• 대한수학회보
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• 제45권4호
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• pp.645-650
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• 2008

Let M be a generalized homogeneous compact space, and let Z(M) denotes the space of homeomorphisms of M with the $C^0$ topology. In this paper, we show that if the interior of the set of weak stable homeomorphisms on M is not empty then for any open subset W of Z(M) containing only weak stable homeomorphisms the orbital shadowing property is generic in W.

• 대한수학회보
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• 제45권3호
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• pp.523-561
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• 2008

The purpose of this paper is to survey the use of the important method of scaling in analysis, and particularly in complex analysis. Applications are given to the study of automorophism groups, to canonical kernels, to holomorphic invariants, and to analysis in infinite dimensions. Current research directions are described and future paths indicated.

• 대한수학회지
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• 제51권4호
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• pp.837-851
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• 2014

We consider ${\omega}$-chaos as defined by S. H. Li in 1993. We show that c-dense ${\omega}$-scrambled sets are present in every transitive system with two-sided limit shadowing property (TSLmSP) and that every transitive map on topological graph has a dense Mycielski ${\omega}$-scrambled set. As a preliminary step, we provide a characterization of dynamical properties of maps with TSLmSP.

• 충청수학회지
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• 제27권3호
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• pp.523-530
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• 2014

In this article, we deal with the notion of ­${\Omega}$-limit sets in dynamical systems. We show that the ${\Omega}$­-limit set of a compact subset of a phase space is quasi-attracting.

• Journal of Astronomy and Space Sciences
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• 제38권3호
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• pp.157-164
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• 2021

We describe a method for the in-orbit calibration of body-mounted magnetometers based on the CHAOS-7 geomagnetic field model. The code is designed to find the true calibration parameters autonomously by using only the onboard magnetometer data and the corresponding CHAOS outputs. As the model output and satellite data have different coordinate systems, they are first transformed to a Star Tracker Coordinate (STC). Then, non-linear optimization processes are run to minimize the differences between the CHAOS-7 model and satellite data in the STC. The process finally searches out a suite of calibration parameters that can maximize the model-data agreement. These parameters include the instrument gain, offset, axis orthogonality, and Euler rotation matrices between the magnetometer frame and the STC. To validate the performance of the Python code, we first produce pseudo satellite data by convoluting CHAOS-7 model outputs with a prescribed set of the 'true' calibration parameters. Then, we let the code autonomously undistort the pseudo satellite data through optimization processes, which ultimately track down the initially prescribed calibration parameters. The reconstructed parameters are in good agreement with the prescribed (true) ones, which demonstrates that the code can be used for actual instrument data calibration. This study is performed using Python 3.8.5, NumPy 1.19.2, SciPy 1.6, AstroPy 4.2, SpacePy 0.2.1, and ChaosmagPy 0.5 including the CHAOS-7.6 geomagnetic field model. This code will be utilized for processing NextSat-1 and Small scale magNetospheric and Ionospheric Plasma Experiment (SNIPE) data in the future.

• 한국항행학회논문지
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• 제26권6호
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• pp.404-411
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• 2022

위성항법시스템 운용 시 주요 기능은 항법위성의 궤도를 정확히 결정하여 항법메시지로 전송하는 것이다. 본 연구에서는 확장 칼만필터와 정밀동역학모델을 결합하여 항법위성의 궤도결정을 수행하는 소프트웨어를 개발하였다. IGS (international gnss service) 지상국의 실제 관측값을 사용하여 GPS (global positioning system)와 QZSS (quasi-zenith satellite system)의 궤도결정을 수행하고, IGS 정밀궤도력과 비교하여 항법시스템의 주요 성능지표인 URE (user range error)를 계산하였다. 항법위성에 탑재된 시계오차를 추정할 경우 radial 방향 궤도오차와 시계오차가 높은 역상관 관계를 가지는데 서로 상쇄되어 GPS와 QZSS의 궤도결정 URE 표준편차는 1.99 m, 3.47 m로 낮은 수준을 유지하였다. 항법위성 시계오차를 추정하는 대신 항법메시지의 시계오차를 모델링한 값으로 대체하여 궤도결정을 수행하였으며, URE와 지역적 상관관계 및 지상국 배치에 의한 영향을 분석하였다.

