RAPID INITIAL DETUMBLING STRATEGY FOR MICOR/NANOSATELLITE WITH PITCH BIAS MOMENTUM SYSTEM

피치 바이어스 모멘텀 방식 초소형 위성의 초기 자세 획득 방안 연구

  • Lee Byung-Hoon (Space System Research Lab, Hankuk Aviation University) ;
  • Choi Jung-Won (Space System Research Lab, Hankuk Aviation University) ;
  • Yun Mi-Yeon (Space System Research Lab, Hankuk Aviation University) ;
  • Chang Young-Keun (Space System Research Lab, Hankuk Aviation University)
  • 이병훈 (한국항공대학교 우주시스템 연구실) ;
  • 최정원 (한국항공대학교 우주시스템 연구실) ;
  • 윤미연 (한국항공대학교 우주시스템 연구실) ;
  • 장영근 (한국항공대학교 우주시스템 연구실)
  • Published : 2006.04.01

Abstract

B-dot logic is generally used for controlling the initial tip-off rate. However, it has the disadvantage of taking a relatively long time to control the initial tip-off rate. To solve this problem, this paper suggests a new detumbling control method to be able to adapt to micro/nanosatellite with the pitch bias momentum system. Proposed detumbling method was able to control the angular rate within 20 minutes which is a significant reduction compared to conventional methods.