• Title/Summary/Keyword: 과학위성1호(STSAT-1)

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Ground station Baseband Controller(GBC) Development of STSAT-2 (과학기술위성2호 관제를 위한 Ground station Baseband Controller(GBC) 개발)

  • Oh Dae-Soo;Oh Seung-Han;Park Hong-Young;Kim Kyung-Hee;Cha Won-Ho;Lim Chul-Woo
    • The Transactions of the Korean Institute of Electrical Engineers D
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    • v.54 no.8
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    • pp.482-485
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    • 2005
  • STSAT-2 is first satellite which is scheduled to launch by first Korea launcher. Ground station Baseband Controller(GBC) for operating STSAT-2 is now developing. GBC control data flow path between satellite operation computers and ground station antennas and count number of received data packets among demodulated audio signals from three antennas and also set data flow path to good-receiving antenna automatically In GBC two uplink FSK modulators(1.2kbps, 9.6kbps) and six downlink FSK demodulators(9.6kbps, 38.4kbps) are embedded. STSAT-2 GBC hardware is more simpler than STSAT-1 GBC by using FPGA in which all digital logic implemented. Now test and debugging of GBC hardware and Software(FPGA Code and CBC Manager Program) is well progressing in SaTReC, KAIST. This paper introduce GBC structure, functions and test results.

Ground station Baseband Controller(GBC) Development of STSAT-2 (과학기술위성2호 관제를 위한 Ground station Baseband Controller(GBC) 개발)

  • Oh, Dae-Soo;Oh, Seung-Han;Park, Hong-Young;Kim, Kyung-Hee;Cha, Won-Ho;Lim, Chul-Woo;Ryu, Chang-Wan;Hwang, Dong-Hwan
    • Proceedings of the KIEE Conference
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    • 2005.05a
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    • pp.116-118
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    • 2005
  • STSAT-2 is first satellite which is scheduled to launch by first Korea launcher. After launch Ground station Baseband Controller(GBC) for operating STSAT-2 is now developing. GBC control data flow path between satellite operation computers and ground station antennas. and GBC count number of received data packets among demodulated audio signals from three antennas and set data flow path to good-receiving antenna automatically. In GBC two uplink FSK modulators(1.2kbps, 9.6kbps) and six downlink FSK demodulators(9.6kbps, 38.4kbps) are embedded. STSAT-2 GBC hardware is more simpler than STSAT-1 GBC by using FPGA in which all digital logic implemented. Now test and debugging of GBC hardware and Software(FPGA Code and GBC Manager Program) is well progressing in SaTReC, KAIST. This paper introduce GBC structure, functions and test results.

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Error Correction Code and SEU Test Analysis of Mass Memory for STSAT-3 (과학기술위성 3호 대용량 메모리에 대한 오류복구 코드 및 SEU 시험 결과 분석)

  • Seo, In-Ho;Ryu, Kwang-Sun;Oh, Dae-Soo;Kim, Byung-Jun
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.38 no.1
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    • pp.87-93
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    • 2010
  • RS(10,8) Code by 4-bit symbol was developed to protect the mass memory of STSAT-3 from SEU in orbit. Therefore, one symbol can be corrected for 32-bit data with 8-bit parity configuration. Moreover, scrubbing period and SEU occurrence rate was calculated based on the KITSAT-3 result. A prediction of SEU rates was performed based on the ground experiment results with a proton accelerator in the KIRAMS(Korea Institute of Radiological Medical Sciences).

이온층 고에너지 입자 상태와 저궤도 위성의 위성체 전위 사이의 상관관계

  • Lee, Jun-Hyeon;Lee, Eun-Sang;Kim, Gwan-Hyeok;Seon, Jong-Ho;Lee, Jae-Jin;Lee, Dong-Hun;Jin, Ho
    • The Bulletin of The Korean Astronomical Society
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    • v.37 no.2
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    • pp.124.2-124.2
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    • 2012
  • 위성체의 전위는 위성 주변의 우주 환경에 크게 영향을 받는다. 본 연구에서는 과학기술위성 1호(STSAT-1)에 탑재된 LP(Langmuir Probe)와 ESA(Electro-Static Analyzer) 관측 자료를 이용하여 위성체의 전위에 위성 주변 고에너지 입자들이 미치는 영향을 분석하였다. 일반적으로 위성체가 대전되어 위성체의 부동전위가 감소할 때 위성 주변의 플라즈마 밀도는 감소하고 온도는 증가한다. 또한 DMSP 위성 등을 비롯한 이전 관측에서는 고에너지 입자의 플럭스가 증가하는 지역을 위성이 통과할 때 위성체의 전위가 감소하였다. 본 연구에서는 위성이 수 ~ 수 십 keV 정도의 고에너지 입자 플럭스가 증가한 후 감소하는 지역을 통과할 때에도 위성체의 전위가 감소하는 현상을 관측하였다. 고에너지 입자의 플럭스가 감소하는 지역에서 일어나는 위성의 대전현상을 통계적으로 분석해 보고 이러한 결과를 토대로 위성체 전위 변화에 우주환경 변화가 어떤 영향을 주는지 연구하였다.

