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Design of Space Launch Vehicle Solenoid Valve for Cryogenic Environment

극저온 환경을 고려한 우주발사체용 솔레노이드 밸브 설계

  • Kim, Byunghun (Supply System Team, Korea Aerospace Research Institute) ;
  • Han, Sangyeop (Supply System Team, Korea Aerospace Research Institute) ;
  • Ko, Youngsung (Dept. of Aerospace Engineering, Chungnam National University)
  • Received : 2015.07.13
  • Accepted : 2015.10.12
  • Published : 2015.11.01

Abstract

Solenoid valves for space launch vehicles require the strict limitations on the size, weight and current consumption comparing to industrial solenoid valves. The preliminary design of a cryogenic and high pressure solenoid valve for propellant tank pressurization which can ensure the operation of solenoid valve under such strict limitation conditions was preformed. The Copper and Constantan materials in coil design have used to prevent the excessive rise of the current at cryogenic state. The measured current of solenoid valve at cryogenic temperature satisfies a design requirement.

발사체에 적용되는 솔레노이드 밸브의 경우 산업용 솔레노이드 밸브에 비해 엄격한 전류 및 무게, 크기 제한 조건을 요구한다. 이러한 제한 조건을 만족하며, 솔레노이드 밸브의 작동을 보장하기 위한 추진제탱크 가압제어용 솔레노이드 밸브 설계를 수행하였다. 극저온 상태에서 솔레노이드 전류 상승을 방지하기 위해 구리와 콘스탄탄 재료를 사용한 새로운 형태의 코일 설계를 적용하였으며, 시제품을 이용한 시험결과 측정된 전류는 설계 규격을 만족하고 있다.

Keywords

References

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