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해상 발사를 위한 우주발사체, 발사플랫폼 및 발사체계 사례연구
정은상(Eunsang Jung),김기범(Gibum Kim),정종진(Jongjin Jung),김대래(Darae Kim),국승민(Seungmin Guk),이민우(Minwoo Lee) 한국추진공학회 2023 한국추진공학회지 Vol.27 No.4
The ocean-based launch is a system that performs launch at sea using launch platforms. In this research, we conduct a case study on ocean-based launch instances, mainly focusing on the case of the multinational corporation Sea Launch, China Aerospace Science and Technology Corporation, and others. Considering the inherent geographical constraints of the Korean space center, we find that the ocean-based platforms and processes can potentially be considered as an alternative means of space launch in Korea. Also, by investigating the types and characteristics of each country’s launch platforms, we propose an appropriate launch platform type for a potential Korean sea launch program.
과산화수소 촉매 분해를 이용한 파라핀 및 PE 하이브리드 로켓의 자연 점화 특성
안성용(Sungyong An),진정근(Jungkun Jin),정은상(Eunsang Jung),권세진(Sejin Kwon) 한국추진공학회 2009 한국추진공학회지 Vol.13 No.5
The auto-ignition tests of hybrid rockets with the concentrated hydrogen peroxide as an oxidizer were presented. Auto-ignition was successfully demonstrated by injecting decomposed gases from H₂O₂ into paraffin or polyethylene fuels. In addition, restart and instant ignition were realized with this rocket. For stable combustion, a higher L* value was required for the paraffin combustion compared with PE. On the other hand, much faster response time was demonstrated in case of a paraffin, which was 13 and 30 ㎳ at ignition delay and rise time respectively.
과산화수소 촉매 분해를 이용한 하이브리드 로켓 자연 점화
안성용(Sungyong An),진정근(Jungkun Jin),정은상(Eunsang Jung),권세진(Sejin Kwon) 한국추진공학회 2009 한국추진공학회 학술대회논문집 Vol.2009 No.11
고농도 과산화수소를 산화제로 이용하는 하이브리드 로켓의 자연 점화 연구를 수행하였다. 별도의 점화기 없이 촉매 반응을 통한 과산화수소 분해가스를 파라핀 및 폴리에틸렌에 분사함으로서 점화를 하였고 연속적인 재점화 및 즉각적인 점화 특성을 확인하였다. 안정적인 연소를 위해 파라핀은 PE에 비해 높은 연소실 특성길이가 요구된 반면, 펄스 응답특성은 점화지연 13 ms, 상승시간 30 ms 로서 폴리에틸렌의 응답성에 비해 두 배 가량 빠른 특성을 보였다. The auto-ignition tests of hybrid rockets with the concentrated hydrogen peroxide as an oxidizer were presented. Auto-ignition, restartability, and instant ignition were successfully demonstrated by injecting decomposed gases from H2O2 into paraffin or polyethylene fuels. In addition, much faster response time was demonstrated in case of a paraffin, which was 13 and 30 ms at ignition delay and rise time respectively.
장경민(Kyeongmin Jang),김희진(Heejin Kim),김수현(Soohyeon Kim),정은상(Eunsang Jung) 한국추진공학회 2019 한국추진공학회 학술대회논문집 Vol.2019 No.5
ADN은 친환경 추진제로 유럽을 중심으로 연구 · 개발되고 있으며, 고체 산화제나 액체 단일추진제로 모두 사용이 가능하다. ADN 단일추진제의 비추력은 259 sec로 하이드라진 이상의 성능을 보여주며, 촉매 분해 온도 또한 450 K로 우수하다. 본 연구에서는 친환경 추진제인 ADN의 생산성을 높이기 위해 전구물질인 KDN 합성 조건을 최적화 하고, UV-Vis, TGA 분석을 통해 수율을 측정하였다. 고 농도 질산(99%) 조건에서 KDN의 수율이 43.8%로 가장 높았으며, 질산의 농도가 진할수록 나이트로화 반응이 빠르기 때문이다. To center of Europe ADN is researched and developed as a green propellant, and ADN also used solid oxidizer and liquid monopropellant. ADN monopropellant’s specific impulse is 259 sec which is greater than hydrazine and catalytic decomposition temperature is 450 K. In this research, for improving of ADN productivity we optimized KDN synthesis condition which is used a precursor to ADN and, analyzed KDN yield using UV-Vis and TGA. The synthesis yield of KDN recorded the highest at 43.8% in 99% nitric acid condition. As the more nitric acid is condensed the more nitration rate is accelerated.
김희진(Heejin Kim),장경민(Kyeongmin Jang),김수현(Soohyeon Kim),정은상(Eunsang Jung) 한국추진공학회 2019 한국추진공학회 학술대회논문집 Vol.2019 No.5
본 연구에서는 5 N급 ADN 기반 단일추진제 추력기 설계 · 제작 기초연구로 전산유체역학 시뮬레이션을 통해 노즐 성능해석을 진행하였다. ADN 기반 단일추진제인 LMP-103S(ADN-물-메탄올-암모니아)와 FLP-106(ADN-물-메탄올)을 선정하였고, 혼합 비율은 LMP-103S(63%, 18.4%, 14%, 4.6%), FLP-106(64. 6%, 11.5%, 23.9%)로 결정하였다. LMP-103S와 FLP-106 추진제 분해 시 발생하는 가스의 성상에 따른 연소생성물 및 조성을 고려하여 노즐 요소별 치수를 설계하였다. 노즐 성능 해석을 위해 ANSYS Fluent 19.0 software k-ω SST 모델을 이용하였고, LMP-103S가 FLP-106보다 우수한 성능을 나타내었다. In this paper, nozzle performance analysis was carried out through the computational fluid dynamics simulation as a basic research on 5 N level ADN based monopropellant thruster design and fabrication. LMP-103S(ADN-water-methanol-ammonia) and FLP-106(ADN-water-methanol) were selected as the monopropellant based on ADN, and each mixing ratio of LMP-103S is (63%, 18.4%, 14%, 4.6%), and FLP -106 is (64.6%, 11.5%, 23.9%). The dimensions of the nozzle elements were designed considering the combustion products and composition according to the properties of gas generated during the decomposition of LMP-103S and FLP-106 propellants. For nozzle performance analysis, ANSYS Fluent 19.0 software k-ω SST model was used and LMP-103S have better performance than FLP-106.