2차 분사의 위치 변화에 따른 로켓노즐 출구에서의 추력 분포 변화

• 영문명: The Variation of Thrust Distribution of the Rocket Nozzle Exit Plane with the Various Position of Secondary Injection
• 발행기관: 강원대학교 산업기술연구소
• 저자명: 김성준(Kim Sung Joon) 이진영(Lee Jin Young) 박명호(Park Myung Ho)
• 간행물 정보: 『산업기술연구』vol.20, 1~9쪽, 전체 9쪽
• 주제분류: 공학 > 공학일반
• 파일형태: PDF
• 발행일자: 2000.09.30

영문 초록

A numerical study is done on the thrust vector control using gaseous secondary injection in the rocket nozzle. A commercial code, PHOENICS, is used to simulate the rocket nozzle flow. A 45˚-15˚ conical nozzle is adopted to do numerical experiments. The flow in a rocket nozzle is assumed a steady, compressible, viscous flow. The exhaust gas of the rocket motor is used as an injectant to control the thrust vector of rocket at the constant rate of secondary injection flow. The injection location which is on the wall of rocket is chosen as a primary numerical variable. Computational results say that if the injection position is too close to nozzle throat, the reflected shock occurs. On the other hand, the more mass flow rate of injection is needed to get enough side thrust when the injection position is moved too far from the throat.

목차

Abstract

1. 서론

2. 이론적 배경

3. 연구 방법

5. 결론

참고문헌

키워드

로켓노즐 2차 분사 충격파 초음속 rocket nozzle secondary injection shock wave supersonic