• Title/Summary/Keyword: 공압 시험

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암반공압파쇄에 의한 지하수위 변화 분석

  • 김혜빈;부성안;김진성;김종태;정교철
    • Proceedings of the Korean Society of Soil and Groundwater Environment Conference
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    • 2004.04a
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    • pp.119-122
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    • 2004
  • 농어촌연구원 내 화강암질편마암지층에 2차에 걸쳐 3공에 대한 공압파쇄 시험 결과 B-1공은 점토성분의 파쇄대 충진으로 수량이 도리어 감소하였다. 공압파쇄 시험 중 파쇄 도달거리를 측정한 결과, P-2 공은 50m 거리에 위치한 B-1공에서의 공압파쇄시험 중에는 약 0.6m의 수위상승이 있었고, 20m 거리에 위치한 B-2공에서의 공압파쇄시험 중에는 약 3.1m의 수위가 상승하였다. 이는 공압파쇄의 유효거리가 암반층에서는 6~15m 정도라고 알려져 있으나 파쇄구간의 발달 정도에 따라 50m 이상 압축공기가 전달됨을 알 수 있다.

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공압벨브의 종합성능 측정자동화 시스템 개발

  • 강보식;김형의;김용채
    • Proceedings of the Korean Society of Precision Engineering Conference
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    • 1991.04a
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    • pp.302-308
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    • 1991
  • 최근 산업현장에서 작업능률의 향상, 인건비의 절감을 목적으로 공장자동화가 급속히 추진됨에 따라 자동화 설비의 핵심기기인 공압벨브의 수요가 급격히 증가하고 있다. 공압밸브는 전기적신호로 솔레노이드를 작동하여 공기의 흐름을 제어하는 것으로 기계와 전기가 결합된 Mechatronics화된 제품이다. 본 연구에서는 공압벨브류의 성능측정 분야 에 있어서 세계 각종규격(ISO, JIS, CETOP) 에 명기된 시험항목들을 자동으로 측정할 수 있는 종합성능 시험시스템을 개발하였고, 시스템의 작동은 한명의 작업자가 측정항목의 모든 시험을 제어할 수 있도록 완전자동화 하였다.

Pneumatic Test of Components and Systems of Launch Vehicle (발사체 구성품 및 시스템의 공압시험)

  • Lim, Ha-Young;Han, Sang-Yeop
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2011.11a
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    • pp.904-907
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    • 2011
  • Various types of gases and propellants are used in launch vehicle. In order to fulfill the mission of the launch vehicle, the components and systems used in launch vehicle should ensure flawless operation in these environments. The pneumatic test is the test performed using compressed gas to prove requirements of the components and systems. This paper describes the requirements of the gas quality for pneumatic test, leak test method, and pneumatic test of the launch vehicle.

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A study on steady state performance of variable thrust nozzle by cold-flow test (공압시험을 이용한 추력가변 노즐의 정상상태 성능 연구)

  • Kim, Jung-Keun;Lee, Ji-Hyung;Oh, Jong-Yun;Chang, Hong-Been;Kim, Shin-Hoe
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2007.04a
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    • pp.289-294
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    • 2007
  • Solid Rocket Motor(SRM) has advantages such as - high specific impulse, operational safety and simplicity in design and manufacturing process, but thrust magnitude can't be controlled. For studying of pintle nozzle that can control the thrust magnitude of SRM, cold flow test and numerical analysis about needle type pintle shape were performed and results were presented in this paper. As the results of this study, pintle tip's shape and nozzle contour were important design parameters because thrust performance and variable thrust range of pintle nozzle depend on them. Especially, the thrust of needle typed pintle nozzle adopted in this test was predicted 13% higher than normal nozzle without pintle.

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Pneumatic Test Assessment of Pulse Separation Device for Multi-Pulse Rocket Motor (다중펄스 로켓모타 적용 펄스분리장치의 공압시험평가)

  • Lee, Dong-Won;Lee, Won-Bok;Kang, Seong-Yeop;Lee, Jong-Won;Chang, Hong-Been
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2010.05a
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    • pp.101-104
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    • 2010
  • A bulkhead-type pulse separation device has been developed for the multi-pulse rocket motor. The design parameters of the pulse separation device were the shape of the rupture disc slit, welding conditions, and the implementation of the seal disc. The pneumatic tests of the fabricated pulse separation devices showed that the rupture pressure increased as the quantity of the rupture disc slit and welding strength increased and the seal disc was implemented.

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Thrust performance at the various pintle shapes and positions (핀틀 형상 및 위치에 따른 추력 성능)

  • Kim, Joung-Keun;Lee, Ji-Hyung;Jang, Hong-Been
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2008.11a
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    • pp.89-93
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    • 2008
  • The effect of pintle shapes and position to the thrust performance of Solid Rocket Motor was studied by experimental-aided Computational Fluid Dynamic(CFD). Among the turbulent models for RANS in Fluent, Spalart-Allmaras model was better agreement with the nozzle wall pressure distribution attained by cold-flow test than other models. When nozzle throat area was decreased, magnitude of thrust was increased. The bigger pintle size was, the more thrust of pintle tip pressure was obtained. Meanwhile the more thrust of nozzle and chamber pressure decreased. Hence, total thrust of big pintle was less than a small pintle under same throat area condition.

