• Title/Summary/Keyword: Launch Vehicle Propulsion System

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The Review of Saturn V 1st Stage (S-IC) Propulsion System (Saturn V 발사체 1단(S-IC) 추진기관 시스템 연구)

  • Hong, Yonggi;Kim, Cheulwoong
    • Journal of the Korean Society of Propulsion Engineers
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    • v.19 no.2
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    • pp.73-80
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    • 2015
  • It had been almost a half century since Apollo Mission was ended. However, in these days, a lot of researches are being conducted for restoration and making improvements in technologies used in Saturn V rocket's development. This study reviews the first stage of Saturn V rocket(S-IC), from development history to technologies in various subsystems such as engine purge system, POGO suppression system, hydraulic and pneumatic control system, propellant dispersion system, telemetry system and retrorocket system. Understandings of S-IC stage's operation systems would be helpful in understanding of launch vehicle system and reduction of time and cost in future development process.

Development Study on the Prototype of Level Measurement System of Launch Vehicle Propellant Tanks (추진제 충전량 측정시스템 시제 개발 연구)

  • Shin, Dong-Sun;Han, Sang-Yeop;Cho, In-Hyun
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2010.11a
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    • pp.590-593
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    • 2010
  • The processes of supplying propellants into propellant tanks play important roles during launch preparation of satellite launch vehicle. The total weight of launch vehicle greatly depends on the accuracy of filling quantity of propellant during launch preparation. Among propellants used for launch vehicles a cryogenic propellant such as liquid oxygen is widely adapted as an oxidizer for launch vehicles. Such cryogenic propellant usually resides in a propellant tank as two-phase fluid with liquid and gas, which needs an accurate level measurement system to detect the position of propellant surface precisely. In this paper the fabricating process of a level measurement system using capacitance type with three electrodes is analyzed. In addition, the change of electric signal according to the height of liquid is verified by testing the level measurement system under consideration. The results of tests shows as expected the linear trend of voltage according to the change of water height in a tank.

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Calculation and Comparison of Liquid Oxygen Filling System between the KSLV-I Flight Test Data and the Modeling of the KSLV-II Launch Complex (한국형발사체 발사대시스템 산화제공급계 충전 운용 설계의 검증을 위한 나로호 비행시험 실증 자료 분석)

  • Seo, Mansu;Lee, Jae Jun;Hong, Ilgu;Kang, Sunil
    • Journal of the Korean Society of Propulsion Engineers
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    • v.22 no.5
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    • pp.107-114
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    • 2018
  • Korea Space Launch Vehicle (KSLV)-I flight test data and the modified 1-dimensional steady state modeling data from the critical design results of the KSLV-II liquid oxygen filling system operation are compared to validate the reliability of critical design modeling. A comparison of major flow rates and pressure values between test data and calculation results are conducted. The relative errors relative to maximum total flow rate for each cooling, filling, and replenishment mode are determined within 6.7%. Calculated pressure values at the outlet of the pump and the inlet of flow control valves are within 5.1%. The pressure at the inlet of the launch vehicle for each operation mode are within the measured pressure range.

Liquid-monopropellant Thrusters for the 3-axis Attitude Control of Space Launch Vehicles -Part 2: A Practical Application of Flight-axes/Attitude Control Thrusters to the Space Launch Vehicle and Their Design Development Localization (우주발사체 3축 자세제어용 단일액체추진제 추력기 -Part 2: 비행축/자세제어용 추력기의 우주발사체 적용과 국내 설계개발)

  • Kim, Jeong-Soo;Bae, Dae-Seok;Jung, Hun;Seo, Hang-Seok;Kim, In-Tae
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2011.04a
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    • pp.179-182
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    • 2011
  • A practical application of flight-axes/attitude control thrusters to the space launch vehicle and their design development localization are investigated and analyzed. Hydrazine thrusters are mostly used in a final stage of space launch vehicles on account of its higher specific impulse and reliability necessary for the precise attitude control attaining the orbit insertion with higher accuracy.

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A Study on Measurement and Elimination Methods of Dissolved Nitrogen in Kerosene (케로신 내 용존질소 측정 및 제거 방법 연구)

  • Lee, Wongu;Kim, Seong Lyong;Ahn, Kyubok
    • Journal of the Korean Society of Propulsion Engineers
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    • v.22 no.6
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    • pp.142-148
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    • 2018
  • To improve the performance of a launch vehicle, kerosene, a launch vehicle fuel, undergoes a densification process. Liquid nitrogen injection cooling is an effective densification method which has a simple system and is inexpensive. During the cooling process, however, nitrogen may dissolve in the kerosene, possibly resulting in changes to fuel properties. Therefore, it is essential to measure and eliminate the amount of dissolved nitrogen in the kerosene. In this study, the vacuum extraction principle is introduced to measure the content of dissolved nitrogen in the kerosene. In addition, the experimental results, which used a designed/manufactured nitrogen sampling device, are described. From the results, the validity of the nitrogen sampling device and the dissolved nitrogen measurement/elimination methods was demonstrated.

