• Title/Summary/Keyword: 추진제 공급계

Search Result 58, Processing Time 0.024 seconds

The test facility for propellant feeding system of liquid propulsion system (액체추진기관 추진제 공급계 시험설비)

  • Kwon Oh-Sung;Na Han-Bee;Lee Joong-Youp;Jeong Yong-Gap;Cho Nam-Kyung;Kil Gyoung-Sub
    • Proceedings of the Korean Society of Propulsion Engineers Conference
    • /
    • 2004.10a
    • /
    • pp.79-82
    • /
    • 2004
  • Propellant feeding system is the system to satisfy propellant feeding requirements(mass flow rate, pressure, temperature) at engine inlet of launch vehicle. Propellant feeding test facility is being constructed for the development scheme of pressurization system, processing in tank, propellant piping system, and flow control system that are main technologies in order to develope propellant feeding system. This paper introduces the propellant feeding test facility being constructed in KARI.

  • PDF

Dynamic Characteristic Analysis of KSR-III Propulsion Feeding System (KSR-III 추진기관 공급계 동특성 해석)

  • 정태규;정영석;조인현;권오성;정동호;이대성
    • Journal of the Korean Society of Propulsion Engineers
    • /
    • v.5 no.4
    • /
    • pp.75-82
    • /
    • 2001
  • KSR-III propulsion feeding system is designed to feed a certain amount of propellant to engine by the end of combustion. The oscillation of propellant to engine would cause combustion instability and thrust oscillation and POGO phenomenon. This article deal with analysis performed such as the effect of rocket acceleration on the propulsion system and POGO analysis to ensure the performance of KSR-III

  • PDF

Review of Propellant Vibration and Control of Liquid Rocket Fuselage Feeding System (액체로켓 기체공급계의 추진제 진동특성 및 제어기술 동향)

  • Cho, Nam-Kyung;Kho, Hyun-Seok;Han, Sang-Yeop;Cho, In-Hyun
    • Proceedings of the Korean Society of Propulsion Engineers Conference
    • /
    • 2010.05a
    • /
    • pp.89-94
    • /
    • 2010
  • Fuselage propellant feeding system should supply propellants to engine with required flow rate, temperature and pressure. Propellant vibration in engine and feeding line changes feeding characteristics, and frequently inhibits to satisfy the required feeding requirements. Sloshing and POGO vibration are known to be the major vibration phenomena. Concerning sloshing and POGO, vehicle control and structural dynamics aspects are extensively studied, whereas, its effect on propellant feeding performance is not clearly understood. This paper focuses on the deviation of required feeding performance due to propellant vibration. Overall characteristics of propellant vibration and its effect on propellant supply to engine are reviewed and control mechanism for suppressing vibration is introduced.

  • PDF

Temperature Control System of Cryogenic Propellant for Launch Complex (발사대 극저온 추진제 온도조절 시스템)

  • Yu, Byung-Il;Park, Soon-Young;Park, Pyun-Gu;Kim, Ji-Hoon
    • Proceedings of the Korean Society of Propulsion Engineers Conference
    • /
    • 2011.11a
    • /
    • pp.793-794
    • /
    • 2011
  • In launch process, propellants should be supplied with established temperature range for engine normal operation. In order to satisfy this temperature condition, propellant feeding systems should be considered some effects during operation. This paper studied liquid oxygen filling system operation process and cooling method of liquid oxygen during launch process.

  • PDF

PTA-I test of KSR-III Propulsion Feeding System (KSR-III 추진기관 공급계 PTA-I 종합수류시험)

  • 권오성;정영석;조인현;정태규;오승협
    • Journal of the Korean Society of Propulsion Engineers
    • /
    • v.7 no.3
    • /
    • pp.22-29
    • /
    • 2003
  • The propulsion feeding system of KSR-III is composed of tubes, valves and PSC, and controls the flow of propellant entering to engine. The test of PTA-I is carried out to verify the characteristic of propulsion feeding system and component. The tests of operation characteristic of component, hydraulic characteristic of tubes, flow control using venturi, oscillation of dynamic pressure, characteristic of regulator are carried out. Troubles of component are found out, and renewed, and the performance of the propulsion feeding system is verified through PTA-I. The results of PTA-I are used to the configuration of propulsion feeding system and test of PTA-II.

Pogo Analysis on the KSR-III Propulsion Feeding System (KSR-III 추진기관 공급계 pogo 해석)

  • ;;O. M. Menshikova
    • Journal of the Korean Society of Propulsion Engineers
    • /
    • v.6 no.3
    • /
    • pp.45-52
    • /
    • 2002
  • This article deals with the introduction of longitudinal instability of liquid rocket (pogo) and the analytical results on the frequency responses of Korean Sounding Rocket (KSR-III) propulsion feeding system. Both the stiffness of bellows and the cavitation volume of venturi affect the frequency response of the feeding system. Especially, bellows has a great roll to reduce the natural frequency of the feeding system. Also, oxidizer and fuel feeding systems of the KSR-III have natural frequencies of about 280Hz and 90Hz, respectively.

