• Title, Summary, Keyword: Rotorcraft

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Development of European Rotorcraft in 21st Century (21세기 유럽의 회전익 개발 동향 분석)

  • Oh, Sejong;Park, Donghun
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.46 no.8
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    • pp.679-686
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    • 2018
  • In previous paper[1], the authors had compared the current status of European and US rotorcraft development status. In this paper, more detailed procedures have been studied how the European rotorcraft technologies are developed preparing for 21 st century to be more competitive to US. For the systematic procedure to develop next generation aviation technologies including rotorcraft, the pan-European organization, ACARE, was established, and proposed major research agenda for next generation aviation technologies and businesses. Based on the proposed research agenda, all the R&D programs supported by EU are reorganized to be more efficient and competitive. The procedures for the rotorcraft technologies are, first, cabin noise/vibration reduction program (FRIENDCOPTER), second, core technologies to increase of rotor efficiencies and reduce rotor noise (GRC), and then finally to develop fast/long-range next generation rotorcraft (Fast Rotorcraft). As mentioned in previously, all the R&D procedure has to satisfy basic research agenda especially the environmental impact. With theses procedure, the European rotorcraft business had successful achievements not only in current and future market share, but also preparing for next generation rotorcraft platform such as compound and tilt-rotor rotorcraft satisfying market needs.

Establishment of Rotor Speed Operating Limitation for Medium Class Utility Rotorcraft (중형 기동 회전익기 로터회전수 제한 수립)

  • Park, Jonghoo
    • Journal of the Korean Society for Aviation and Aeronautics
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    • v.21 no.2
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    • pp.26-32
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    • 2013
  • The rotorcraft makes lift and control forces by the rotor thrust. At the development phase of the rotorcraft, the operational limitations have to be established. And it shall be demonstrated to operate the rotorcraft safely within the limitations. This paper introduces establishment and evaluation results of operational rotor speed limitations for the medium class utility rotorcraft. And it shows the follow-up activities after design changes of rotor speed indicators and aural warning systems for implementing the rotor speed limitations.

Numerical Predictions of Rotor Performance using aNavier-Stokes Simulationcoupled with a Time-Marching Free-Wake Model

  • Chung, Ki-Hoon;Yee, Kwan-Jung;Hwang, Chang-Jeon;Lee, Duck-Joo
    • International Journal of Aeronautical and Space Sciences
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    • v.5 no.2
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    • pp.62-70
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    • 2004
  • CFD method has been coupled with a time-marching free-wake model by usingfield velocity approach suggested by J. D. Baeder (Ref. 1). The coupled method hasbeen applied to rectangular and BERP-like blades and the calculated perfonnance dataare compared with the experimental results.For hovering analysis, the present method could yield sufficiently good resultswith reasonable computation time and is particularly suitable for the flow fieldanalysis with the complex shaped blade.

Rotorcraft Waypoint Guidance Design Using SDRE Controller

  • Yang, Chang-Deok;Kim, Chang-Joo;Yang, Soo-Seok
    • International Journal of Aeronautical and Space Sciences
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    • v.10 no.2
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    • pp.12-22
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    • 2009
  • This paper deals with the State-Dependent Riccati Equation (SDRE) Technique for the design of rotorcraft waypoint guidance. To generate the flight trajectory through multiple waypoints, we use the trigonometric spline. The controller design and its validation is based upon a level 2 simulation rotorcraft model and the designed SDRE controller is applied to the trajectory tracking problems. To verify the designed guidance law, the simulation environment of high fidelity rotorcraft model is developed using three independent PCs. This paper focuses on the validation of rotorcraft waypoint guidance law which is designed by using SDRE Controller.

Further Improvement in Rotor Aerodynamics Estimation in Helicopter Conceptual Design and Optimization Framework for a Compound Rotorcraft

  • Lim, JaeHoon;Shin, SangJoon;Kee, YoungJung
    • International Journal of Aeronautical and Space Sciences
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    • v.18 no.4
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    • pp.641-650
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    • 2017
  • In order to include the design capability for a compound rotorcraft in a helicopter conceptual design and optimization framework, relevant further improvement was planned and conducted. Previously, a certain conceptual design optimization framework was developed by the present authors to design a modern rotorcraft with single main and tail rotor. The previously developed framework was further improved to expand its capability for a compound rotorcraft. Specifically, its power estimation algorithm was upgraded by using a comprehensive rotorcraft analysis program, CAMRAD II. The presently improved conceptual design and optimization framework was validated using data of the XH-59A aircraft.

