frames per second of stabilized video. Our proposed method can be used for the video acquired by UAV and also for the shaking video from non-professional users. The proposed method can also be used in any other fields which require object tracking, or accurate image analysis/representation.

• 대한기계학회논문집A
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• 제40권1호
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• pp.1-8
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• 2016

본 논문에서는 기존의 관성안정화 플랫폼에서 보편적으로 사용됐던 PID 제어에 외란관측기를 적용하는 알고리즘 제안한다. 외란관측기 알고리즘을 적용하기 위하여 직접구동 모터로 구동되는 안정화 플랫폼 축의 관성모멘트와 축 마찰 특성을 실험적으로 구하고, 시뮬레이션과 실험결과를 비교하여 정확도를 검증하였다. 또한 차수와 상대차수가 다른 여러 가지 Q-filter 적용실험을 통하여 필터 특성에 따른 시스템의 안정성을 확인하였다. 본 논문에서 제안한 알고리즘은 6 자유도 시뮬레이터를 이용하여 차량 모션 인가실험을 통해 이중 PID 제어 루프의 결과와 비교/검증하였다.

• 전기전자학회논문지
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• 제18권3호
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• pp.376-382
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• 2014

본 논문은 4개의 BLDC 모터를 이용한 쿼드콥터 무인비행체의 센서 신호 성능 개선을 위해 진동에 강인한 센서융합 방식을 제안하고 이를 기반으로 하여 자세제어를 위한 개선된 PID 제어 기법을 제안한다. 쿼드콥터의 자세추정을 위해 사용하는 가속도 센서와 자이로 센서 각각의 특성에서 나타나는 단점을 상호 보완하고 모터에서 발생하는 진동의 영향을 최소화하도록 상보필터를 적용하여 두 센서를 융합하는 방법을 제안하였다. 본 논문에서 제안하는 센서 융합 방식은 쿼드콥터의 방진을 위해 일반적으로 사용되는 이동평균 필터나 저역통과 필터에 비해 진동에 더욱 강인하고 지연이 적은 결과를 얻을 수 있었다. 또한 쿼드콥터의 자세 제어를 위해 일반적으로 사용되는 PID 제어 중 D 제어 성분을 추정된 각도의 변화량을 이용하는 대신 자이로 센서를 사용하는 쿼드콥터의 특성에 맞게 자이로 센서 출력을 사용하는 방식을 제안하여 사용함으로써 자세 제어 오차를 줄일 수 있고 자세 제어의 안정화가 보다 용이하게 이루어질 수 있음을 확인하였다.