지원사업
학술연구/단체지원/교육 등 연구자 활동을 지속하도록 DBpia가 지원하고 있어요.
커뮤니티
연구자들이 자신의 연구와 전문성을 널리 알리고, 새로운 협력의 기회를 만들 수 있는 네트워킹 공간이에요.
논문 기본 정보
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- 학위논문
- 저자정보
- 발행연도
- 2014
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이 논문의 연구 히스토리 (5)
2014
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Nozzle configurations and atmospheric conditions play a significant role in the infrared signature level of aircraft propulsion system. Various convergent nozzles of an unmanned aircraft under different atmospheric conditions are considered.
The circular convergent nozzle is designed through a performance analysis of an unmanned aircraft. The configuration of circular convergent nozzle was changed by selecting the reference aircraft. An analysis of thermal flow field and nozzle surface temperature distribution is conducted using a compressible CFD code. From the information of the thermal flow fields, plume and solid IR signatures are calculated through the narrow-band model and RadThermIR code.
It is shown that the IR level in rear direction is considerably reduced in deformed nozzles, whereas the IR level in adjacent azimuth angles is increased in aspect ratios around 6 due to the plume spreading effect caused by high aspect ratio of nozzles. In addition, an analysis of atmospheric transmissivity for various seasons and observation distance is conducted using a LOWTRAN 7 code and subsequently IR signature is calculated by considering atmospheric effects. It is shown that the IR signature is reduced significantly in summer season and near the band of carbon dioxide in case of relatively long distance.
The circular convergent nozzle is designed through a performance analysis of an unmanned aircraft. The configuration of circular convergent nozzle was changed by selecting the reference aircraft. An analysis of thermal flow field and nozzle surface temperature distribution is conducted using a compressible CFD code. From the information of the thermal flow fields, plume and solid IR signatures are calculated through the narrow-band model and RadThermIR code.
It is shown that the IR level in rear direction is considerably reduced in deformed nozzles, whereas the IR level in adjacent azimuth angles is increased in aspect ratios around 6 due to the plume spreading effect caused by high aspect ratio of nozzles. In addition, an analysis of atmospheric transmissivity for various seasons and observation distance is conducted using a LOWTRAN 7 code and subsequently IR signature is calculated by considering atmospheric effects. It is shown that the IR signature is reduced significantly in summer season and near the band of carbon dioxide in case of relatively long distance.
목차
Ⅰ. 서 론 11. 연구 배경 12. 연구 목적 53. 이전 연구 및 사례조사 7Ⅱ. 본론 171. 열유동장 해석을 위한 노즐 형상설계 171) 항공기 성능 분석 및 원형노즐 설계 172) 형상변형 설계 변수를 적용한 노즐 설계 202. 노즐 형상에 따른 열유동장 해석 231) 계산격자 및 경계조건 232) 열유동장 해석 결과의 타당성 검증 243. 노즐 형상에 따른 IR 신호 분석 271) Narrow-band 모델을 이용한 spectral intensity 계산 272) RadThermIR을 이용한 고체 IR 신호 계산 303) LOWTRAN 7을 이용한 대기투과율 계산 314. 결과 및 분석 321) 형상변형에 따른 열유동장 해석 결과 322) 플룸 IR 신호 분석 결과 353) 고체 IR 신호 분석 결과 394) 대기효과를 고려한 플룸 IR 신호 분석 결과 43Ⅲ. 결론 49참고 문헌 51감사의 글 54
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