Journal of the Korean Society for Aeronautical & Space Sciences (한국항공우주학회지)

The Korean Society for Aeronautical and Space Sciences (한국항공우주학회)
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Development of BLDC Motor Driven Cryogenic Thrust Control Valve for Liquid Propellant Rocket Engine

BLDC 모터로 구동되는 액체 추진제 로켓엔진용 극저온 추력제어밸브 개발

  • Received : 2010.05.20
  • Accepted : 2010.09.07
  • Published : 2010.10.01
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Abstract

This paper summarizes the activities performed for the development of a BLDC(Brushless Direct Current) motor driven cryogenic thrust control valve with application to KSLV-II rocket engine. The developed thrust control valve can modulate the flow rate of liquid oxygen under cryogenic temperature of 90K and high pressure of 113.2 bar with the help of electro-mechanical actuator driven by a BLDC motor. This valve can be applied to an engine combustion test after minor change because all development certification test have been performed successfully.

본 논문에서는 KSLV-II의 로켓엔진에 사용될 BLDC 모터로 구동되는 극저온 추력제어 밸브의 개발 과정 및 결과를 소개하였다. 개발된 추력제어밸브는 90K의 극저온, 113.2bar의 고압 환경에서 액체산소의 유량을 BLDC 모터로 작동되는 밸브 구동기를 통해 조절할 수 있다. 추력제어밸브는 모든 개발 인증시험을 통과하였으므로 향후 일부 하드웨어 수정 후, 엔진 연소시험에 적용이 가능하다.

Keywords

References

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Cited by

  1. A Study on Control Algorithm of Thrust Control Valve for a Liquid Rocket Engine vol.40, pp.12, 2012, https://doi.org/10.5139/JKSAS.2012.40.12.1055