The Way of Determinating the Optimal Parameters of the Propellant Tank Pressurization Gas in the Feeding System for Liquid Rocket Engine (액체로켓 추진기관의 추진제탱크 가압시스템 최적변수 설계 방법)

  • Bershadskiy V.A.;Cho Kie-Joo;Lim Seok-Hee;Jung Young-Suk;Cho Gyu-Sik;Oh Seung-Hyub
    • Journal of the Korean Society of Propulsion Engineers
    • /
    • v.9 no.2
    • /
    • pp.62-69
    • /
    • 2005
  • The design method to calculate the main features of propellant tank pressurization system during the development procedure of propellant feed system of the liquid rocket engine was suggested. We have considered the influences of parameters of pressurization gas on the efficiency of the thermodynamic processes in the tank. The optimum value of temperature and velocity of pressurization gas at the entrance of tank are obtained by the suggested way.

Pogo Suppressor Design of a Space Launch Vehicle using Multiple-Objective Optimization Approach (다목적함수 최적화 기법을 이용한 우주발사체의 포고억제기 설계)

  • Yoon, NamKyung;Yoo, JeongUk;Park, KookJin;Shin, SangJoon
    • Journal of the Korean Society of Propulsion Engineers
    • /
    • v.25 no.1
    • /
    • pp.1-11
    • /
    • 2021
  • POGO is a dynamic axial instability phenomenon that occurs in liquid-propelled rockets. As the natural frequencies of the fuselage and those of the propellant supply system become closer, the entire system will become unstable. To predict POGO, the propellant (oxidant and fuel) tank in the first stage is modeled as a shell element, and the remaining components, the engine and the upper part, are modeled as mass-spring, and structural analysis is performed. The transmission line model is used to predict the pressure and flow perturbation of the propellant supply system. In this paper, the closed-loop transfer function is constructed by integrating the fuselage structure and fluid modeling as described above. The pogo suppressor consists of a branch pipe and an accumulator that absorbs pressure fluctuations in a passive manner and is located in the middle of the propellant supply system. The design parameters for its design optimization to suppress the decay phenomenon are set as the diameter, length of the branch pipe, and accumulator. Multiple-objective function optimization is performed by setting the energy minimization of the closed loop transfer function in terms of to the mass of the pogo suppressor and that of the propellant as the objective function.

Development of Propellant On-Board Feeding System of Pump-fed Liquid Rocket Propulsion System (터보펌프식 발사체 추진기관의 기체공급계 개발)

  • Cho, Nam-Kyung;Jeong, Yong-Gahp;Kwon, Oh-Sung;Han, Sang-Yeop;Kim, Young-Mog
    • Proceedings of the Korean Society of Propulsion Engineers Conference
    • /
    • 2006.11a
    • /
    • pp.122-126
    • /
    • 2006
  • Two types of pressurization system and low weight feeding piping system are developed. With sub-system tests, ullage pressure control performance was verified for 1 step and 2 step pressurization system and the feeding performance of feeding piping system was also verified. The weight of the feeding piping system is low enough for the application of launch vehicle. In addition, LOX conditioning system is developed for avoiding geysering and LOX temperature rise. Integrated performance was verified through integrated on-board feeding system performance tests.

  • PDF

Proposal of Pipe Pressure Mode Analysis Method in Propulsion System for Predicting the Pogo of Space Launch Vehicle (우주 발사체의 포고현상 예측을 위한 공급/추진계의 파이프 압력모드 해석 기법 제안)

  • Lee, SangGu;Lee, SiHun;Shin, SangJoon
    • Proceedings of the Korean Society of Propulsion Engineers Conference
    • /
    • 2017.05a
    • /
    • pp.714-717
    • /
    • 2017
  • Among the factors considered in the design stage of a space launch vehicle using liquid propellant, research has been focused out on the pogo phenomenon, longitudinal dynamic instability. The pogo phenomenon refers to the instability that the longitudinal vibration of the launch vehicle structure causes a change in the pressure and flow rate of the fluids in propulsion system, and this change re-excites the fuselage structure. This mechanism constitutes a closed system to gradually increase the vibration of the launch vehicle. This paper specifically focuses on the dynamic analysis of pressure and flow changes in the propulsion system. Based on the example study of the space shuttle, the acoustic modal analysis of the propulsion system is performed to predict the modes of the supply line causing instability of the fuselage.

  • PDF