• Title/Summary/Keyword: 헬기착륙장치

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Semi-Active Control of Helicopter Landing Gear using Magneto-Rheological Damper (MR 댐퍼를 이용한 헬기 착륙장치 반능동제어)

  • Hwang, Jae-Up;Hwang, Jae-Hyuk;Bae, Jae-Sung;Hyun, Young-O;Lim, Kyoung-Ho;Kim, Doo-Man;Kim, Tae-Wook
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.36 no.4
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    • pp.346-351
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    • 2008
  • In this paper, the semi-active control of a helicopter landing gear using magneto -rheological(MR) damper is studied. A dynamic model of the MR damper is formulated by incorporating magnetic field-dependent Bingham properties of the MR fluid. The electromagnet of the MR damper is designed and its magnetic field is analyzed using a commercial finite element code. The damping characteristics of MR damper by changing the intensity of the magnetic field are investigated and the dynamic responses of the helicopter landing gear with MR damper are simulated. The semi-active control of the helicopter landing gear is simulated by implementing a sky-kook control algorithm and its performance is evaluated comparing to the passive control.

Crashworthy Design of Helicopter Landing Gear (헬기용 착륙장치 내추락 설계)

  • Lee, Sang-Wook;Kim, Tae-Uk;Shin, Jeong-Woo;Lee, Seung-Gyu;Kim, Sung-Chan;Hwang, In-Hee;Lee, Je-Dong
    • Proceedings of the KAIS Fall Conference
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    • 2011.12b
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    • pp.507-510
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    • 2011
  • 착륙장치는 완충장치를 이용하여 항공기 착륙 시의 충격을 흡수하는 역할을 한다. 군용 헬기를 비롯한 일부 항공기에서는 비상 착륙시 탑승원의 생존성과 안전성을 향상시키기 위해, 착륙장치에 내추락 요구조건을 부여하기도 한다. 본 연구에서는 내추락 요구조건을 충족하는 다양한 착륙장치 설계 개념 가운데, 파손 장치를 이용한 전륜 착륙장치와 Blow-off 밸브를 이용한 주륜 착륙장치 설계를 제시하고, 성능해석을 통한 입증 과정을 소개한다.

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Force Control of Main Landing Gear using Magneto-Rheological Damper (MR 댐퍼를 이용한 주륜 착륙장치 하중제어기법 연구)

  • Hyun, Young-O;Hwang, Jae-Up;Hwang, Jae-Hyuk;Bae, Jae-Sung;Lim, Kyoung-Ho;Kim, Doo-Man;Kim, Tae-Wook
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.37 no.4
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    • pp.344-349
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    • 2009
  • To improve performance of the main landing gear for helicopters, a semi-active control landing gear is introduced in this paper. An MR damper based on commercial finite element electromagnetic field analysis of an electromagnet has been adapted the shock absorber. Force control algorithm (which maintains constantly the sum of air spring force and damping force as internal forces) which keep the sum of air spring force and damping force constant during landing, has been used for the controller, applied to control the semi-active landing gear. A series of drop simulations using ADAMS has been done with the passive, sky-hook control type, and force control type landing gears. The result of each simulation has been compared to evaluate the landing performance of the proposed force control type landing gear.

Drop Test Simulation of semi-active Landing Gear using Commercial Magneto-Rheological Damper (상용 MR 댐퍼를 이용한 반능동형 착륙장치 낙하실험)

  • Hwang, Jae-Up;Hwang, Jae-Hyuk;Bae, Jae-Sung;Lim, Kyoung-Ho
    • Journal of Aerospace System Engineering
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    • v.4 no.4
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    • pp.44-48
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    • 2010
  • This paper is used the commercial magneto-rheological(MR) damper for landing gear. The damping characteristics of Commercial MR damper by changing the intensity of the magnetic field are investigated and the dynamic responses of the landing gear. it is set up tset equipment, the landing gear drop test system. The landing gear involved drop testing the gear. The landing gear is tested by implementing sky-hook control algorithm and its performance is evaluated comparing to the result.

