• Title/Summary/Keyword: 고체 로켓 노즐

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Thrust modulation performance analysis of pintle-nozzle motor (핀틀 노즐형 로켓 모타의 추력 조절 성능에 관한 연구)

  • Kim, Joung-Keun;Park, Jong-Ho
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.37 no.4
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    • pp.392-398
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    • 2009
  • Theoretical thrust equations for the diverse nozzle expansion condition were derived. By using the obtained thrust equations, parametric studies were carried out to estimate the effect of pressure exponent, minimum operation pressure, ambient pressure and extinguishment pressure on thrust modulation performance in pintle-nozzle solid rocket motors. Analysis results showed that thrust turndown ratio can be easily attained by small nozzle-throat area variation at high pressure exponent, low minimum operation pressure, high ambient pressure and high extinguishment pressure condition. At those conditions, the highest chamber pressure to obtain the intended thrust turndown ratio can be minimized.

Development of the Korean 2.75 inch Rocket Propulsion System (한국형 2.75 인치 로켓 추진기관 개발)

  • Kang, Kiha;Lee, Yongbum;Yeom, Yongyeol;Bang, Gibok;Yang, Youngjun
    • Journal of the Korean Society of Propulsion Engineers
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    • v.18 no.3
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    • pp.70-77
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    • 2014
  • In this paper, the development of unique model of the 2.75 inch rocket propulsion system is described. Recently developed korean 2.75 inch rocket propulsion system shows the improvement of a flame stability resulted from a change in the configuration of propellant grain, and of an incidental ignition protection function using the EMI(electromagnetic interference) filter on ignition system. Moreover it is shown that a directional flight stability is improved by increasing the number of fins and changing the nozzle configuration. Static firing test and thermal shock test were conducted for the validation before flight, and flight test of 210 rounds of rockets was conducted to verify the trajectory uniformity. In addition, intellectual property issues can be overcome with the unique korean 2.75 inch rocket motor as well as the performance improvement.

Internal Flow Characteristics of Simulated Dual Pulse Rocket Motor by Using the Hot Gas and Cold Gas (Hot Gas와 Cold Gas를 이용한 모사 이중펄스 로켓 추진기관의 내부 유동 특성)

  • Cho, Kihong;Park, Jungho;Kim, Euiyong
    • Journal of the Korean Society of Propulsion Engineers
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    • v.19 no.2
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    • pp.1-8
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    • 2015
  • Dual pulse rocket motor is a variant of solid rocket motor with two propellant grain separated by a pulse separation device. The major performance of such a rocket motor is influenced by the change in the hole area of pulse separation device to nozzle throat area ratio. In this study, we performed flow analysis to investigate the internal flow characteristics according to the pulse separation device hole area to nozzle throat area ratio change. Gases used flow analysis were used combustion gas of HTPB/AP composite propellant and nitrogen gas. Flow analysis results of the dual pulse rocket motor were validated by comparison with experimental results of pneumatics. Commercial CFD code ANSYS FLUENT 14.5 is used in this study to simulate flow analysis.

The Effect of Pressure and Oxidation Mole Fraction on Ablation Rate of Graphite for Nozzle Throat Insert (압력과 산화몰분율이 그라이트 목삽입재의 삭마율에 미치는 영향)

  • Hahm, Heecheol;Kang, Yoongoo
    • Journal of the Korean Society of Propulsion Engineers
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    • v.18 no.1
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    • pp.8-15
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    • 2014
  • The ablation characteristics of graphite nozzle throat insert is analyzed for the use in solid rocket propulsion system. The propulsion system is composed of three types of conventional nozzles, such as De-Laval type, blast tube type, and submerged type. Various kinds of propellants are used in the thirteen kinds of propulsion system that has different shapes of each other. Total thirty seven tests are performed. From the results of the analysis, it is found that the ablation rate is higher for the higher average chamber pressure and the higher concentration of oxidizing species in combustion gas.

Numerical Study on Dynamic Characteristics of Pintle Nozzle for Variant Thrust (가변 추력용 핀틀 노즐의 동적 특성에 관한 수치적 연구)

  • Park, Hyung-Ju;Kim, Li-Na;Heo, Jun-Young;Sung, Hong-Gye;Yang, June-Seo
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2011.11a
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    • pp.213-217
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    • 2011
  • Unsteady numerical simulations of pintle nozzles were implemented for solid rocket thrust vector control. The variation of pintle location was considered using unsteady numerical techniques, and dynamic characteristics of various pintle models were investigated. In order to consider the variation of the pintle location, a moving mesh method was applied. The effects of shape and location of the pintle nozzle have been analytically investigated. And the results were compared with numerical results. The chamber pressure, mass flow and thrust are analyzed to take account dynamic characteristics of pintle performance.

