• Title/Summary/Keyword: 기동성 비행

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Cross-sectional Design and Stiffness Measurements of Composite Rotor Blade for Multipurpose Unmanned Helicopter (다목적 무인헬기 복합재 로터 블레이드의 단면 구조설계 및 강성 측정)

  • Kee, Young-Jung;Kim, Deog-Kwan;Shin, Jin-Wook
    • Journal of Aerospace System Engineering
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    • v.13 no.6
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    • pp.52-59
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    • 2019
  • The rotor blade is a key component that generates the lift, thrust, and control forces required for helicopter flight by the torque transmitted through the hub and the blade pitch angle control, and should be designed to factor vibration characteristics so that there is no risk of resonance with structural safety. In this study, the structural design of the main rotor blade for MPUH(Multi-Purpose Unmanned Helicopter) was conducted and the sectional stiffness measurement of the fabricated blade was performed. The evaluation of the vibration characteristics of the main rotor system was then conducted factoring the measured stiffness distribution. The interior of the rotor blade comprised of the skin, spar, and torsion box, and carbon and glass fiber composites were applied. The Ksec2D program was applied to predict the stiffness of blade, and the results were compared to the measured data. CAMRADII, a comprehensive rotorcraft analysis program, was applied to investigate the natural frequency trends and resonance risks due to the rotor rotation.

An operational analysis and dynamic behavior for a landing gear system using ADAMS (ADAMS를 이용한 항공기 착륙장치 작동 동적거동 해석)

  • Choi, Sup;Kwon, Hyuk-Beom;Chung, Sang-Joon;Jung, Chang-Rae;Sung, Duck-Yong
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.31 no.6
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    • pp.110-117
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    • 2003
  • The operational characteristics of the landing gear retraction/extension depend on the complexity of design variables operational/environmental conditions. In order to meet the requirements of minimum stow area and performance, the integration of the landing gear system requires operational kinematic and dynamic analysis considering an effect of its related system. This study investigates operational dynamic behaviors of the T-50 landing gear system using ADAMS. Taking into account for various operational/environmental conditions, an analysis of dynamic behavior on the landing gear operational characteristics is performed with experience derived from a wide range of proprietary designs. Analytical results are presented for discussing the effects of temperature, aerodynamic and maneuver load on normal/emergency operation of the landing gears and doors. This analysis leads us to the conclusion that the proposed program is shown to be a better quantitative one that apply to a new development and troubleshooting of the landing gear system.

고에너지 중이온 TOF-ERDA를 이용한 박막분석

  • Hong, Wan;Woo, Hyung-Joo;Kim, Young-Seok;Kim, Gi-Dong;Kim, Jun-Gon;Choi, Han-Woo
    • Proceedings of the Korean Vacuum Society Conference
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    • 1999.07a
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    • pp.77-77
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    • 1999
  • 박막시료의 분석에는 RBS, XPS, SIMS, AES 등이 주로 이용되고 있으며, 특히 RBS는 비교체가 필요없고 정량성이 좋다는 장점 때문에 중요하다. 그러나 RBS는 원리적으로 경원소에 대한 감도가 낮아 기판원소보다 무거운 질량을 갖는 원소의 분석에만 이용되는 것이 보통이다. 이러한 단점을 보완하기 위해 본 연구에서는 수년전부터 RBS와 비슷한 원리를 갖고 같은 장비를 이용하여 수행이 가능한 경원소 분석법인 TOF-ERDA(Time of Flight Elastic Recoil detection)을 개발하여 실용화 하였다. 본 연구실에서 보유하고 있는 미국 NEC사의 5SDH 가속기는 최대 가속전압이 1.7MV로 Cl5+ 이온을 사용하는 경우 10 MeV가 최대 가속에너지가 된다. 이런 정도의 에너지 범위에서는 TOF spectrometer의 시간분해능이 아주 높을 필요가 없고 비교적 작은 가속기로도 분석이 가능하며, 수소의 검출효율이 우수하다는 점 등 많은 장점이 있다. 그러나 한편으로는 분석가능한 깊이가 수천 $\AA$ 정도로 제한되고 질량 분해능도 수십 MeV 내지 100MeV 이상의 고에너지 이온빔을 이용하는 경우에 비해 떨어진다는 단점이 있다. 또한 묵운 원소의 분석이 불가능하기 때문에 경원소의 분석에 국한하여 적용하고 무거운 원소에 대해서는 RBS를 병용하게 된다. 본 연구에서는 일본 이화학연구소의 선형가속기인 RILAC으로부터 얻은 40MeV Ar 이온 및 138 MeV Xe 이온을 이용하여 TOF-ERDA 시스템을 제작하였다. 그러기 위해서 고에너지 이온의 비행시간을 측정하는 목적으로 높은 시간 분해능을 갖는 시간 검출기를 설계, 제작하였다. 또한 표적함 밑에는 회전원판이 있어 시간검출기 및 에너지 검출기가 중앙의 시료홀더를 중심으로 회전이 가능하도록 되었다. 회전은 표적함 밖에서 원격조정 가능하다. 이렇게 함으로써 검출각을 임의로 바꾸면서 측정이 가능하도록 하였다. 제작된 분석시스템의 성능을 확인하기 위해 YBaCuO 초전도 박막을 측정하였으며 그 결과를 그림에 나타낸다. 저 에너지 ERDA에서는 나타나기 힘든 Ba, Y, Cu 등의 무거운 원소의 피크들이 분명히 나타남을 확인할 수 있다.