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Crashworthy Design and Test of Landing Gear (착륙장치 내추락 설계 및 시험평가)

  • Kim, Tae-Uk;Lee, Sang-Wook;Shin, Jeong-Woo;Lee, Seung-Kyu;Kim, Sung-Chan;Hwang, In-Hee;Jo, Jeong-Jun;Lee, Je-Dong
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.40 no.7
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    • pp.601-607
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    • 2012
  • The main function of a landing gear is to absorb the impact energy during touchdown. It it occasionally required for landing gear to have crashworthiness for improving survivability and safety in case of emergency landing. This paper introduces the design concept, performance analysis and drop test procedures for the development of the crashworthy landing gear. The shock absorbing ability and the crash behavior are proved by analyzing various sensor data and video clips from high speed camera recording during drop tests.

Dynamic Analysis of a Helicopter Landing Gear with Considering Flexible Structural Modes (동체의 유연성을 고려한 헬기 착륙장치의 동특성 해석 연구)

  • Hyun, Young-O;Bae, Jae-Seoung;Kim, Young-Seok;Hwang, Jae-Up;Lim, Kyoung-Ho;Kim, Doo-Man;Kim, Tae-Wook;Hwang, Jai-Hyuk
    • Journal of the Korean Society for Aviation and Aeronautics
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    • v.15 no.4
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    • pp.33-37
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    • 2007
  • In this paper, a dynamic analysis of a helicopter landing gear with considering flexible structural modes has been investigated. The main body of the helicopter has been modeled as a flexible body using FEM code, then a few selected vibration modes of the helicopter main body have been used as basis for the dynamic analysis of the helicopter landing gear. The simulation of dynamic analysis was carried out on the base of ADAMS aircraft module. It has been found by a series of simulation that the flexible structural modes has a significant effect on the dynamic characteristics of helicopter landing gear as the flexibility of the main body is increased.

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Force Control of Main Landing Gear using Hybrid Magneto-Rheological Damper (하이브리드 MR댐퍼를 이용한 주륜 착륙장치 하중제어기법 연구)

  • Hyun, Young-O;Hwang, Jae-Up;Hwang, Jae-Hyuk;Bae, Jae-Sung;Lim, Kyoung-Ho;Kim, Doo-Man;Kim, Tae-Wook;Park, Myung-Ho
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.38 no.4
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    • pp.315-320
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    • 2010
  • To improve not only the basic performance but also the fail-safe performance, power consumption of the main landing gear for helicopters, a semi-active control landing gear using hybrid MR damper, was introduced in this paper. This damper of the configuration to install a permanent magnet in a electromagnet MR damper, was designed by the trade-off study on permanent magnet location and a magnet field analysis. Force control algorithm which keep the sum of air spring force and damping force at a specified value during landing, was used for the controller. The drop simulations using ADAMS Model for this semi-active control landing gear, were done. The improvement of the preceding performances as the result to evaluate the landing performance by the simulations, has been confirmed.

An Improvement Study on Brake System for KUH-1 (한국형 기동헬기의 제동장치 개선에 관한 연구)

  • Choi, Jae Hyung;Lim, Hyun-Gyu;Yoon, Jong Jin;Kang, Deuk Soo
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.45 no.4
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    • pp.292-299
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    • 2017
  • The KUH-1's Wheel Brake Assembly which is Brake System is an essential component to perform flight mission for pilot. It has function of taxing, differential braking and parking to sustain landing capability. However, the skid and abrasion of tire were occurred in mass-produce operation. Also, if it is occurred on the ground, the flight can not be performed. In this case, the defect is a major cause of the decrease in the operation rate of aircraft. In this paper, the cause of the defect in flight was identified and the failure process was organized. Also, it describes design improvements which was derived from troubleshooting and suggests verification results of flight test.