• Title/Summary/Keyword: 접촉 점화성 추진제

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A Review of the Technical Development on Green Hypergolic Propellant (친환경 접촉점화 추진제 연구 개발 동향)

  • Park, Seonghyeon;Kang, Hongjae;Park, Youngchul;Lee, Jongkwang
    • Journal of the Korean Society of Propulsion Engineers
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    • v.24 no.4
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    • pp.79-88
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    • 2020
  • Hypergolic propellants have been widely used for space propulsion systems based their long-term storability and high ignition reliability. Since conventional hypergolic propellants are highly toxic and carcinogenic, handling and operating costs are significant. To overcome the drawbacks, numerous studies have been actively performed to develope new hypergolic propellants, ensuring that the combinations are high performance, low toxicity and low environmental impact. In the present study, a comprehensive survey was conducted to summarize the research and development of green hypergolic propellants involving hydrogen peroxide, nitric acid, and ionic liquids.

Experimental Ignition Delay Assessment of H2O2 Based Low Toxic Hypergolic Propellants with Variation of Reactive Additive Concentration (반응성 첨가제 농도에 따른 과산화수소 기반 저독성 접촉점화성 추진제의 점화지연 시험평가)

  • Rang, Seongmin;Kim, Kyu-Seop;Kwon, Sejin
    • Journal of Aerospace System Engineering
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    • v.14 no.3
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    • pp.24-31
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    • 2020
  • A study on the H2O2 based low toxic hypergolic propellant was conducted. The fuel candidates were chosen as a mixture of Amine solvent and reactive additive. The analytical performance was calculated via the NASA CEA code and 96% Isp of the NTO/UDMH was confirmed. The ignition delay measurement with drop test was performed and all candidates showed less than 10 ms in the best performance cases. Based on these results, the feasibility of high response H2O2 based low toxic hypergolic propellant was confirmed.

Non-ignition Evaluation Method for Hypergolic Propellant Using Microreactor (마이크로 반응기를 이용한 접촉점화 추진제의 비점화 평가 방법)

  • Lee, Kyounghwan;Park, Seonghyeon;Kang, Hongjae;Lee, Jongkwang
    • Journal of the Korean Society of Propulsion Engineers
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    • v.26 no.2
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    • pp.20-27
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    • 2022
  • Hypergolic propellant ignited spontaneously when fuel and oxidizer contact without ignition system. Due to this characteristic, the risk of accidents is high when new propellants are evaluated. Prevention of accidents is very important because the damage can be large when the accident occur. In this work, we proposed non-ignition evaluation method which can replace conventional ignition evaluation method by using microreactor. The reactor was fabricated by MEMS. The heat of reaction as according to fuel and NaBH4 was estimated. At the condition of highest heat of reaction ignition was observed by drop test.

Research Studies of Impingement Characteristics for Hypergolic Propellant (접촉 점화성 추진제의 충돌형 혼합 특성 연구 사례)

  • Kim, Kyu-Seop;Kim, Yehyun;Jung, Sangwoo;Jeong, Junyeong;Kwon, Sejin
    • Journal of the Korean Society of Propulsion Engineers
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    • v.23 no.5
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    • pp.90-100
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    • 2019
  • Hypergolic thrusters have been extensively researched and applied to spacecraft propulsion based on their simplicity and high reliability of ignition. Research on the impingement characteristics of $N_2O_4$/amine has been profoundly carried out since the 1960s in advanced countries, especially the United States. Recently, enhancements to advanced hypergolic thrusters using MON/MMH have been planned by NASA to improve compactness and high performance. In this work, technical studies were investigated on the mixing of hypergolic propellant and its combustion instabilities such as reactive separation flow and popping.

Ignition Test of an Oxidizer Rich Preburner (산화제과잉 예연소기 점화시험)

  • Moon, Il-Yoon;Moon, In-Sang;Yoo, Jae-Han;Jeon, Jae-Hyoung;Lee, Seon-Mi;Hong, Moon-Geun;Ha, Seong-Up;Kang, Sang-Hun;Lee, Soo-Young
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2011.11a
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    • pp.869-872
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    • 2011
  • Ignition tests of an oxidizer rich preburner for a staged combustion cycle liquid rocket engine were performed to evaluate combustion performance. Design operation conditions of the tested oxidizer rich preburner are about 60 of OF ratio and 20 MPa of combustion pressure. The entire kerosene and some LOx injected into the mixing head is burned in combustion chamber and the remaining LOx injected through center holes of combustion chamber is vaporized. Full flow ignition method with hypergolic fuel was used. Each propellant was supplied in two stages for soft ignition. Test results, low frequency oscillation was occurred in low flow rate conditions under 45% of design flow rate. Stable ignition in the course of design combustion pressure was able to induce by minimization of low flow rate ignition region to escape low frequency oscillation.