On the Pressurization System for a Launch Vehicle (우주발사체 가압시스템 설계)

  • Hong, Moon-Geun;Chung, Yong-Gahp;Kim, Young-Mog
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2006.11a
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    • pp.113-115
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    • 2006
  • Consulting Stout & Snell's paper[1], design approaches for the pressurization system for a launch vehicle are introduced. We have outlined the typical system requirements and a dynamic model of the pressurization system. A brief summary on the control loop design for multiple on-off valve control systems has been also presented.

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Optimum Design Method for Pressure-reducing System using High-pressure Gas (고압가스감압시스템 최적화 설계기법)

  • Chung, Yong-Gahp;Cho, Nam-Kyung
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2010.11a
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    • pp.748-751
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    • 2010
  • To launch rocket on launch pad, propellants and gases are charged into the rocket by remote control system. Using pneumatic pressure-reducing regulators, kinds of gases with various pressure levels are supplied into launch pad. As most of operations for launching the vehicle are remotely controled in the launch control room, pressure pulsations due to rapidly gas supply at the upstream of regulators can make the required operating pressure range missed and cause damage to the regulators. In this paper, the optimum design methods of pressure regulators of pressure-reducing system on launch pad using high-pressure gases were investigated to solve the aforementioned problems and for stable gas supply to launch pad.

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Analysis on the Filling Mode of Propellant Supply System for the Korea Space Launch Vehicle (한국형발사체 추진제공급시스템 충전모드 해석)

  • Lee, Jaejun;Park, Sangmin;Kang, Sunil;Oh, Hwayoung;Jung, Eun Sang
    • Journal of the Korean Society of Propulsion Engineers
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    • v.20 no.4
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    • pp.50-58
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    • 2016
  • Korean Space Launch Vehicle (KSLV-II) Propellant Supply System charges liquid oxygen and kerosene to each propellant tank for the stages. To charge the launch vehicle propellant tank safety, the propellant charge flow rates and scenarios should be defined. First, the Propellant Supply System was modeled with 1D flow analysis program. The control valve capacity and orifice size were calculated by performing the 1D steady state simulation. Second, the 1D transient simulation was performed by using the steady state simulation results. As propellants were being charged at the each tank, the increased tank liquid level decreases the charge flow rate. Consequently, the proposed supply system satisfies the required design charging conditions.

Performance Requirement Analysis and Weight Estimation of Reusable Launch Vehicle using Rocket based Air-breathing Engine (로켓기반 공기흡입추진 엔진이 적용된 재사용 발사체의 요구 성능 및 중량 분석)

  • Lee, Kyung-Jae;Yang, Inyoung;Lee, Yang-Ji;Kim, Chun-Taek;Yang, Soo-Seok
    • Journal of the Korean Society of Propulsion Engineers
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    • v.19 no.6
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    • pp.10-18
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    • 2015
  • Performance requirement analysis and weight estimation of a reusable launch vehicle with a rocket-based air-breathing engine(RBCC : Rocket Based Combined Cycle) were performed. Performance model for an RBCC engine was developed and integrated with flight trajectory model. The integrated engine-trajectory model was validated by comparing the results with those from previous research reference. Based on the new engine-trajectory model and previous research results, engine performance requirements were derived for an reusable launching vehicle with gross take-off weight of 15 tones. Dependence of the propellant amount requirement on the mode transition Mach number of the engine was also analyzed.

Comparison of the Mission Performance of Korean GEO Launch Vehicles for Several Propulsion Options (시스템 구성에 따른 정지궤도 발사체의 임무성능 비교)

  • Hong, Mir;Yang, Seong-Min;Kim, Hye-Sung;Yoon, Youngbin;Choi, Jeong-Yeol
    • Journal of the Korean Society of Propulsion Engineers
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    • v.21 no.2
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    • pp.60-71
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    • 2017
  • A trajectory analysis program is developed using a 3DOF trajectory model for the performance analysis of geostationary launch vehicles by system options. Launch trajectory and the performance of injection at GTO was estimated using this program for several propellant options, engine types, number of engines and the location of launch site. Results of the analysis presents that the possibility of mission accomplishment by several design options using domestic launch sites and the development direction of GEO launch vehicles.