항공우주시스템공학회지 (Journal of Aerospace System Engineering)

  • 제14권3호
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  • Pages.42-50
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  • 2020
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  • 1976-6300(pISSN)
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  • 2508-7150(eISSN)
항공우주시스템공학회 (The Society for Aerospace System Engineering)
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우주용 영상센서 출력특성 교정용 흑체 설계의 해석적 유효성 검토

Numerical Investigation of Blackbody Design for Spaceborne Image Sensor Non-uniformity Characteristic Calibration

  • 김혜인 (조선대학교 항공우주공학과 우주기술융합연구실) ;
  • 최필경 (한화 시스템 기계설계팀) ;
  • 조문신 (한화 시스템 기계설계팀) ;
  • 오현웅 (조선대학교 항공우주공학과 우주기술융합연구실)
  • Kim, Hye-In (Department of Aerospace Engineering, Chosun University) ;
  • Choi, Pil-Gyeong (Mechanical Design Team, Hanwha Systems) ;
  • Jo, Mun-Shin (Mechanical Design Team, Hanwha Systems) ;
  • Oh, Hyun-Ung (Department of Aerospace Engineering, Chosun University)
  • 투고 : 2019.04.08
  • 심사 : 2020.02.12
  • 발행 : 2020.06.30
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초록

우주용 적외선 센서의 탑재 교정용 흑체 시스템은 궤도상에서 센서 출력특성 교정을 위해 다양한 기준온도에서 한정된 개수의 온도센서로부터 고정밀의 대표표면온도 추정이 가능해야 한다. 본 논문에서 제안된 흑체 시스템은 흑체 가열 후 잔열 수송을 위한 히트파이프를 흑체 후면 중앙의 일체형 플랜지에 결합하는 방식을 적용하였다. 따라서 흑체 표면온도구배 최소화와 함께 원형 대칭 형태의 온도구배를 얻을 수 있어 표면온도 추정이 용이하면서도 발사 및 궤도환경에서 하중이 가해지더라도 안정적인 히트파이프 접속부를 갖도록 하며, 복수의 히트파이프 적용에 따른 Fail Safe 설계가 가능하도록 한다. 또한 온도센서 부착작업이 용이하도록 센서를 흑체 외부 표면에 적용하더라도 높은 정확도로 표면온도 추정이 가능하다. 본 논문에서 제안된 흑체 시스템의 설계 유효성 입증을 위해 궤도 열해석을 수행하였으며, 해석결과를 기반으로 온도센서 개수 및 위치에 따른 대표표면온도 추정을 실시하였다.

For calibration of the non-uniformity characteristics of the space-borne infrared (IR) sensor, a black body system shall provide estimated representative surface temperature at various reference temperatures by using the limited number of temperature sensors. The black body system proposed in this study has an I/F flange integrated on the rear side of the black body for installation of the heat pipe to transfer the residual heat after the black body heat-up. This design allows for obtaining a circular symmetric thermal contour of black body with low surface temperature gradient, leading to much easier representative temperature estimation. Additionally, this provides mechanically stable thermal I/F under launch and on-orbit environmental loads, as well as allowing a fail safe design by using the two heat pipes. Also, a highly accurate temperature estimation is possible even if the temperature sensors are attached on the surface on the rear side of the black body. The effectiveness of the thermal design of the proposed black body has been verified through the on-orbit thermal analysis. Based on the results, the representative surface temperature was estimated according to the number and position of the temperature sensors.

키워드

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