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A Study on the Cause and Improvement of Crack in the Installing Structure of the Bulkhead of Aircraft (항공기 Bulkhead 체결구조의 균열 원인 및 개선에 관한 연구)

  • Choi, Hyoung Jun;Park, Sung Jae
    • Journal of the Korea Academia-Industrial cooperation Society
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    • v.21 no.6
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    • pp.448-454
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    • 2020
  • This study aims to determine the cause of structural defects occurring during aircraft operations and to verify the structural integrity of the improved features. The fracture plane was analyzed to verify the characteristics of the cracks and the fatigue failure leading to the final fracture was determined by the progress of the cracks by the repeated load. During aircraft operations, the comparative analysis of the load measurement data at the cracks with the aircraft design load determined that the measured load was not at the level of 30% of the design to be capable of being damaged. A gap analysis resulted in a significant stress of approximately 32 ksi at the crack site. Pre-Load testing also confirmed that the M.S. was reduced by more than 50% from +0.71 to +0.43, resulting in a sharp increase in aircraft load and the possibility of cracking when combined. Thus, structural reinforcement and the removal of the gap for aircraft cracking sites improved the defect. Based on the structural strength analysis of the improvement features, the bulkhead has a margin of about +0.88 and the fitting feature is about +0.48 versus allowable stress. In addition, the life analysis results revealed an improvement of approximately 84000 hours.

Unguided Rocket Trajectory Analysis under Rotor Wake and External Wind (로터 후류와 외풍에 따른 무유도 로켓 궤적 변화 해석)

  • Kim, Hyeongseok;Chae, Sanghyun;Yee, Kwanjung
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.46 no.1
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    • pp.41-51
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    • 2018
  • Downwash from helicopter rotor blades and external winds from various maneuvering make an unguided rocket change its trajectory and range. For the prediction of the trajectory and range, it is essential to consider the downwash effect. In this study, an algorithm was developed to calculate 6-Degree-Of-Freedom(6 DOF) forces and moments exerting on the rocket, and total flight trajectory of a 2.75-inch unguided rocket in a helicopter downwash flow field. Using Actuator Disk Model(ADM) analysis result, the algorithm could analyze the entire trajectory in various initial launch condition such as launch angle, launch velocity, and external wind. The algorithm that considered the interference between a fuselage and external winds could predict the trajectory change more precisely than inflow model analysis. Using the developed algorithm, the attitude and trajectory change mechanism by the downwash effect were investigated analyzing the effective angle of attack change and characteristics of pitching stability of the unguided rocket. Also, the trajectory and range changes were analyzed by considering the downwash effect with external winds. As a result, it was concluded that the key factors of the rocket range change were downwash area and magnitude which effect on the rocket, and the secondary factors were the dynamic pressure of the rocket and the interference between a fuselage and external winds. In tailwind case which was much influential on the range characteristics than other wind cases, the range of the rocket rose as increasing the tailwind velocity. However, there was a limit that the range of the rocket did not increase more than the specific tailwind velocity.

Study on the Defect Improvement of Fuel Flow Proportioner Install Structure on Aircraft (항공기 연료흐름분배기 장착 구조물 결함개선 연구)

  • Choi, Hyoung Jun;Lee, Jin Won;Choi, Jae Ho;Park, Sung Jae
    • Journal of the Korea Academia-Industrial cooperation Society
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    • v.21 no.4
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    • pp.558-567
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    • 2020
  • This study examined the defect characteristics of fuel flow proportioner-mounted structures to analyze the causes of structural defects during aircraft operation. System vibrations and single component vibrations that occur during aircraft operations are usually the cause of structural defects. The fuel flow proportioner causes a defect in the support structure due to the vibration caused by the pressure change caused by the sudden increase in the flow rate. Defects in the support structure of the fuel flow proportioner are not correlated directly with the cracking of the maneuver, and flight time according to aircraft operation analysis is related to the use of A/B. The structural reinforcement configuration was confirmed through static and life analysis of the cracks of the bracket mounted under the fuel flow proportioner for improvement of the defect. An analysis of the reinforcement revealed a minimum structural strength of +0.15. Structural life analysis confirmed that the stress acted on the site under 15Ksi. The fatigue life was confirmed to be more than 7,700 Cycles.