• Title/Summary/Keyword: 지구저궤도

Search Result 143, Processing Time 0.022 seconds

Prediction of Parabolic Antenna Satellite Drag Force in Low Earth Orbit using Direct Simulation Monte Carlo Method (직접모사법을 이용한 지구 저궤도 파라볼릭 안테나 탑재 위성의 항력 예측)

  • Shin, Somin;Na, Kyung-Su;Lee, Juyoung;Cho, Ki-Dae
    • Journal of the Korean Society for Aeronautical & Space Sciences
    • /
    • v.42 no.7
    • /
    • pp.616-621
    • /
    • 2014

  • Consumption of the fuel on the satellite operating in low earth orbit, is increased due to the air resistance and the amount of increase makes the satellite lifetime decrease or the satellite mass risen. Therefore the prediction of drag force of the satellite is important. In the paper, drag force and drag coefficient analysis of the parabolic antenna satellite in low earth orbit using direct simulation monte carlo method (DSMC) is conducted according to the mission altitude and angle of attack. To verify the DSMC simulated rarefied air movement, Starshine satellite drag coefficient according to the altitude and gas-surface interaction are compared with the flight data. Finally, from the analysis results, it leads to appropriate satellite drag coefficient for orbit lifetime calculation.

  • https://doi.org/10.5139/JKSAS.2014.42.7.616 인용 PDF KSCI

Re-entry Survivability and On-Ground Risk Analysis of Low Earth Orbit Satellite (저궤도 위성의 대기권 재진입 시 생존성 및 피해확률 분석)

  • Jeong, Soon-Woo;Min, Chan-Oh;Lee, Mi-Hyun;Lee, Dae-Woo;Cho, Kyeum-Rae;Bainum, Peter M.
    • Journal of the Korean Society for Aeronautical & Space Sciences
    • /
    • v.42 no.2
    • /
    • pp.158-164
    • /
    • 2014

  • LEO(Low Earth Orbit) Satellite which is discarded should be reentered to atmosphere in 25 years by '25 years rule' of IADC(Inter-Agency Space Debris Coordination Committee) Guidelines. If the parts of satellite are survived from severe aerothermodynamic condition, it could damage to human and property. South Korea operates KOMPSAT-2 and STSAT series as LEO satellite. It is necessary to dispose of them by reentering atmosphere. Therefore this paper analyze the trajectory, survivability, casualty area and casualty probability of a virtual LEO satellite using ESA(European Space Agency)'s DRAMA(Debris Risk Assesment and Mitigation Analysis) tool. As a result, it is noted that casuality area is $15.2742m^2$ and casualty probability is 5.9614E-03 then will be survived 198.831kg.

  • https://doi.org/10.5139/JKSAS.2014.42.2.158 인용 PDF KSCI