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Numerical Study and Thrust Prediction of Pintle-Controlled Nozzle with Split-line TVC System (스플릿라인 TVC 시스템을 적용한 핀틀 추력조절 노즐의 유동해석 및 추력 성능 예측)

  • Jo, Hana
    • Journal of the Korean Society of Propulsion Engineers
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    • v.26 no.3
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    • pp.43-53
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    • 2022
  • In this study, analysis of the flow characteristics of pintle-controlled nozzle with split-line TVC system and the thrust performance prediction was performed. The numerical computation was verified by comparing the thrust coefficient derived from the analysis results with the experimental data. By applying the same numerical analysis technique, the flow characteristics of nozzle were confirmed according to operating altitude, pintle stroke position and TVC angle with the 1/10 scale. As the TVC angle increased, thrust loss occurred and the tendency of AF was different depending on the position of the pintle stroke. Based on the analysis results, the relation of thrust coefficient was derived by applying the response surface methods. The thrust performance model with a slight difference of 1.2% on average from the analysis result was generated.

Research and Development of KSR-III Apogee Kick Motor (KSR-III Apogee Kick Motor 연구 및 개발)

  • 조인현;오승협;강선일;황종선
    • Journal of the Korean Society of Propulsion Engineers
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    • v.5 no.4
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    • pp.40-49
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    • 2001
  • The basic research on AKM(Apogee Kick Motor) for space launch vehicle was carried out. AKM which will be used as 3rd stage solid rocket motor in 3-stage Korean Sounding Rocket(III) has been developing. KM is a solid rocket motor using composite propellant based on HTPB and is composed of composite motor case and submerged nozzle. To develop KM rocket motor satisfing a given set of requirement, firstly the full-scale KM with diameter 520mm was designed, then sub-scale motors reduced about 60% were manufactured and tested. Full-scale ground firing test is accomplished two times.

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조종장치 개발을 위한 지상 시험장치의 효과적인 연계방안

  • 김월동;박성준
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 1997.11a
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    • pp.4-4
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    • 1997
  • 로켓 조종장치는 크게 추력방향 조종(TVC, Thrust Vector Control) 장치, 측면추력조종(Lateral Thrust Control) 장치 그리고 공기역학 조종면으로 분류할 수 있다. 조종장치의 공통된 특징은 모터가 작동하거나 유도탄이 비행할 때만 타의 효과가 발생한다는 점이다. 그러므로 조종장치를 개발하기 위해서는 이상류 초음속 유동이나 삼음속 이상의 자유유동(freestream)을 지상에서 효과적으로 모의할 수 있는 지상 시험장치가 필요하다. 이 시험장치에는 초음속 풍동과 유동 시험장치(cold-flow test stand), 그리고 6분력 트러스트 스텐드가 포함된다. 삼성항공은 우주용 추진기관의 성능을 지상에서 간단한 장치를 구현하여 시험할 수 있는 모의연소 시험장치, 노즐유동에 포함된 고체입자를 직접 수집할 수 있는 고체입자 포집장치 등 각종 시험장치를 제작하였다. 이를 바탕으로 차세대 전술유도탄의 핵심기술가운데 하나인 조종장치와 이를 효과적으로 개발하기 위한 지상 시험장치 확보에 착수하고 있다.

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Combustion Characteristics of a Small Hybrid Rocket Using Paraffin-Wax as Fuel (파라핀 연료를 사용하는 소형 하이브리드 로켓의 연소 특성)

  • Kim, Kwon-Ho;Park, Hyun-Chun;Baek, Seung-Wook
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2008.11a
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    • pp.261-264
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    • 2008
  • This study experimentally examines combustion characteristics of a hybrid rocket in which solid paraffin is used as a fuel, while oxidizer is pure oxygen. Especially, the experiment investigates the effects of chamber pressure and configuration of fuel grain. The pressure inside the combustion chamber is varied by changing a flow rate of oxidizer. The regression rate is observed to increase as the chamber pressure does. There also exists the effects of shape of fuel grain on thrust. Characteristic of paraffin hybrid rocket changes with shape of fuel grain. When there is a room near the injector, thrust increases. On the other hand, the room near the nozzle does not contribute to thrust increasement.

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A Study on the Influence Factors for Ablation Rate of Graphite Nozzle Throat Insert (흑연 노즐목 삽입재의 삭마율에 미치는 영향 인자 연구)

  • Hahm, Heecheol;Kang, Yoongoo;Seo, Sangkyu
    • Journal of the Korean Society of Propulsion Engineers
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    • v.21 no.4
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    • pp.12-20
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    • 2017
  • The ablation characteristics of graphite nozzle throat insert was analyzed for the use in solid rocket propulsion system. The propulsion system was composed of three types of conventional nozzles, such as De-Laval type, blast tube type, and submerged type. Various kinds of propellants were used in ten kinds of propulsion system that had different shapes with each other. Total forty eight tests were performed. From the results of the analysis, it was found that the ablation rate was increased for the higher average chamber pressure and the higher oxidizer mole fraction. A useful correlation for nozzle throat ablation rate was developed in terms of the chamber pressure, oxidizer mole fraction, and throat size. The calculated ablation rates from the correlation showed agreement within ${\pm}0.10mm/s$ with the experimentally determined values.