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A Review of the Technical Development on Ionic Liquids for Hypergolic Propellants (하이퍼골릭 이온성 추진제 연구 개발 동향)

  • Hongjae Kang;Kyounghwan Lee;Chungman Kim;Jongkwang Lee
    • Journal of the Korean Society of Propulsion Engineers
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    • v.26 no.6
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    • pp.74-85
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    • 2022
  • Since the late 1990s, the demand for developing green or reduced-toxic storable propellants has been rising to replace the existing toxic propellants. Most of the research activities are focusing on development of new hypergolic fuels and either white fuming nitric acid or hydrogen peroxide is utilized as an oxidizer. The newly-developed hypergolic fuels are classified as three types, catalytic fuel, reactive fuel, and ionic fuel. In the present study, recent R&D trend of ionic liquid propellants is described and the main results in the previous studies are analyzed.

Development of 500 Kgf Thrust Liquid Propellant Rocket Engine (추력 500 Kgf 액체추진제 로켓엔진 개발)

  • 정동호;조용재;정규상
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 1997.04a
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    • pp.3-10
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    • 1997
  • 본 연구에서는 추력 500 Kgf의 액체 추진기관을 설계, 제작 및 연소시험을 수행하여 연소 특성을 살펴보았다. 추진제로는 우주발사체 Booster용으로 폭넓게 사용되는 탄화수소계 연료인 kerosene과 산화제로 취급이 용이하고 저장 특성을 지닌 98 % White Fuming Nitric Acid(WFNA)를 사용하였고, 엔진 점화를 위해 WFNA와 접촉 발화성 (Hypergolic)을 갖는 Furfuryl Alcohol/Aniline 혼합액을 사용하였다. 로켓엔진은 20 Kgf/$cm^2$의 연소실 압력으로 500 Kgf의 평균 추력을 내도록 설계되었고, 연소실벽을 고온 연소가스로 부터 보호하기 위해 Film Cooling 방식을 적용하였다.

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Study of the Ignition with TEAL for an Oxygen Rich Preburner (산화제 과잉 예연소기를 위한 TEAL 점화연구)

  • Moon, In-Sang;Moon, Il-Yoon;You, Jae-Han;Lee, Sun-Mee;Lee, Soo-Yong
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2011.04a
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    • pp.97-100
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    • 2011
  • It is critical to set up the starting sequence of liquid rocket engines because not carefully arranged process can lead the engine damages. Thus, many efforts were made to prevent the hard start at the ignition. Hypergolic fuels are frequently used to ignite LRE and TEAL, one of the hypergolic fuel is also used for kerosene-LOx LRE ignition. However, since we are still lack of experiences igniting oxygen rich preburners of the staged combustion cycle engines, it would be helpful to estimate the TEAL ignition phenomena before the actual tests.

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Analysis of Safety Regulation and Chemical Reactivity of Hypergolic Propellant (접촉점화성 추진제 안전기준 및 상호반응성 분석)

  • Eungwoo Lee;Ahntae Shin;Sangyeon Cho;Byeongmun Park
    • Journal of the Korean Institute of Gas
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    • v.27 no.3
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    • pp.108-115
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    • 2023
  • Although hydrazine is an excellent liquid propellant, caution is required during storage and handling due to its high toxicity and reactivity. Safety guidelines should be established in consideration of the chemical reactivity by unintended leakage. In this study, the status of hydrazine facilities at launch site and safety standards for storing and handling were investigated and then, the reactivity between chemicals and hydrazine was analyzed. As a result of the analysis, hydrazine has reactivity with the exception of fuel oil. This paper emphasizes the imperative nature of constructing a dedicated hydrazine storage facility. Ensuring compatibility between hydrazine and the materials used in storage containers and handling equipment is crucial to prevent undesired reactions that could compromise safety. It was intended to be used as basic data to secure the range safety when handling hydrazine.