• 제목/요약/키워드: Aircraft Vibration

검색결과 348건 처리시간 0.032초

복합재 쿼드콥터의 진동 특성 분석과 공진 회피에 대한 연구 (Research of Vibration Analysis and Resonance Avoidance Design of Composite Quadcopter)

  • 김상률;김위대
    • Composites Research
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    • 제33권3호
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    • pp.133-139
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    • 2020
  • 본 연구에서는 복합재료가 적용된 쿼드콥터의 진동 특성을 분석하고, 공진에 대해 회피 설계 및 해석을 수행하였다. 로터-암의 파이프가 복합재료로 구성된 상용 쿼드콥터의 플랫폼을 모사하고 상용 해석 프로그램을 이용하여 진동 특성 분석을 하였다. 실제 적층 배열을 해석에 적용하고, 참고 문헌과의 비교를 통해 신뢰성을 판단하였다. 그리고 모터의 가동범위 내에 특정 모드의 고유 진동수가 포함되는 것을 확인하였다. 기존 모델에서 적층 배열, 로터-암의 길이, 두께의 총 3가지의 변수를 선정해 공진 회피 설계를 수행하였다. 공진 회피 설계의 3가지 변수에서 각 해석의 결과를 비교한 후, 공진 회피 설계의 효율성 측면에서 방향을 제시하였다.

공항 인근주민들의 항공기소음에 대한 피해의식 구조에 관한 연구 - 대구공항을 사례지역으로 - (A Study on Subjective Nise Evaluation of Rdesidential Area on Aircraft Noise near Airport - Case Study on Taegu Airport -)

  • 김재석
    • 소음진동
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    • 제10권1호
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    • pp.41-48
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    • 2000
  • Evaluation model for damage consciousness was established through the survey of 2,210 residents' consciousness on aircraft noise near Taegu Airport. There were none who replied that the level of the aircraft noise was as los as it was quiet. 77(3.5%) people replied the noise was normal, and 2,133(95.5%) people said it was noisy. As to the period of time when the aircraft noise occurred, 51%, 97%, 86%, 0.6% of the residents pointed out the morning time, the day time, the evening time, and the night time, respectively. Because of aircraft noise, 73%, 88%, 70%, 77%, 78%, and 33% of the residents felt it disturbing indoor conversation, telephoning, watching TV or listening to the ratio, reading or meditating, working, sleeping, and studying, respectively. It was examined that the bad effects of aircraft noise on the health were severe : 43% of the resident said they experienced embarrassment. 52% astonishment, 66% absence of mind, 61% heart-beating. 77% headaches, 78% earache, and 93% displeasure. For the survey of the residents' damage consciousness about aircraft noise, the level of aircraft noise was set as an objective variable, and gender, age, occupation. Education, the type of house, the structure of windows, the consciousness of settlement in the district, and the period of residence were set as explanatory variables. And the quantification theory I was applied to the analysis. The most influencing factor of the damage consciousness on aircraft noise was the education, the second occupation, the third age, the forth the consciousness of settlement, the fifth the period of residence, the sixth gender, the seventh the type of house, and the least influencing factor among them was the structure of windows. These findings will be a useful guideline when the government seeks to set up policies which will help solve the resident's noise problems near Taegu Airport.

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항공기 탑재를 위한 FBG 센서 장비의 설계조건 도출 (Design Scheme of FBG Sensor System for Aircraft Application)

  • 박상욱;윤혁진;박상오;송지용;김천곤
    • 한국복합재료학회:학술대회논문집
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    • 한국복합재료학회 2005년도 추계학술발표대회 논문집
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    • pp.215-218
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    • 2005
  • In this research, design scheme of fiber Bragg grating(FBG) sensor system for aircraft application is suggested from the results and the know-how from the fon11er researches on structural health monitoring techniques using fiber optic sensors. Design factors to be taken into consideration were derived for both sensor parts including connection and system parts. For the stability of FBG sensor system, design requirements of temperature, vibration, humidity, electromagnetic interference were presented from U. S. military standards. The direction of software programming which increases stability and perfon11ance of the aircraft with the FBG sensor system was also examined.

