• Title/Summary/Keyword: Side Thrust

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The Prediction of Side Thrust Generated by Grousers Under Track (그라우저에 의해 발생되는 궤도의 측면추진력 예측)

  • 박원엽;이규승;박준걸
    • Journal of Biosystems Engineering
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    • v.25 no.1
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    • pp.1-10
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    • 2000
  • This study was conducted to develop the mathmatical model for predicting the side thrust which is generated by the shearing action on the vertical surfaces of the sides of the track. Experiments were conducted with the three different shear plates with grouser length of 1, 3 and 5 cm for two different soil condition using soil bin system. The measured side thrust were compared with the values predicted by the new model developed in this study and by Bekker's model respectively. The values of side thrust predicted by the new model were more close to the measured values than those of the side thrust predicted by Bekker's model . The total thrust measured were also compared with the values predicted by the conventional model which considers only bottom thrust effect and by the new model which contains not only bottom thurst but side thrust effect. The values of the thrust predicted by conventional modelwere lower than measured values for both of the soil conditions and the three levels of grouser length. The maximum errors of conventional model were increased with the increase of grouser length. but the values of the total thrust predicted by the model developed in this study were well matched to the measured ones for both of the soil conditions and the three levels of grouser lengths.

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Analysis of Gross Thrust and Side Thrust of Air-Breathing Engine (공기 흡입 엔진의 총추력 및 측추력 분석)

  • Kim, Jeongwoo;Jung, Chihoon;Ahn, Dongchan;Lee, Kyujoon
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2017.05a
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    • pp.572-582
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    • 2017
  • It is definitely important to measure thrust during ground test when developing air-breathing engine, and in case of air-breathing engine, gross thrust should be calculated considering not only the measured thrust but also the force induced by the air flow of engine intake. Also, side thrust like yaw and pitch should be measured and analyzed using multi-component thrust measurement system. Engine performance was accurately evaluated by calculating the gross thrust of air breathing engine precisely which is analyzed from below serial procedure: labyrinth seal isolation, 1-axis gross thrust calculation, develop multi-component thrust measurement system, and side thrust analysis.

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The Gross Thrust Estimation Technique of Air-Breathing Engine (공기 흡입 엔진의 총추력 추정 기법)

  • Kim, Jeongwoo;Jung, Chihoon;Ahn, Dongchan;Lee, Kyujoon
    • Journal of the Korean Society of Propulsion Engineers
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    • v.22 no.3
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    • pp.97-108
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    • 2018
  • It is definitely important to measure thrust during ground test when developing air-breathing engine, and in case of air-breathing engine, gross thrust should be calculated considering not only the measured thrust but also the force induced by the air flow of engine intake. Also, side thrust like yaw and pitch should be measured and analyzed using multi-component thrust measurement system. Engine performance was accurately evaluated by calculating the gross thrust of air breathing engine precisely which is analyzed from below serial procedure: labyrinth seal isolation, 1-axis gross thrust calculation, develop multi-component thrust measurement system, and side thrust analysis.

Numerical study on flow characteristics of a variable thrust side jet thruster with a rectangular nozzle (사각 노즐이 적용된 가변 추력용 측추력기의 유동특성에 관한 수치해석)

  • Kim, Li-Na;Sung, Hong-Gye;Jeon, Young-Jin;Cho, Seung-Hwan
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2012.05a
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    • pp.110-116
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    • 2012
  • To analyze flow characteristics and performance of the side jet thruster with 4 shutters and rectangular nozzles, a 3-D simulation has been implemented. Numerical calculations for three rotation anlgles of the shutter, have been conducted. Internal recirculation in a chamber and asymmetric flow structure in a nozzle were observed. In addition, the more shutter rotated, the more asymmetries of flow increased, and this phenomena resulted in thrust bias. The degrees of thrust bias and thrust performance with the rotation angles of the shutter were predicted and comparisons with theoretical thrust were made.

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Numerical Study on the Flow Characteristics of a Side Jet Thruster Having Variable Thrust with a Rectangular Nozzle (사각 노즐이 적용된 가변 추력용 측추력기의 유동특성에 관한 수치해석)

  • Kim, Lina;Sung, Hong-Gye;Jeon, Young-Jin;Cho, Seunghwan
    • Journal of the Korean Society of Propulsion Engineers
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    • v.17 no.2
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    • pp.63-70
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    • 2013
  • To analyze flow characteristics of the side jet thruster with 4 shutters and rectangular nozzles, a 3-D simulation has been implemented. Numerical calculations for two rotation angles of the shutter, have been conducted. Internal recirculation in a chamber and asymmetric flow structure in a nozzle were observed. In addition, the more shutter rotated, the more asymmetries of flow increased, and this phenomena resulted in thrust bias. The degrees of thrust bias and thrust performance with the rotation angles of the shutter were predicted and compared with theoretical thrust.

