Canted Slit 형상의 핀틀 인젝터 로켓엔진의 특성길이와 운동량비에 따른 연소성능

다국어 초록 (Multilingual Abstract)

In this study, a pintle injector rocket engine which uses kerosene and liquid oxygen as propellants was manufactured by collecting basic design data and establishing a design procedure. Combustion performance of the liquid rocket engine was investigated by characteristic velocity efficiency with characteristic length of the combustion chamber and total momentum ratio. As a result of hot fire tests, it showed that the engine had shorter characteristic length comparing to those of other type injectors, which was known as recommended value with the propellant combination. Also, the characteristic velocity efficiency was greatly affected by total momentum ratio and almost constant within 1.0~1.5.

참고문헌 (Reference)

1 김수종, "하이브리드 로켓 모터에 대한 연소 실험 측정 불확도" 한국항공운항학회 19 (19): 7-14, 2011

2 유기정, "핀틀 인젝터의 개도가 액체-기체 상압 분무에 미치는 영향" 한국항공우주학회 43 (43): 585-592, 2015

3 Dressler, G. A., "TRW Pintle Engine Heritage and Performance Characteristics" AIAA 2000

4 Mueller, T., "TRW 40Klbf LOX/RP-1 Low Cost Pintle Engine Test Results" AIAA 2000

5 Kim, H. M., "Spray Characteristic of Liquid-Liquid Pintle injectors" 787-790, 2014

6 Gromski, J. M., "Northrop Grumman TR202 LOX/LH2 Deep Throttling Engine Technology Project Status" AIAA 2010

7 Yu, K. J., "Liquid Sheet Breakup of Water Simulants with Pintle Injector" 368-369, 2014

8 Nasser Ashgriz, "Handbook of Atomization and Sprays" Springer 2011

9 Calvignac, J., "Design and Testing of Non-Toxic RCS Thrusters for second Generation Reusable Launch Vehicle" AIAA 2003

10 Daric, W.E., "Design and Preliminary Hot Fire and Cold Flow Testing of Pintle Injectors" The graduate school of the pennsylvania state university 1996