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VARIATION OF LOCAL TIME OF ASCENDING NODE DUE TO THE ALTITUDE DECAY OF SUN-SYNCHRONOUS SATELLITE

태양동기위성의 고도감소에 의한 승교점 통과시각의 변화

  • 이병선 (한국전자통신연구원 위성관제기술연구팀) ;
  • 황유라 (한국전자통신연구원 위성관제기술연구팀) ;
  • 김해연 (한국전자통신연구원 위성관제기술연구팀) ;
  • 윤재철 (한국항공우주연구원 다목적 실용위성 체계종합그룹) ;
  • 김해동 (한국항공우주연구원 우주응용센터) ;
  • 김재훈 (한국전자통신연구원 위성관제기술연구팀)
  • Published : 2006.06.01

Abstract

Variation of the Local Time of Ascending Node (LTAN) has been analysed according to initial inclinations when the altitude of Sun-synchronous satellite is continuously decreased due to the atmospheric drag. Orbit predictions of 3 years have been performed with the satellite of 500 km altitude when the initial LTAN were set to 06:00, 09:00, 12:00, 15:00, and 18:00. Different profiles of the inclination and LTAN have been obtained according to the satellite altitude decay and initial LTAN value. Using the profiles of the inclination and LTAN, initial orbital elements can be derived for minimizing the LTAN variations during the mission life time of the sun-synchronous satellite without any on-board thrusters for orbit maneuvers.

Keywords

sun-synchronous orbit;orbital decay;local time of ascending node

References

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