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반디호 수출형 시제기에 대한 플러터 매커니즘 분석 (Flutter Mechanism Analysis for Firefly Export Model)

  • 백승길;이상욱
    • 항공우주기술
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    • 제6권1호
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    • pp.35-44
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    • 2007
  • 본 연구에서는 선미익을 채용한 경항공기인 반디호의 수출형 시제기에 대한 플러터 해석을 수행하였다. 내부 하중 생성용 유한요소모델을 기초로 강성 모델을 작성하였고, 중량 통제를 위한 중량 DB에 근거하여 중량 모델을 작성하였다. 공력모델은 DLM을 이용하였다. 작성된 모델을 이용하여 1차 플러터 해석을 수행하였다. 이를 토대로 주요 진동 모드를 구분해 내고, 지상진동시험을 수행하여 진동 특성을 획득하였다. 획득된 고유진동수를 근거로 유한요소모델의 수정이 이루어졌고 2차 해석이 수행되었다. 해석 결과 주요 플러터 근의 특성을 정리하였다. 가장 중요한 플러터 근은 롤 운동을 갖는 강체 모드와 반대칭 주익 피칭 모드의 연계 모드로 판명되었다.

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THI를 이용한 항공기소음이 주민 건강상태에 미치는 영향 (Questionnaire study conducted around Gimpo International Airport by using THI)

  • 손진희;이건;장서일
    • 한국소음진동공학회:학술대회논문집
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    • 한국소음진동공학회 2007년도 추계학술대회논문집
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    • pp.436-441
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    • 2007
  • This study was carried out to evaluate health effects of aircraft noise using THI(Todai Health Index). The questionnaire survey was conducted around the Gimpo International Airport in Seoul, Korea from 8 August to 9 September. Study subjects, 614 residents, were divided into three groups following to the aircraft noise level: under 75WECPNL(area(1)), $75{\sim}80$WECPNL(area(2)) and $80{\sim}85$WECPNL(area (3)). Twelve scale scores are converted to dichotomous variables based on scale scores of 90 percentile value or 10 percentile value in the control group. Logistic regression analysis taking twelve scores converted as the dependent variables and WECPNL(area), age, gender as the independent variables is conducted. Significant dose-response relationships are found in the scale of MOUT, DEPR, NERV, LIFE, where p denotes significance probability of trend test. Factor analysis was carried out and 2 factors are extracted which may be called "somatic factor" and "mental factor". The dose-response relationship with these factors and noise exposure is not clear. But strangely the odds ratio of mental factor in area 2 is the highest and the annoyance of this area is also higher than other areas.

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고고도 장기체공 태양광 무인기 EAV-3 기체구조 개발 (Airframe Structure Development of Solar-powered HALE UAV EAV-3)

  • 신정우;박상욱;이상욱;김태욱
    • 한국항공운항학회지
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    • 제25권3호
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    • pp.35-43
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    • 2017
  • Research for solar-powered high altitude long endurance(HALE) UAV was conducted by Korea Aerospace Research Institute(KARI), and the EAV-3 with 19.5m wing span was developed. For HALE flight, aircraft should be lightly designed. Especially, airframe structure that accounts for a large portion of the total weight of aircraft should be lightweight. In this paper, development process of airframe structure for solar-powered HALE UAV, EAV-3, is described briefly. Domestic developed T-800 grade CFRP(Carbon Fiber Reinforced Plastic) composite material with high modulus and strength was used to design main load carrying structures. Flightloads analysis that takes into account large structural deformation was carried out. Stress and flutter analyses for airframe structure sizing were conducted. Static strength test for main wing and aircraft ground vibration test were conducted successfully and structural integrity was secured.

면내하중을 받는 복합적층판에 대한 충격하중 및 음향 해석 (Impact Force and Acoustic Analysis on Composite Plates with In-plane Loading)

  • 김성준;황인희;홍창호
    • 한국소음진동공학회논문집
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    • 제22권2호
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    • pp.179-186
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    • 2012
  • The potential hazards resulting from a low-velocity impact(bird-strike, tool drop, runway debris, etc.) on aircraft structures, such as engine nacelle or leading edges has been a long-term concern to the aircraft industry. Certification authorities require that exposed aircraft components must be tested to prove their capability to withstand low-velocity impact without suffering critical damage. In most of the past research studies unloaded specimens have been used for impact tests, however, in reality it is much more likely that a composite structure is exposed to a certain stress state when it is being impacted, which can have a significant effect on the impact performance. And the radiated impact sound induced by impact is analyzed for the damage detection evaluation. In this study, an investigation was undertaken to evaluate the effect in-plane loading on the impact force and sound of composite laminates numerically.

