• Title/Summary/Keyword: 이원추진제 추력기

Search Result 22, Processing Time 0.028 seconds

인공위성의 추진체계 현황 및 전망

  • 이상희;이성태;이용수
    • Proceedings of the Korean Society of Propulsion Engineers Conference
    • /
    • 1995.11a
    • /
    • pp.59-66
    • /
    • 1995
  • 인공위성의 궤도진입, 궤도수정 및 자세제어를 담당하는 추진체계는 위성의 용도와 궤도위치, 자세/궤도제어 방식 등을 고려하여 설계하여야 한다. 현재까지도 널리 사용되고 있는 인공위성 추진체계는 AKM(Apogee Kick Motor)과 단일 추진제 추력기로 구성된 "통상 추진체계"이나 최근에는 AKE(Apogee Kick Engine)과 이원 추진제추력기로 구성된 "통합 추진체계" 그리고 이와 유사한 "완전통합 추진체계", "이중 추진체계" 등이 기술적 선택방안으로 제안되어 일부 적용되고 있는 실정이며 이러한 추진체계의 효과적 실용화를 위해서 단일 추진제(하이드라진) 추력기의 성능향상 및 이원 추진제 엔진과 이원 추진제 추력기의 기술개선 연구가 이루어지고 있다.원 추진제 엔진과 이원 추진제 추력기의 기술개선 연구가 이루어지고 있다.

  • PDF

A study of thrust modeling of bi-propellant rocket engine (이원 추진제 로켓 엔진의 추력 모델링 연구)

  • Jeong,Hae-Seung;Kim,Yu;Ham,Mi-Suk;Park,Eung-Sik
    • Journal of the Korean Society for Aeronautical & Space Sciences
    • /
    • v.31 no.8
    • /
    • pp.85-90
    • /
    • 2003
  • To control spacecraft including satellite, we should understand precisely the performance of propulsion system and the program logic with appropriate format for satellite operations. In this study, the thruster performance functions was generated by using the best curve fitting for performance data from bi-propellant thrusters. Detailed thruster performance data are, in general, company proprietary information, therefore real firing tests were performed to understand the basic characteristics of the performance curve. Experimental rocket motor utilize liquid oxygen and kerosine as propellant and designed average thrust was 100 pound.

Study for Design and Performance Characteristics of Small Bipropellant Thruster using $H_2O_2$/Kerosene (과산화수소/케로신 소형 이원추진제 추력기의 설계 및 성능특성에 관한 연구)

  • Kim, Jung-Hoon;Lee, Jae-Won;Jeon, Young-Jin;Chae, Byoung-Chan;Jeon, Jun-Su;Kim, Yoo;Kim, Sun-Jin
    • Proceedings of the Korean Society of Propulsion Engineers Conference
    • /
    • 2009.05a
    • /
    • pp.41-45
    • /
    • 2009
  • The small-sized bi-propellant thruster using a high concentrated hydrogen peroxide and kerosene as the oxidizer and fuel was designed and fabricated in this study. The water cold-flow test was performed to verify the performance characteristics of the injector. The mixing head assembly used in this model thruster was designed as a structure to combine igniter, injectors and film cooling, which are capable of regulating each mass flowrate. This maximize the experimental verification and efficiency of the design optimization. Finally, the mass flowrate and spray pattern of injector were evaluated by the hydraulic test. Therefore, the design validity of the mixing head was verified.

  • PDF

Exhaust Plume Behavior Study of MMH-NTO Bipropellant Thruster (MMH-NTO 이원추진제 추력기의 배기가스 거동 해석 연구)

