• Journal of Astronomy and Space Sciences
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• 제22권1호
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• pp.35-46
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• 2005

This paper addresses the design and analysis results of a 2-axes magnetometer for attitude determination of small satellite. A low-cost and efficient 2-axes fluxgate magnetometer was selected as the most suitable attitude sensor for LEO microsatellites which require a low-to-medium level pointing accuracy. An optimization trade-off study has been performed for the development of 2-axes fluxgate magnetometer. All the relevant parameters such as permeability, demagnetization factor, coil diameter, core thickness, and number of coil turns were considered for the sizing of a small satellite magnetometer. The magnetometer which is designed, manufactured, and tested in-house as described in this paper satisfies linearity requirement for determining attitude position of small satellites. On the basis of magnetometer which is designed in Space System Research Lab. (SSRL), commercial magnetometer will be developed.

• Journal of Astronomy and Space Sciences
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• 제39권3호
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• pp.117-126
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• 2022

The Ionospheric Anomaly Monitoring by Magnetometer And Plasma-probe (IAMMAP) is one of the scientific instruments for the Compact Advanced Satellite 500-3 (CAS 500-3) which is planned to be launched by Korean Space Launch Vehicle in 2024. The main scientific objective of IAMMAP is to understand the complicated correlation between the equatorial electro-jet (EEJ) and the equatorial ionization anomaly (EIA) which play important roles in the dynamics of the ionospheric plasma in the dayside equator region. IAMMAP consists of an impedance probe (IP) for precise plasma measurement and magnetometers for EEJ current estimation. The designated sun-synchronous orbit along the quasi-meridional plane makes the instrument suitable for studying the EIA and EEJ. The newly-devised IP is expected to obtain the electron density of the ionosphere with unprecedented precision by measuring the upper-hybrid frequency (f_UHR) of the ionospheric plasma, which is not affected by the satellite geometry, the spacecraft potential, or contamination unlike conventional Langmuir probes. A set of temperature-tolerant precision fluxgate magnetometers, called Adaptive In-phase MAGnetometer, is employed also for studying the complicated current system in the ionosphere and magnetosphere, which is particularly related with the EEJ caused by the potential difference along the zonal direction.

• Journal of Astronomy and Space Sciences
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• 제9권2호
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• pp.203-212
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• 1992

인공위성의 자세결정을 위해 3축 magnetometer에 의해 측정된 지구 자기장의 자료와 IGRF 모델(tilted-eccentric dipole 모델)을 사용하였다. 지구자기장 모델으 값들을 계산하여 magnetometer 측정자료들과 비교해 보았고 이것으로부터 두 자세각 $\alpha$ 각과 $\beta$들을 구하였다. 이 두 각들을 이용하여 자세결정에 사용되는 Z 축과 자기장의 수직성분 사이의 실 자세각 $\gamma$ 에 대한 bound $\gamma1$과 $\gamma2$를 계산하여 UoSAT-11, 14, 22의 자세 상태를 알아보았다.

• 한국자기학회지
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• 제16권3호
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• pp.182-185
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• 2006

본 연구에서는 인공위성의 자세제어용으로 사용될 3-축 flux-gate 마그네토 미터를 개발 제작하였다. 제작된 3-축의 flux-gate 마그네토 미터는 소비전력이 1W 미만에서 정확도는 ${\pm}1%$ 이내였으며 noise는 1Hz에서 $0.2nT/\sqrt{Hz}$이였다. 또한 제작된 마그네토미터를 인공위성에 적용하기 위한 환경시험을 수행하였다. 환경시험으로 가속도시험은 진동주파수의 범위가 $10Hz{\sim}1000Hz$에서 15g(g : 지구의 중력가속도)의 가속도에서 수행하였고, themal cycle 시험은 $1x10^{-6}$ Torr의 진공에서 $-55^{\circ}C{\sim}80^{\circ}C$의 온도 사이에서 24시간 동안 4회의 thermal cycle 시험을 한 결과 모두 정상 작동 되었다.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2003년도 ICCAS
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• pp.36-40
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• 2003

The considered satellite is supposed to operate in the earth-point mode and sun-point mode in accordance with the mission requirements. The magnetic field correction is based on the orbit geometry using a set of measured magnetic field data from the three-axis-magnetometer and its algorithm excludes the earth’s magnetic field model. Moreover, the usefulness of the proposed method is investigated throughout the simulation of KOMPSAT-1.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2003년도 ICCAS
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• pp.1259-1261
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• 2003

The vehicle's heading angle determination is formulated and the proposed method based on geometry engages the magnetometer and the GPS. The resulting maximum determination accuracy of 0.3deg over the entire earth as a standard deviation is obtained for a magnetometer with measurement error of 1nT.