• Journal of Positioning, Navigation, and Timing
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• 제3권4호
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• pp.155-161
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• 2014

The purpose of this study is to develop precise point positioning (PPP) algorithms based on GLONASS code-pseudorange, verify their performance and present their utility. As the basic correction models of PPP, we applied Inter Frequency Bias (IFB), relativistic effect, satellite antenna phase center offset, and satellite orbit and satellite clock errors, ionospheric errors, and tropospheric errors that must be provided on a real-time basis. The satellite orbit and satellite clock errors provided by Information-Analytical Centre (IAC) are interpolated at each observation epoch by applying the Lagrange polynomial method and linear interpolation method. We applied Global Ionosphere Maps (GIM) provided by International GNSS Service (IGS) for ionospheric errors, and increased the positioning accuracy by applying the true value calculated with GIPSY for tropospheric errors. As a result of testing the developed GLONASS PPP algorithms for four days, the horizontal error was approximately 1.4 ~ 1.5 m and the vertical error was approximately 2.5 ~ 2.8 m, showing that the accuracy is similar to that of GPS PPP.

• Journal of Astronomy and Space Sciences
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• 제26권1호
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• pp.59-74
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• 2009

Relative navigation system is presented using GPS measurements from a single-channel global positioning system (GPS) simulator. The objective of this study is to provide the real-time inter-satellite relative positions as well as absolute positions for two formation flying satellites in low earth orbit. To improve the navigation performance, the absolute states are estimated using ion-free GRAPHIC (group and phase ionospheric correction) pseudo-ranges and the relative states are determined using double differential carrier-phase data and singled-differential C/A code data based on the extended Kalman filter and the unscented Kalman filter. Furthermore, pseudo-relative dynamic model and modified relative measurement model are developed. This modified EKF method prevents non-linearity of the measurement model from degrading precision by applying linearization about absolute navigation solutions not about the priori estimates. The LAMBDA method also has been used to improve the relative navigation performance by fixing ambiguities to integers for precise relative navigation. The software-based simulation has been performed and the steady state accuracies of 1 m and 6 mm ($1{\sigma}$ of 3-dimensional difference errors) are achieved for the absolute and relative navigation using EKF for a short baseline leader/follower formation. In addition, the navigation performances are compared for the EKF and the UKF for 10 hours simulation, and relative position errors are mm-level for the two filters showing the similar trends.

• 한국위성정보통신학회논문지
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• 제7권2호
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• pp.72-75
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• 2012

저궤도 인공위성에 사용되는 태양전력 조절기는 태양전지의 영향으로 일반적인 DC-DC 컨버터와는 다른 소신호 특성을 갖는다. 이로 인하여 벅-부스트 형 태양전력 조절기는 태양전지의 전류원 영역에서 평균전류모드제어가 불가능하다. 이 논문에서는 벅-부스트 형 태양전력 조절기를 의사-연속전류모드로 동작시켜 태양전지의 전 영역에서 태양전력조절기를 평균전류모드 단일 제어한다. 우선 의사-연속전류모드 벅-부스트 형 태양전력 조절기의 회로 동작을 설명하고, 소신호 전달함수를 구하고 이를 바탕으로 평균전류모드제어기를 구성한다. 최종적으로 모의실험을 통하여 의사-연속전류모드 벅-부스트 형 태양전력 조절기의 평균모드제어를 검증한다.

• 한국항공우주학회지
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• 제45권9호
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• pp.757-765
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• 2017

위성항법시스템 (GNSS: Global Navigation Satellite System)으로 계산되는 위치 정확도는 위성 의사거리 (Pseudo-Range) 측정값 정확도와 DOP (Dilution of Precision) 으로 표현되는 위성의 배치관계를 통해 결정된다. 위성의 의사거리 측정값은 위성 시계, 궤도, 전리층, 대류층, 다중경로 등 여러 요인에 의해 오차가 발생하게 되며, 사용자 의사거리정확도를 향상을 위해서는 정확한 의사거리 측정값이 필요하다. 반면, 위성의 배치의 경우, 사용자의 수신환경에 따라 위치 정확도가 달라진다. 예를 들어, 고층 빌딩이 많은 도심의 경우에는 위성전파 차단의 위험이 많아 가시위성의 수가 감소하고 개활지에 비해 상대적으로 양호한 DOP을 가지기 어렵다. 본 논문은 가상위성 (Virtual Satellite)을 통해 DOP 성능 개선과 의미있는 가상거리측정값 (VRM: Virtual Range Measurement) 정확도를 확보하여, 위치 정확도 향상 시키는 방법에 대해 연구하였다. 그 결과 적절한 가상위성배치와 정확한 가상 거리측정값을 이용하면 수직위치 정확도의 개선 효과를 얻을 수 있었다.