  • Kim, Hyeonah;Lee, Kyun Ho
    • Journal of the Korean Society for Aeronautical & Space Sciences
    • /
    • v.45 no.4
    • /
    • pp.300-309
    • /
    • 2017
  • A spacecraft obtains a reaction momentum required for an orbit correction and an attitude control by exhausting a combustion gas through a small thruster in space. If the exhaust plume collides with spacecraft surfaces, it is very important to predict the exhaust plume behavior of the thruster when designing a satellite, because a generated disturbance force/torque, a heat load and a surface contamination can yield a life shortening and a reduction of the spacecraft function. The purpose of the present study is to ensure the core technology required for the spacecraft design by analyzing numerically the exhaust gas behavior of the 10 N class bipropellant thruster for an attitude control of the spacecraft. To do this, calculation results of chemical equilibrium reaction between a MMH for fuel and a NTO for oxidizer, and continuum region of the nozzle inside are implemented as inlet conditions of the DSMC method for the exhaust plume analysis. From these results, it is possible to predict a nonequilibrium expansion such as a species separation and a backflow in the vicinity of the bipropellant thruster nozzle.

Preliminary Research of Regenerative Cooling Channel Design for Small Scale Bipropellant Thruster (소형 이원추진제 추력기를 위한 재생냉각 유로형상 설계에 대한 선행연구)

  • Jang, Dong-Wook;Jo, Sung-Kwon;Cho, Hwang-Rae;Bang, Jeong-Seok;Kwon, Se-Jin
    • Journal of the Korean Society of Propulsion Engineers
    • /
    • v.16 no.2
    • /
    • pp.1-9
    • /
    • 2012
  • Applicability of regenerative cooling in 2,500 N-class bipropellant thruster using hydrogen peroxide and kerosene was considered for improvement of performance and application in various missions. Calculation was performed by one dimensional approach using hydrogen peroxide as a coolant. The heat flux of thruster at nozzle throat was estimated at 18 - 20 MW/$m^2$. Designed cooling channel width and height were 2.5 mm and 0.5 mm, respectively. Based on designed cooling channel configuration, flat plate model was manufactured and tested for estimation of pressure drop in cooling channel, and CFD analysis was compared with the test result. The maximum error between CFD analysis and experimental result was approximately 13% and average error was approximately 5%.

Performance Evaluation of Hydrogen Peroxide with Storage Conditions (온도 조건에 따른 과산화수소의 저장성평가)

  • Chung, Seung-Mi;An, Sung-Yong;Kwon, Se-Jin
    • Proceedings of the Korean Society of Propulsion Engineers Conference
    • /
    • 2008.11a
    • /
    • pp.105-108
    • /
    • 2008
  • Nowadays, as there is so much interest in environment, hydrogen peroxide attracts attention as an eco-propellant. Hydrogen peroxide is widely used for mono-propellant of thruster, and oxidizer of bi-propellant rocket. Especially, it is used as mono-propellant of the thruster for attitude control of satellite and military weapons. So, the need of long time storage of hydrogen peroxide appears and storage test is required. In this paper, necessity of storage test of hydrogen peroxide and some conditions and methods are introduced. In addition, the results of storage tests under some condition are compared and analyzed.

  • PDF

이원 추력기의 성능 모델링 연구

  • Ham, Mi-Suk;Kim, Yoo;Park, Eung-Sik;Park, Bong-Gyu
    • Proceedings of the Korean Society of Propulsion Engineers Conference
    • /
    • 2002.04a
    • /
    • pp.82-83
    • /
    • 2002
  • 궤도상에 올려진 위성들은 인형의 궤도 운행을 하게 된다. 그러나 지구가 완전한 구형이 아니고 태양과 달의 인력이 작용하여 위성에 섭동이 발생하게 된다. 그리고 무중력 상태의 우주이므로 태양풍이나 미세 운석 그리고 위성체 내부의 가스 누출이나 내부의 토크 변화에 의해 위성 자세에 조금의 변동을 야기한다. 통신 위성의 경우 지상의 한 지점을 계속 향하고 있어야 하므로 정기적인 자세제어가 필요하다. 위성의 섭동에 의해 EWSK(East-West station keeping)나 NSSK(North-South station keeping)를 하기 위해 추력 모델은 단일 $\Delta$$\upsilon$기동이나 회전 세차 운동(spin precession maneuver)을 지원해야 한다. 위성은 주어진 임무를 수행하는데 필요한 $\Delta$$\upsilon$기동을 위해 적절한 성능의 추력기와 임무기간 동안 사용할 적절한 양의 추진제를 탑재하고 있다. 지상에서 필요한 임무를 수행하기 위해 위성에 지령을 하였을 때, 추력기가 정상작동을 하였는지 그리고 잔류 추진제가 어느 정도 인지를 정확히 알 수 있어야 한다.

