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

  • 제42권2호
  • /
  • Pages.144-149
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  • 2014
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  • 1225-1348(pISSN)
  • /
  • 2287-6871(eISSN)
한국항공우주학회 (The Korean Society for Aeronautical and Space Sciences)
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하이드라진 추력기의 추력실 특성길이 변화가 연소성능에 미치는 영향

Effects of Characteristic Length Variation for Thrust Chamber on the Hot-fire Performance of Hydrazine Thruster

  • Kim, Jong Hyun (Department of Mechanical Engineering, Graduate School, Pukyong National University) ;
  • Jung, Hun (Department of Mechanical Engineering, Graduate School, Pukyong National University) ;
  • Kim, Jeong Soo (Department of Mechanical Engineering, Pukyong National University)
  • 투고 : 2013.10.29
  • 심사 : 2014.01.31
  • 발행 : 2014.02.01
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초록

우주발사체 자세제어용 하이드라진 추력기의 추력실 특성길이($L^*$) 변화에 따른 연소성능을 확인하기 위해 개발모델 추력기에 대한 지상연소시험을 수행하였다. 각각의 추력기에 대한 성능특성이 추진제 주입압력 2.41 MPa (350 psia)에서의 정상상태 추력, 비추력, 응답특성 및 특성속도 등과 같은 성능변수로 분석되었다. 시험결과, 표준모델 대비 추력실 특성길이의 증가와 감소에 따라 특성속도 및 비추력성능이 공히 감소하였던 바, 표준모델의 추력실 형상이 요구성능에 대하여 가장 적합하게 설계되었다는 사실이 확인되었다.

A ground firing test for hot-fire performance evaluation according to the characteristic length($L^*$) variation of thrust chamber was carried out for the hydrazine thruster which may be employed in space launch vehicles. A scrutiny into the performance characteristics of each thruster is made in terms of thrust, specific impulse, response characteristics, and characteristic velocity at steady-state firing mode with propellant inlet pressure of 2.41 MPa (350 psia). Through the test results, it has been verified that performance of characteristic velocity and specific impulse degrades as the characteristic length deviates from that of the standard model. Thus, it is confirmed that the thrust chamber configuration of standard model was suitably designed for the requirement specified.

키워드

참고문헌

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