• Title/Summary/Keyword: Thruster Plume

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Numerical Analysis on Plasma Particles inside Electro-magnetic Field Using Particle-in-cell Method (Particle-in-cell 기법을 이용한 전자기장내 플라즈마 입자의 거동 해석)

  • Han, Doo-Hee;Joe, Min-Kyung;Shin, Junsu;Sung, Hong-Gye;Kim, Su-Kyum
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.45 no.11
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    • pp.932-938
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    • 2017
  • Particle-in-cell method which blends Eulerian grids and Lagrangian particle is utilized to solve simplified hall-effect thruster. Since this study individually tracks not only neutrons and ions but also electrons, message passing interface(mpi) scheme is adopted for parallel computer cluster. Helical movement of an electron cloud in constant magnetic field is validated comparing with an exact solution. A plasma in radial magnetic field and axial electric field in a reaction cylinder is established. Electrons do double helix movement and are well anchored in a cylinder. Ionization of neutrons by impact with high-speed electrons generates ion particles. They are accelerated by axial electric field, which forms a plume of a plasma-effect thruster.

Performance Analysis of the Supersonic Nozzle Employed in a Small Liquid-rocket Engine for Ground Firing Test (소형 액체로켓엔진 지상연소시험용 초음속 노즐의 성능해석)

  • Kam, Ho-Dong;Kim, Jeong-Soo;Bae, Dae-Seok;Lee, Jae-Won
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2011.11a
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    • pp.321-324
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    • 2011
  • A computational analysis of nozzle flow characteristics and plume structure using Reynolds-averaged Navier-Stokes equations with $k-{\omega}$ SST turbulence model was conducted to examine performance of the supersonic nozzle employed in a small liquid-rocket engine for ground firing test. Computed results and experimental outcome of 2-D converging-diverging nozzle flow were compared for verifying the computational capability as well as the turbulence model validity. Numerical computations of 2-D axisymmetric nozzle flow was carried out with the selected model. As a result, flow separation with backflow appeared around the nozzle exit. This investigation was reported as a background data for the optimal nozzle design of small liquid-propellant rocket engine for ground test.

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Development of Propulsion Subsystem for KOMPSAST (다목적 실용위성의 추진시스템 개발)

  • 최진철;윤효철
    • Journal of the Korean Society of Propulsion Engineers
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    • v.2 no.3
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    • pp.80-89
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    • 1998
  • Propulsion subsystem transfers KOMPSAT into mission orbit and controls its attitude. Design factor consists of structure safety, electrical circuit design, consumable power estimation of thermal hardwares, damping device design of fuel transient pressure, and system configuration design by considering plume effect from thruster firing. System level analysis should be performed for verification of system design under launch vehicle and orbital environment. Electrical functional test of thermal control hardware, proof pressure test, cleanliness verification test, and internal/external leakage test of fuel feeding system should be carried out for performance estimation of propulsion system. Design and assembly process of propulsion subsystem was depicted and reliability of system was verified by test analysis in this paper.

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