• Title/Summary/Keyword: Propellant

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Propellant utilization system on liquid-fuelled rocket (액체추진 발사체의 추진제 소진시스템)

  • Cho, Kie-Joo;Lim, Seok-Hee;Jung, Young-Suk;Oh, Seung-Hyub
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2006.11a
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    • pp.203-206
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    • 2006
  • We have studied, for maximizing the total impulse of liquid propulsion system, Propellant Utilization System (PUS) to minimize outage of propellant. Propellant outage is mainly influenced by propellant mixture ratio during flight and real quantity of loaded propellant. If one employs cryogenic propellant, the variation of propellant density due to the temperature change has major effect on outage control. Feedback control of propellant level of each tank during flight could deplete both tanks simultaneously. To introduce this system, however, the mixture ratio control system of rocket engine is necessary.

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Analysis of Residual Propellant Gauging System Using Thermal Pumping of Satellite Employing Multi-tank System (다중탱크를 갖는 인공위성의 열펌핑을 이용한 잔여연료량 측정방법 연구)

  • Han Jo Young;Kim Jung Hoon;Park Eung Sik
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2004.10a
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    • pp.141-145
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    • 2004
  • The residual propellant of satellite is the primary factor of satellite life. This propellant used in the satellite is stored as liquid in tanks. But it is very difficult to accurately measure propellant to be used for maintaining of satellite by an irregular influence of environment. In this paper, a new method of gauging propellant residual of satellite employing multi-tank system by measuring mass flow of thermal pumping liquid propellant is presented. In cases of being connected between tanks, propellant in tanks move by temperature difference of tanks. If propellant mass flow is measured at line between tanks, residual propellant in tanks is able to be estimated.

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Performance Evaluation of Components of Micro Solid Propellant Thruster (마이크로 고체 추진제 추력기 요소의 성능 평가)

  • Lee Jongkwang;Lee Dae Hoon;Choi Sunghan;Kwon Sejin
    • Transactions of the Korean Society of Mechanical Engineers B
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    • v.28 no.10
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    • pp.1264-1270
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    • 2004
  • In this paper research on micro solid propellant thruster is reported. Micro solid propellant thruster has four basic components; micro combustion chamber, micro nozzle, solid propellant and micro igniter. In this research igniter, solid propellant and combustion chamber are focused. Micro igniter was fabricated through typical micromachining and the effect of geometry was evaluated. The characteristic of solid propellant was investigated to observe burning characteristic and to obtain burning velocity. Change of thrust force and the amount of energy loss following scale down at micro combustion chamber were estimated by numerical simulation based on empirical data and through the calculation normalized specific impulses were compared to figure out the efficiency of combustion chamber.

The Effect of Stabilizer(DPA, $CaCO_3$) Addition on the Shelf Life of the Single Base Propellant (단기추진제 저장수명에 미치는 안정제(DPA, $CaCO_3$) 첨가의 효과)

  • 윤근식;고석일;유승곤
    • Journal of the Korea Institute of Military Science and Technology
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    • v.6 no.2
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    • pp.9-19
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    • 2003
  • Nitrogen oxide gases which were produced by spontaneous reaction of nitrocellulose(NC) in the single base propellant accelerate the decomposition of propellant, and result in the reduction of shelf life. The amount of nitrogen oxide was reduced by the addition of 0.3wt% $CaCO_3$ to conventional stabilizer(DPA) and down of the solvent leaching temperature from $64^{\circ}C$ to $56^{\circ}C$, which extended the shelf life of the single base propellant as much as twice compare with commercial propellant. The perforation diameter increase of propellant from 0.64mm to 0.77mm could compensate for the drop of burning rate which was caused the addition of $CaCO_3$.

Performance Evaluation of Components of Micro Solid Propellant Thruster (마이크로 고체 추진제 추력기 요소의 성능 평가)

  • Lee, Jong-Kwang;Lee, Dae-Hoon;Kwon, Se-Jin
    • Proceedings of the KSME Conference
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    • 2004.04a
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    • pp.1280-1285
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    • 2004
  • Microsystem technology has been applied to space technology and became one of the enabling technology by which low cost and high efficiency are achievable. Micro propulsion system is a key technology in the miniature satellite because micro satellite requires very small and precise thrust force for maneuvering and attitude control. In this paper research on micro solid propellant thruster is reported. Micro solid propellant thruster has four basic components; micro combustion chamber, micro nozzle, solid propellant and micro igniter. In this research igniter, solid propellant and combustion chamber are focused. Micro igniter was fabricated through typical micromachining and evaluated. The characteristic of solid propellant was investigated to observe burning characteristic and to obtain burning velocity. Change of thrust force and the amount of energy loss following scale down at micro combustion chamber were estimated by numerical simulation based on empirical data and through the calculation normalized specific impulses were compared to figure out the efficiency of combustion chamber.