• Journal of Astronomy and Space Sciences
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• 제35권3호
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• pp.175-183
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• 2018

Many recent satellites have mission periods longer than 10 years; thus, satellite-based local space weather monitoring is becoming more important than ever. This article describes the instruments and data applications of the Korea Space wEather Monitor (KSEM), which is a space weather payload of the GeoKompsat-2A (GK-2A) geostationary satellite. The KSEM payload consists of energetic particle detectors, magnetometers, and a satellite charging monitor. KSEM will provide accurate measurements of the energetic particle flux and three-axis magnetic field, which are the most essential elements of space weather events, and use sensors and external data such as GOES and DSCOVR to provide five essential space weather products. The longitude of GK-2A is $128.2^{\circ}E$, while those of the GOES satellite series are $75^{\circ}W$ and $135^{\circ}W$. Multi-satellite measurements of a wide distribution of geostationary equatorial orbits by KSEM/GK-2A and other satellites will enable the development, improvement, and verification of new space weather forecasting models. KSEM employs a service-oriented magnetometer designed by ESA to reduce magnetic noise from the satellite in real time with a very short boom (1 m), which demonstrates that a satellite-based magnetometer can be made simpler and more convenient without losing any performance.

• Current Optics and Photonics
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• 제5권3호
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• pp.213-219
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• 2021

We describe a single-channel rubidium (Rb) radio-frequency atomic magnetometer (RFAM) as a receiver that takes magnetic signal resonating with Zeeman splitting of the ground state of Rb. We optimize the performance of the RFAM by recording the response signal and signal-to-noise ratio (SNR) in various parameters and obtain a noise level of 159 $fT{\sqrt{Hz}}$ around 30 kHz. When a resonant radiofrequency magnetic field with a peak amplitude of 8.0 nT is applied, the bandwidth and signal-to-noise ratio are about 650 Hz and 88 dB, respectively. It is a good agreement that RFAM using alkali atoms is suitable for receiving signals in the very low frequency (VLF) carrier band, ranging from 3 kHz to 30 kHz. This study shows the new capabilities of the RFAM in communications applications based on magnetic signals with the VLF carrier band. Such communication can be expected to expand the communication space by overcoming obstacles through the high magnetic sensitive RFAM.

• 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.

• 우주기술과 응용
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• 제4권2호
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• pp.153-168
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• 2024

사운딩 로켓은 저렴한 비용과 빠른 개발 기간을 통해 전리권이나 무중력 환경을 직접 탐사하는 유용한 도구이다. 이러한 로켓은 목표 고도에 신속하게 도달하며, 다양한 과학적 장비를 탑재하여 데이터를 실시간으로 수집할 수 있다. 페리지에어로스페이스(주)는 2024년 상반기에 첫 시험 발사를 진행한 뒤, 2025년 1월경에는 2차 성능시험 사운딩 로켓을 발사할 예정이다. 이 로켓은 제주 해상에서 발사될 예정이며, 약 150 km의 목표 고도에 총 30 kg의 탑재체를 싣고, 준궤도 영역에서 다양한 실험을 수행할 것이다. 특히, 중위도 지역의 전리권에서는 간헐적으로 전자 밀도가 증가하는 스포라딕 E층과 적도 전기제트에 의한 자기장의 미세변화를 관측할 수 있을 것으로 예상된다. 이러한 관측을 위해 KAIST 인공위성연구소에서 개발 중인 탑재체 IAMMAP(ionospheric anomaly monitoring by magnetometer and plasma-probe)의 사운딩 로켓 버전이 발사체에 실릴 예정이다. 본 연구는 중위도 지역의 전리권에 대해서 이해하고, 2차 성능시험에서의 관측 가능한 임무 설계에 중점을 두고자 한다.