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On Stability of the Pulsed Plasma Thruster for STSAT-2 based on the Lyapunov Function (리아프노프 함수에 기초한 과학기술위성 2호 펄스형 플라즈마 전기추력기의 동작 안정성 연구)

  • Sin, Gu-Hwan;Nam, Myeong-Yong;Gang, Gyeong-In;Im, Jong-Tae;Cha, Won-Ho
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.34 no.1
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    • pp.95-102
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    • 2006
  • The PPT being currently developed for the flight model represents a significant leap in techniques and technology compared to the previous flight ones. The electrical energy to be charged in the pulsed plasma thruster (PPT) is a very important aspect to provide an uniform impulse bit ,, and a specific impulse ,, for satellite attitude control. In this paper, we propose a nonlinear control technique and a stability analysis based on the Lyapunov function for the pulsed plasma thruster. Specifically, the proposed control law guarantees to charge and discharge the electrical energy generated from the power processing unit (PPU) within the specified time.

Current Status and Future Prospects of Satellite Payloads Technology (인공위성 탑재체 기술 현황 및 전망)

  • Yong, Sang-Soon;Kang, Gm-Sil;Heo, Haeng-Pal
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.44 no.8
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    • pp.710-717
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    • 2016
  • Satellite payload can be classified as electro-optical payload, SAR, microwave radiometer, communication payload, navigation payload and so on in accordance with the mission objective. The technology of satellite payload was tried to be obtained through development of KOMPSAT series, COMS and STSAT in Korea. In this paper, the required technology for the development and world market trend of satellite payload were studied and described. Since KOMPSAT program has been started in 1994, technology status and future prospects of satellite payload in Korea are studied and analyzed.

Environmental Test Results of a Flight Model of a Compact Imaging Spectrometer for a Microsatellite STSAT-3 (과학기술위성3호 소형영상분광기 발사모델 환경시험 결과)

  • Lee, Sang-Jun;Kim, Jung-Hyun;Lee, Jun-Ho;Lee, Chi-Won;Jang, Tae-Sung;Kang, Kyung-In
    • Korean Journal of Optics and Photonics
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    • v.22 no.4
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    • pp.184-190
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    • 2011
  • A compact imaging spectrometer (COMIS) was developed for a microsatellite STSAT-3. The satellite is now rescheduled to be launched into a low sun-synchronous Earth orbit (~700 km) by the end of 2012. Its main operational goal is the imaging of the Earth's surface and atmosphere with ground sampling distance of 27 m and 2 - 15 nm spectral resolution over visible and near infrared spectrum (0.4 - 1.05 ${\mu}m$). A flight model of COMIS was developed following an engineering model that had successfully demonstrated hyperspectral imaging capability and structural rigidity. In this paper we report the environmental test results of the flight model. The mechanical stiffness of the model was confirmed by a small shift of the natural frequency i.e., < 1% over 10 gRMS random vibration test. Electrical functions of the model were also tested without showing any anomalies during and after vacuum thermal cycling test with < $10^{-5}$ torr and $-30^{\circ}C\;-\;35^{\circ}C$. The imaging capability of the model, represented by a modulation transfer function (MTF) value at the Nyquist frequency, was also kept unvaried after all those environmental tests.

Stray Light Analysis of a Compact Imaging Spectrometer for a Microsatellite STSAT-3 (과학기술위성3호 부탑재체 소형영상분광기 미광 해석)

  • Lee, Jin Ah;Lee, Jun Ho
    • Korean Journal of Optics and Photonics
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    • v.23 no.4
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    • pp.167-171
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    • 2012
  • This paper reports on the stray light analysis results of a compact imaging spectrometer (COMIS) for a microsatellite STSAT-3. COMIS images Earth's surface and atmosphere with ground sampling distances of 27 m at the 18~62 spectral bands (0.4 ~ 1.05 ${\mu}m$) for the nadir looking at an altitude of 700 km. COMIS has an imaging telescope and an imaging spectrometer box into which three electronics PCBs are embedded. The telescope images a $27m{\times}28km$ area of Earth surface onto a slit of dimensions $11.8{\mu}m{\times}12.1mm$. This corresponds to a ground sampling distance of 27 m and a swath width of 28 km for nadir looking posture at an altitude of 700 km. Then the optics relays and disperses the slit image onto the detector thereby producing a monochrome image of the entrance slit formed on each row of detector elements. The spectrum of each point in the row is imaged along a detector column. The optical mounts and housing structures are designed in order to prevent stray light from arriving onto the image and so deteriorating the signal to noise ratio (SNR). The stray light analysis, performed by a non-sequential ray tracing software (LightTools) with three dimensional housing and lens modeling, confirms that the ghost and stray light arriving at the detector plane has the relative intensity of ${\sim}10^{-5}$ and furthermore it locates outside the concerned image size i.e. the field of view of the optics.