• Title/Summary/Keyword: 날개회전주파수

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A Study on Vibration Measurement Using LabVIEW and Acceleration Sensor (LabVIEW와 가속도 센서를 이용한 진동신호 측정에 관한 연구)

  • Park, Jiye;Moon, Chae-Joo;Kim, Tae-Gon;Jeong, Moon-Seon
    • Proceedings of the KIPE Conference
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    • 2012.11a
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    • pp.129-130
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    • 2012
  • 본 논문에서는 3축 가속도 센서의 부착 방법과 위치에 따른 진동 신호의 주파수 특성을 분석하였다. 날개 하나가 깨진 환풍기를 철제 기둥에 나사로 고정하고 회전수를 50rpm, 1710rpm, 2400rpm으로 각기 달리하여 진동을 발생 시켜 가속도 센서의 부착 방법과 위치에 따른 진동 신호를 측정하고 비교하였다. 3축 가속도 센서를 측정하기 위한 측정 소프트웨어를 설계 제작하였으며, 센서의 진동을 비교한 결과 실험에 사용된 회전수에서는 각각의 부착 방법보다는 부착 위치에 따른 진동의 차이가 있는 것으로 나타났다.

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Design Improvements for Preventing Crack of Equipment Mounting Structure in Rotary Wing Aircraft (회전익 항공기의 장비 장착 지지 구조물의 균열 방지를 위한 설계 개선)

  • Bang, Daehan;Lee, Sook;Lee, Sanghoon;Choi, Sangmin
    • Journal of Aerospace System Engineering
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    • v.14 no.1
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    • pp.28-35
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    • 2020
  • This paper presents the design improvements made for the crack which is in the mounting structure of the mechanical structure of rotary wing aircraft. The doubler added to the mounting structure of rotary wing aircraft was designed and manufactured based on the load at the development stage, and a crack was found in the surface of doubler at a certain point during the operation of the aircraft. To identify the cause of the crack, the initial deformation of the structure, which may occur as a result of fastening condition, was considered and the dynamic analysis of the natural frequency of the structure comparing to the blade passing frequency of the aircraft were additionally reviewed. As a result of this study, a shim was added to remove the physical gap of the fastening area, and a doubler with thickened reinforcement was installed. The increase of structural strength is shown by reviewing the results of dynamic analysis for the structural verification of the improved design, and the fatigue evaluation complied to the requirement of the aircraft lifetime.

High Frequency Signal Analysis of LOx Pump for Liquid Rocket Engine under Cavitating Condition (캐비테이션 환경에서의 액체로켓엔진용 산화제펌프의 고주파 신호 분석)

  • Kim, Dae-Jin;Kang, Byung Yun;Choi, Chang-Ho
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2017.05a
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    • pp.1093-1098
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    • 2017
  • High frequency signals are analyzed which are measured at the inlet / outlet pipeline and pump casing during cavitation tests of the LOx pump for the liquid rocket engine. RMS values of data are shown according to the cavitation number. RMS values of the synchronous frequency, its harmonic frequencies and frequencies of cavitation instabilities are also calculated. The pressure pulsations of the inlet and outlet pipeline are affected by cavitation instabilities. 3x component is predominant in the outlet pulsation sensor since 3x component generated at the inducer is amplified at the impeller. The cavitation instability is also found at the accelerometer signal of the casing.

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Optimization of the multi-chamber perforated muffler for the air processing unit of the fuel cell electric vehicle (연료전지 자동차용 흡기 소음기의 설계 변수 최적화에 관한 연구)

  • Kim, Eui-Youl;Kim, Min-Soo;Lee, Sang-Kwon;Seo, Sang-Hoon
    • Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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    • 2009.04a
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    • pp.342-350
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    • 2009
  • Fuel cells convert a fuel together with oxygen in a highly efficient electrochemical reaction to electricity and water. Since the electrochemical reaction in the fuel cell stack dose not generate any noise, Fuel cell systems are expected to operated much quieter than combustion engines. However, the tonal noise and the broad band noise caused by a centrifugal compressor and an electric motor cause which is required to feed the ambient air to the cathode of the fuel cell stack with high pressure. In this study, the multi-camber perforated muffler is used to reduce noise. We propose optimized muffler model using an axiomatic design method that optimizes the parameters of perforated muffler while keeping the volume of muffler minimized.

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Dynamic Aeroelastic Characteristics of an All-Movable Canard with Oscillating Flap Used in UAV (플랩이 있는 무인기 전운동 카나드의 동적공탄성 특성)

  • Kim, Dong-Hyun;Koo, Kyo-Nam;Lee, In;Kim, Sung-Jun;Kim, Sung-Chan;Lee, Jung-Jin;Choi, Ik-Hyun
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.32 no.6
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    • pp.56-63
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    • 2004
  • In this study, dynamic aeroelastic analyses of the canard with oscillating flap are conducted considering the effect of aerodynamic compressibility. The canard model considered herein is an all-movable type with a pitching axis on a canard-rotor-wing aircraft which was considered as one of the major UAV candidates under developing in Korea. The equivalent structural model is constructed based on the initial design data by the Korea smart UAV development center. Both the frequency and the time-domain aeroelastic analyses have been applied to practically conduct parametric studies on the effects of equivalent torsional stiffness. In the case of all-movable control surface with oscillating flap, the equivalent rotational stiffness of the pitch axes are important design parameters. The parametric results for the aeroelastic instability are practically presented.