Abstract
본 연구에서는 액체 로켓 엔진의 고온 연소 가스를 이용하여 축소형 고고도 환경 모사용 초음속 디퓨저 성능 실험을 수행하였다. 실험 장치는 연소실, 진공 챔버, 디퓨저로 구성되어 있다. 고고도 환경 모사 시험은 연소실 압력이 약 26, 29, 32barg 세 조건으로 수행하였고, 세가지 조건에서 모두 디퓨저는 성공적으로 시동되었으며 진공 챔버 압력이 약 140torr로 형성하였다. 이전의 상온 고압 가스를 이용한 디퓨저의 시동 특성과 비교하였을 때 시동 압력과 압력 분포 등의 시동 특성의 경향성은 유사하였으나, 고온 환경으로 인하여 진공 챔버에 형성되는 압력은 2배 정도 높은 것을 확인하였다. 본 연구 결과는 향후 실물형 고고도 환경 모사 시험 설비를 구축하는데 기초 자료로 활용될 수 있을 것으로 판단된다. Performance tests of a supersonic exhaust diffuser were conducted by using a liquid rocket engine for simulating high-altitude environment. The experimental setup consisted of a combustion chamber, a vacuum chamber and a diffuser. The combustion tests for simulating high-altitude environment were carried out at three cases by chamber pressure variation(26, 29, 32barg). The test results showed that the diffuser was started at all case and vacuum chamber pressures were approximately 140torr. The starting pressure using combustion gas was similar with that of cold gas, but the vacuum chamber pressure was relatively high because of high temperature in the vacuum chamber. The results of this test can be used as an essential database for the design of real-scale high-altitude simulation test facility in the future.
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More From: Journal of the Korean Society for Aeronautical & Space Sciences
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