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A Study on the Nondestructive Test Method for Adhesively Bonded Joint in Motor Case Assembly (연소관 조립체의 접착 체결부에 대한 비파괴 시험 방법 연구)

  • Hwang, Tae-Kyung;Lee, Sang-Ho;Kim, Dong-Ryun;Moon, Soon-Il
    • Journal of the Korean Society for Nondestructive Testing
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    • v.26 no.5
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    • pp.343-352
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    • 2006
  • In the present paper, the nondestructive test method was suggest to establish the bonding status of a motor case assembly composed of a steel motor case, adiabatic rubber layer and an ablative composite tube with strain data, AE(acoustic emission) signals and UT(ultrasonic test) data. And, finite element analysis was conducted to verify quantitatively the bonding status of motor case assembly under inner pressure loading. The bonding status could be judged whether the bonding status is perfect or contact condition by the data correlation study with AE signals and strain data measured from air pressure test. And, to classify the bonding status of motor case and rubber layer among bonding layers, UT method was also applied. From this study, the bonding status could be classified and detected into fourth types for all bonding layers as follows: (1) initial un-bonding, (2) perfect do-bonding during an air pressure test, (3) partially de-bonding during an air pressure test, and (4) perfect bonding.

Effects of Cavitation and Drop Characteristics on Oleo-Pneumatic Type Landing Gear Systems (공동현상을 고려한 유공압 방식 착륙장치의 낙하특성에 관한 연구)

  • Han, Jae-Do;Lee, Young-Sin;Kang, Yeon-Sik;Ahn, Oh-Sung;Kong, Jeong-Pyo
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.37 no.2
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    • pp.193-200
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    • 2009
  • This paper investigated the drop characteristics of oleo pneumatic type landing gear for small aircraft and the effects of cavitations in modeling the landing gear system. The landing gear system employed a simple oleo pneumatic type damper without a metering pin. In general, oleo-pneumatic type landing gears are light-weighted because of it's simplicity, yet they offer excellent impact absorption characteristics. In this study, the landing gear system was modeled using MSC ADAMS, which offers a drop simulation module. After modeling the system, a series of testing was conducted, using a prototype landing gear system, to validate the analysis model and simulation results. The effect of cavitation was considered in the simulation model to obtain a better correlation between the test and simulation results. The results show that adding the cavitation effect in the simulation model significantly improved the simulation model and better captured the dynamic behaviors of the landing system. Using the 'cavitation' model, dynamics characteristics of the landing gear were further evaluated for other landing conditions, such as landing in various angles of slopes.

A Study on Development of Commercial Prototype BLDC Motor Grinder in Shipbuilding to Replace Air Grinder (조선해양 작업장의 공압 그라인더 대체용 BLDC 모터 전동 그라인더 상용 시제품 개발 연구)

  • Ha, Seok-Moon;Ahn, Wooyoung
    • Proceedings of the KIPE Conference
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    • 2014.11a
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    • pp.171-172
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    • 2014
  • 조선해양 생산현장에서는 생산 용도로 다양한 에너지원을 사용하고 있지만 가장 많이 사용하는 에너지원은 전기이며, 전기의 30% 이상을 압축공기 생산에 사용하고 있다. 압축공기를 동력으로 이용하는 경우, 특히 그라인더에서는, 에너지 변환 효율이 전력대비 1/4~1/5 수준으로 매우 낮다. 본 연구에서는 공압 그라인더를 BLDC 모터 전동 그라인더로 대체하기 위한 연구를 수행하였다. 그 결과 7인치 공압 그라인더와 대등한 출력을 내면서 안전성과 내구성 면에서 우수한 상용급 전동 그라인더 시제품을 설계 및 개발하였다. 또한 시제품에 대한 현장 시험을 거쳐 다양한 개선방안과 설계개선안을 통해 향후 상용급 BLDC모터 전동 그라인더 개발을 위한 설계기술을 확보할 수 있었다.

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Analysis of Dynamic Characteristics of Pneumatic Driving Solenoid Valve (공압구동용 솔레노이드밸브의 동특성 해석)

  • Jang, Je-Sun;Kim, Byung-Hun;Han, Sang-Yeop
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2011.11a
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    • pp.731-736
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    • 2011
  • A pneumatic driving solenoid valve operates pneumatic control devices by opening/closing operating flow passage when the command is given by control system for the liquid-propellant feeding system of space launch vehicle. The simulation model of pneumatic driving solenoid valve is designed with AMESim to verify the designs and evaluate the dynamic characteristics and pneumatic behaviors of valve. To validate a valve simulation model, the simulation results of their operating durations of valve by AMESim analysis are compared with the results of experiments. In addition, the results of internal flow simulation with FLUENT are utilized to improve the accuracy of valve-modeling. Using the model, we analyze performance of valve; opening/closing pressure, operating time on various design factors; shape of control valve seat, drainage seat, rate of sealing diameter, volume of control cavity. This study will serve as one of reference guides to enhance the developmental efficiency of ventilation-relief valves with the various operating conditions, which shall be used in Korea Space Launch Vehicle-II.

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