Numerical Analysis on the flow characteristics of L-type side jet thruster (L-type 측추력 발생장치의 유동특성 해석)

  • Lim, S.;Jeon, Y.J.;Cho, S.H.
    • 한국전산유체공학회:학술대회논문집
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    • 2011.05a
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    • pp.368-372
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    • 2011
  • The aerodynamic characteristics of the L-type side jet thruster are examined by using computational fluid dynamics methods. The critical design points of L-type side jet thruster with bent nozzle by 90degrees are studied in terms of the relation between side jet nozzle geometry and thrust efficiency.

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Development of Side Jet Thruster with Nozzle Closure Separation Device (고기동 추진기관의 노즐개방형 측추력기 개발)

  • Han, Houkseop;Park, Euiyong;Kim, Dongjin;Son, Youngil
    • Journal of the Korean Society of Propulsion Engineers
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    • v.18 no.2
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    • pp.80-85
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    • 2014
  • Side jet thruster using nozzle closure separation device provides a solid rocket with a trajectory shift function. Side jet thruster consists of low combustion temperature propellant, neutral type propellant grain and nozzle closure separation device. If a trajectory shift is required, side jet thrust is generated on the rocket by separating some nozzle closures located in the opposite direction to thrust. After completing trajectory shift, the other nozzle closures located in the thrust direction are separated to cease side jet thrust. The operation process is verified through ground static test. The result in this study can be applied to changing rocket trajectory by controlling side jet thrust through nozzle closure separation.

Analyses of Thrust Bearing in a Scroll Compressor Considering Oldham Ring (올댐링을 고려한 스크롤 압축기 스러스트 베어링의 해석)

  • Park, Sang-Shin;Lee, Seung-Ryoul
    • Tribology and Lubricants
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    • v.23 no.3
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    • pp.109-116
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    • 2007
  • A scroll compressor is on the increase in the use for the cooling and ambition machinery because of the advantages about high efficiency, low vibration and low noise. The design of thrust bearing for scroll compressor has depended on the experience. The lubrication considering the squeeze flow was applied for high side shell and low side shell of scroll thrust bearing. This work was based on governing fluid lubrication equation at the general coordinate. It shows the behavior for an orbiting scroll with direct numerical analysis using FDM. This study obtained the theoretical design value by finding load capacity and tilting angle of an orbiting scroll for thrust bearing in a scroll compressor. Especially this work performed the analysis about the design parameter. The program was written using Visual C++ to enhance user to change the design parameter easily. In particular the result value and the pressure profile were displayed as windows in every step for user to understand without difficulty.

Characteristics Analysis of Double Side Excitation Type Multi-separated LDM (양측 여자형 다분할 LDM의 특성해석)

  • Yoon, Shin-Yong;Baek, Soo-Hyun;Kim, Yong
    • Journal of the Korean Institute of Illuminating and Electrical Installation Engineers
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    • v.16 no.4
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    • pp.64-72
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    • 2002
  • The use of linear DC motor is spreaded according to industrial development. This study was objected to study the analysis of double side excitation LDM with moving magnet type. In this LDM structure, the mover made use of permanent magnet with six pieces so as to large thrust, the stator was bedded for the multi separated type winding to repress the i개n saturation. Also, double side excitation winding is suppressed to thrust ripple with stratification to zigzag type and designed to production for static thrust. Then it is important to ratio of permanent magnet to winding width at multi separate, this paper analyzed to separate to three pieces of 1:1, 1:0.84 and 1:0.5 with width ratio. The analysis method calculated the parameter useful for permeance and magnetic resistance more than FEM of complicated numerical value analysis. Through manufactured experiment system, measurement result of thrust was almost acquired to constant thrust for all displacement.

Numerical Analysis on the Flow Characteristics of Side Jet Thruster (Side Jet 발생기의 유동특성에 관한 해석)

  • Hong S. K.;Sung W. J.
    • Journal of computational fluids engineering
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    • v.6 no.3
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    • pp.27-31
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    • 2001
  • For rapid and abrupt control of a missile in supersonic flight, side jet on a missile body is found to be a useful device as evidenced by recent missile development at several nations. The magnitude of the side jet and the duration of it decide the level of control of such a missile system. In this paper, the aerodynamic characteristics of the side jet device itself are examined in terms of key parameters such as the side jet nozzle geometry, the chamber pressure and temperature. Specifically attention is paid to the effect of the chamber shape between the straight nozzle and the bent nozzle by 90 degrees on the nozzle flow properties. The thrust magnitudes are compared between the two shapes. Whether the way the nozzle is bent at the joint affects the nozzle performance is also investigated. Effects of the length and the divergence angle of the nozzle on the thrust are also quantified among three different side jet nozzles.

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