Next Generation Rotorcraft Technologies in USA and Europe (미국과 유럽의 차세대 회전익 기술 개발 현황)

  • Oh, Sejong;Kim, Sung Hwan
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.42 no.8
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    • pp.713-721
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    • 2014
  • In Europe and USA, new programs called GRC(Green Rotorcraft) and SRW (Subsonic Rotary Wing program) respectively, have been currently underway for developing the next generation rotorcraft. The final goal is to develope fuel-efficient/environmental-friendly tilt-rotor civilian rotorcraft, which can partly replace short-range regional aircrafts. Also for safe operation, the new rotorcraft technology is cooperated with the new air transport management(ATM) system, called SESAR(Single European Sky ATM Research) and NextGen(Next Generation Air Transport System) in Europe and USA. In addition to achieve the final goal, the tilt-rotor aircraft, they are trying to improve the performance of conventional helicopters by adopting more efficient propulsion system, active rotor system, and reducing internal and external noise. Especially in GRC program of Europe, the environmental factors such as noise, fuel efficiency, reduction of emission gas(CO2, NOx), are focused for the new technologies.

A Study on the Icing Certification of Rotorcraft (회전익 항공기의 결빙 인증에 대한 연구)

  • Lee, Hae-Sun;Park, Jong-Hyuk
    • Aerospace Engineering and Technology
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    • v.7 no.2
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    • pp.196-204
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    • 2008
  • Modem rotorcraft is required to have the capability to operate in all-weather conditions. Also icing condition is important issue to aircraft safety and certification. And rotorcraft icing research has come a long way during the past few decades. The aircraft icing is the most difficult to handle. So, icing-related accidents, incidents and operating problems still occur regularly in service, despite improvements in design and test techniques. By reviewing icing certification requirement of FAR(Federal Aviation Regulations) and KAS(Korean Airworthiness Standard), this paper describes methods how to demonstrate safety in the flight and consideration of icing when rotorcraft is required TC(Type Certification).

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Developmental Trends of High Performance Rotorcraft and the Analytic Method of Autorotation (고성능 회전익기의 개발동향과 자동회전의 해석기법)

  • Kim, Hak-Yoon;Sheen, Byung-jun
    • Journal of the Korean Society for Aviation and Aeronautics
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    • v.22 no.3
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    • pp.60-67
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    • 2014
  • Technical history of VTOL aircraft is examined from the early helicopter appearance to recent experimental rotorcraft in order to distinguish the core issues of those aircraft. Performance and technological challenges of some VTOL aircraft such as tilt rotor, convertiplane, gyroplane, and coaxial helicopter are discussed. As a new generation high performance rotorcraft, Sikorsky X2 is intensively investigated. Considering the developmental history of X2, the autorotational ability at high speed is recognized as a core technology. Analytic method of autorotation and some results are shown and presents research subjects related to the future Korean high performance rotorcraft.

A Simulation on the Weapon System of Rotorcraft for Improving the Effects of Korean Future Combat System(FCS) (한국형 미래전투체계 효과도 분석을 위한 회전익 무장체계 시뮬레이션)

  • Hong, Jungwan;Park, Sang C.;Kwon, Yongjin
    • Journal of the Korea Institute of Military Science and Technology
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    • v.16 no.4
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    • pp.501-506
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    • 2013
  • This research is to develop a simulation framework to gauge the mission effectiveness of the rotorcraft system that will be a part of Korean future combat system. The rotorcraft system comprises of many subsystems that are very time-consuming and tedious to model. Each subsystem and its characteristics have been modeled using component-based modeling techniques, which enhances its reusability. The entire system is then constructed from the individually modeled component, which significantly reduces the modelling time. The mission effectiveness of the rotorcraft system is simulated using the developed models, and the output indicates that the methodology proposed in this study is useful, which will be suitable for the modeling and simulation of Korean future combat system.

Assessment of Crashworthiness Performance for Fuel Tank of Rotorcraft (회전익 항공기용 연료탱크 내추락 성능 시험평가)

  • Kim, Hyun-Gi;Kim, Sung-Chan;Lee, Jong-Won;Hwang, In-Hee;Hue, Jang-Wook;Shin, Dong-Woo;Jun, Pil-Sun;Jung, Tae-Kyung;Ha, Byung-Kun
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.38 no.8
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    • pp.806-812
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    • 2010
  • Fuel tanks for rotorcraft have a great influence on the survivability of crews. The philosophy of crashworthy rotorcraft design evolved from the long term effort of the US Army. US army established MIL-DTL-27422D for specifying detail requirements related to crash resistant fuel tank especially for military rotorcraft to prevent post crash fire which is the greatest threat to life in rotorcraft crash. Crashworthiness of the rotorcraft fuel tank could be guaranteed through the crash impact tests which are specified in the MIL-DTL-27422D. Fuel tanks for Korea Helicopter Program have been developed and tested according to MIL-DTL-27422D with minor modifications of flexible fittings. The present study shows some results of the mandatory crash impact tests of the fuel tanks to verify their performances.