  • PDF

Study on 1,200 N-class bipropellant rocket engine using decomposed $H_2O_2$ and kerosene (분해된 과산화수소와 케로신을 이용한 1,200 N 급 이원추진제 로켓 엔진의 연구)

  • Jo, Sung-Kwon;An, Sung-Yong;Kim, Jong-Hak;Yoon, Ho-Sung;Kwon, Se-Jin
    • Proceedings of the Korean Society of Propulsion Engineers Conference
    • /
    • 2010.05a
    • /
    • pp.156-164
    • /
    • 2010
  • As part of preliminary study for development of 1,200 N-class bipropellant rocket engine with the concentrated hydrogen peroxide, bipropellant engine elements were designed and experimentally tested. The catalysts of $MnO_2$ and $MnO_2$ added Pb as an addictive were compared to achieve high decomposition performance and the catalytic reactor with $MnO_2$ added Pb was designed and its decomposition efficiency of 97.2% was achieved. The autoignition tests of kerosene by decomposed hydrogen peroxide were carried out under various equivalence ratios to ignite without additional ignition sources. Autoignition were achieved in all experimental conditions and $C^*$ efficiencies at each condition were at or above 90%. From the measured thrust results, the highest value was 830 N which is in corresponds with 1,035 N at vacuum level using 94.1% theoretical $I_{sp}$.

  • PDF

Study on 1,200 N-class bipropellant rocket engine using decomposed $H_2O_2$ and kerosene (분해된 과산화수소와 케로신을 이용한 1,200 N 급 이원추진제 로켓 엔진의 연구)

  • Jo, Sung-Kwon;An, Sung-Yong;Kim, Jong-Hak;Yoon, Ho-Sung;Kwon, Se-Jin
    • Journal of the Korean Society of Propulsion Engineers
    • /
    • v.14 no.6
    • /
    • pp.69-78
    • /
    • 2010
  • As part of preliminary study for development of 1,200 N-class bipropellant rocket engine with the concentrated hydrogen peroxide, bipropellant engine elements were designed and experimentally tested. The catalysts of $MnO_2$ and $MnO_2$ added Pb as an additive were compared to achieve high decomposition performance and the catalytic reactor with $MnO_2$ added Pb was designed and its decomposition efficiency of 97.2% was achieved. The autoignition tests of kerosene by decomposed hydrogen peroxide were carried out under various equivalence ratios to ignite without additional ignition sources. Autoignition were achieved in all experimental conditions and $C^*$ efficiencies at each condition were at or above 90%. From the measured thrust results, the highest value was 830 N which is in corresponds with 1,035 N at vacuum level assuming $C^*$ efficiency equals $I_{sp}$ efficiency.

Requirement Analysis of Propulsion System for Active Anti-Ship Missile Decoy (능동형 대함 유도탄 기만기의 추진 시스템 요구 조건 분석)

  • Moon, Yongjun;Kwon, Sejin
    • Journal of the Korean Society of Propulsion Engineers
    • /
    • v.17 no.4
    • /
    • pp.1-9
    • /
    • 2013
  • An active anti-ship missile decoy system was designed conceptually to analyze propulsion system requirements and feasibility to use a liquid bi-propellant rocket engine. Overall mass, size, and shape were assumed referring to specifications of Nulka which was developed by US and Australia in 1990s. The propulsion system was assumed to be a 1,000 N-class $H_2O_2$/kerosene rocket engine with a pressurized feed system. A three-degree-of-freedom optimal trajectory was calculated based on the assumptions, and mass budget was designed from the calculation results. It was found that the requirements for the propulsion system is that it shall be operated more than 100 sec; it shall be re-ignitable; it shall have a throttle capability of a range from 35% to 100% when the maximum thrust at sea level is 1,000 N.