비틀림 비선형성을 갖는 2차원 익형의 모델링 및 Bifurcation 해석 (Modeling and Bifurcation Analysis of the 2D Airfoil with Torsional Nonlinearity)

  • 임주섭;이상욱;김성준
    • 한국소음진동공학회논문집
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    • 제24권1호
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    • pp.14-20
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    • 2014
  • Recent developments for high altitude, long endurance conventional UAVs(HALE UAVs) have revealed new issues regarding aircraft structure design and analysis. First of all, due to intensive mission requirements, the structures of HALE UAVs have lightweight and very flexible main wing with high aspect ratio, and slender fuselage. For this kind of structures, aeroelastic characteristics are different from conventional aircrafts. Hence, currently developed analysis methods are not suitable to fully understand strucutral dynamics of the very flexible aircraft, and to guarantee structural reliability. Therefore, various structural studies considering nonlinear behaviors which are generally ignored for the conventional aircraft strucutral analyis have been attracting researchers interests. Nonlinear flutter of the very flexible wing is one of the subject to be studied in combination with strong coupling between aeroelastic characteristics and flight dynamics. Herein, as preliminary study, modeling and nonlinear system analysis of the 2D airfoild with torsional nonlinearity have been discussed.

비틀림 비선형성을 갖는 2차원 익형의 모델링 및 Bifurcation 해석 (Modeling and Bifurcation Analysis of the 2D Airfoil with Torsional Nonlinearity)

  • 임주섭;이상욱;김성준
    • 한국소음진동공학회:학술대회논문집
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    • 한국소음진동공학회 2013년도 추계학술대회 논문집
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    • pp.226-231
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    • 2013
  • Recent developments for high altitude, long endurance conventional UAVs (HALE UAVs) have revealed new issues regarding aircraft structure design and analysis. First of all, due to intensive mission requirements, the structures of HALE UAVs have lightweight and very flexible main wing with high aspect ratio, and slender fuselage. For this kind of structures, aeroelastic characteristics are different from conventional aircrafts. Hence, currently developed analysis methods are not suitable to fully understand strucutral dynamics of the very flexible aircraft, and to guarantee structural reliability. Therefore, various structural studies considering nonlinear behaviors which are generally ignored for the conventional aircraft strucutral analyis have been attracting researchers interests. Nonlinear flutter of the very flexible wing is one of the subject to be studied in combination with strong coupling between aeroelastic characteristics and flight dynamics. Herein, as preliminary study, modeling and nonlinear system analysis of the 2D airfoild with torsional nonlinearity have been discussed.

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군용 항공기 소음평가 방법에 관한 연구 (A Study on the Evaluation Method of a Military Aircraft Noise)

  • 송화영;홍병국;양수영;제현수;이주원;이동훈
    • 한국소음진동공학회:학술대회논문집
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    • 한국소음진동공학회 2004년도 추계학술대회논문집
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    • pp.768-771
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    • 2004
  • 항공기 소음평가 방법에 있어 전혀 다른 소음특성을 갖는 군용 항공기 소음과 민간 항공기 소음을 환경부에서 고시한 소음 진동공정 시험방법에 의거하여 소음을 측정하고 평가하는데는 많은 문제점이 뒤따른다. 따라서 본 연구에서는 민간 항공기와 군용 항공기 소음의 측정 및 평가방법에 대한 문제점들을 고찰하였다. 연구결과로 부터, 민간 항공기나 군용 항공기의 정확한 소음측정을 위해서는 동특성을 빠름(Fast)으로 설정하여 측정하는 것이 바람직한 것으로 확인되었다. 또한 등가 소음도를 측정하여 항공기 소음을 평가하는 방식은 민간 항공기 소음평가시에는 적절하지만, 이를 군용 항공기 소음에 적용하여 평가할 때에는 상당한 오차를 포함하는 것으로 조사되었다. 그리고 군용 항공기 이 착륙지점에서의 소음 지속시간이 대부분 30초를 초과하는 것으로 조사되었기 때문에, 군용 항공기 소음평가시에는 지속시간에 대한 보정이 반드시 반영되어야 할 것으로 사료된다.

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