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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
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    • 2004.10a
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    • pp.79-82
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    • 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.

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The Study for the Single-based Propellant Shelf Life extension (단기추진제 저장수명 연장을 위한 방안 연구)

  • Bong, Ha-Gyu;Yoon, Keun-Sig
    • Journal of Applied Reliability
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    • v.5 no.3
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    • pp.357-371
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    • 2005
  • Nitrogen oxide gases which were produced by spontaneous reaction of nitrocellulose (NC) in the single base propellant accelerate the decomposition of propellant, and result in the reduction of shelf life, The amount of nitrogen oxide was reduced by the addition of $0.3wt\%$ CaCO3 to conventional stabilizer(DPA) which extended the shelf life of the single base propellant as much as twice compared with commercial propellant.

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Ultrasonic Inspection Technology of Defect Detection of Propellant/Liner Debond & Propellant Microcrack (초음파를 이용한 추진제/라이너 미접착 및 추진제 미세 크랙의 결함 검출 기법)

  • Na, Sung-Youb
    • Journal of the Korean Society of Propulsion Engineers
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    • v.11 no.1
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    • pp.34-42
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    • 2007
  • Ultrasonic inspection method is more profitable than X-ray radiographic inspection in cost and effect of defect detection such as debond, damage, and it doesn't need special constructions. The method can also be a possible real time inspection with safety. This report explains 1)the experiment and analysis of ultrasonic property of solid propellant, 2)the inspection methods of propellant/liner debond by inside or outside inspection, and 3)the inspection methods of propellant microcrack by damage. From the results, it is possible to detect the defect of propellant/liner debond by inside or outside inspection. Futhermore, it can be possible to detect the propellant microcrack caused by damage using the ultrasonic attenuation.

A Study on the Pressure Increase due to the Foam Left in the Radial Slot of Propellant Grain (추진제 그레인 래디얼 슬롯내의 폼 코어에 의한 압력증가 해석)

  • Kim Jong-Yul;Jung Gyoo-Dong;Yang Jun-Seo
    • Journal of the Korea Institute of Military Science and Technology
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    • v.7 no.4 s.19
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    • pp.125-132
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    • 2004
  • The radial slot configuration in the solid propellant grain is usually fabricated by the polyurethane foam slot former The foam cannot be easily removed from the solid propellant, some can remain in the slot. Analogue solid propellant rocket motors using polyurethane foam to shape the slot are static fired with the foam former still in place in the slot. The pressure increases at the slot part are measured and there are indications of the propellant cracks at the insulations above the slot. The pressure increase is produced at the beginning of the burning sequence as the foam will hinder the combustion gas of the burning propellant from flowing into the central bore. The pressure increase up to about 300psi is predicted for the motor tested and this pressure increase depends on the gap between the propellant and foam surfaces and remaining foam volume. This amount of pressure increase inside of the slot is estimated to cause the propellant crack. To prevent this pressure increase, minimizing the foam remainder in the slot and making sufficient chamfering at the comer of the slot entrance are suggested.

Residual Propellant Gauging Methods for Geostationary Satellites and Recent Technology Status (정지궤도위성의 잔여추진제량 측정방법 및 기술동향)

  • Park, Eungsik;Huh, Hwanil
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.42 no.10
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    • pp.870-877
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    • 2014
  • Geostationary satellites undergo various orbital perturbations and this results in location change. Therefore, all the geostationary satellites use the thruster in order to control the location change. For this purpose, the suitable amount of liquid propellant is mounted and the amount of propellant is reduced as time goes by. This means that the lifetime of the satellite depends on the residual propellant amount. Therefore precise residual propellant gauging is very important for the mitigation of economic losses arised from premature removal of satellite from its orbit, satellites replacement planning, slot management and so on. In this paper, we introduce the propellant gauging methods used in the geostationary satellites and the propellant gauging method studied in the laboratory level.