• Title/Summary/Keyword: 틸팅각

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Dynamic Interaction Analysis of Tilting Train and Curved Track (틸팅열차 주행시 곡선부 궤도에서의 동적상호작용)

  • Chung, Keun-Young;Koh, Tae-Hoon
    • Journal of the Korean Society for Railway
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    • v.15 no.2
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    • pp.162-171
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    • 2012
  • In this study, a new dynamic interaction analysis method for tilting trains and curved track is presented. Three dimensional lumped parameter vehicle elements are used to model tilting train, and the proposed analysis technique can simulate driving direction change of vehicle, the effect of track cant, wheel-rail contact angle, and tilting angle of tilting trains, etc. The proposed method passed several basic verification tests, and it is expected that the suggested method is applicable for practical problems.

The Characteristics of Cutting Force and Surface Roughness According to Tool Tilting Angle in 5-axis High Speed Machining of Molds (금형의 5축 고속가공에서 공구 틸팅각에 따른 절삭력에 표면거칠기 특성)

  • Kang, Ik-Soo;Kim, Jeong-Suk;Kim, Suk-Won;Lee, Ki-Yong
    • Transactions of the Korean Society of Machine Tool Engineers
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    • v.16 no.5
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    • pp.63-69
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    • 2007
  • The high speed machining has been widely applied to manufacture dies and machine elements in industrial field. Especially, 5-axis milling has been employed to produce a wide range of turbine blades, impellers and complex molds. In this study, the machining characteristics of injection molds were investigated according to tool tilting angles in 5-axis milling. The cutting force and surface roughness were investigated with various tool tilting angles. When the tool tilting angle was over than 10 degree, the characteristics of cutting force and surface roughness were improved in machining of Al alloy.

Vibration Control of Composite Wing-Rotor System of Tiltrotor Aircraft (틸트로터 항공기 복합재료 날개의 진동 제어)

  • Song, Oh-Seop
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.35 no.6
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    • pp.509-516
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    • 2007
  • Mathematical modeling and vibration control of a tiltrotor aircraft composite wing-rotor system are investigated in this study. A wing-mounted rotor can be tilted from the vertical position to a horizontal one, and vice versa. Effect of vibration control of the wing-rotor system via piezoelectricity is studied as a function of tilt angle, ply angle of composite wing and rotor's spin speed. Composite wing is modeled as a thin-walled box beam having a circumferentially uniform stiffness configuration that produces elastic coupling between flap-lag and between extension-twist behavior. Numerical simulations are provided and pertinent conclusions are outlined.

FLOW ANALYSIS AROUND THE ROTOR BLADE WITH TILT ANGLES (틸팅각에 따른 로터 블레이드 주위의 유동장 해석)

  • Yoo, Y.H.;Choi, J.W.;Kim, S.C.;Kim, J.S.
    • 한국전산유체공학회:학술대회논문집
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    • 2008.03a
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    • pp.166-170
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    • 2008
  • The changing process from hovering mode to transition one is of importance to determine a stability of tilt-rotor aircraft, which is utilized in UAV(Unmaned Aerial Vehicle). The analysis on fluid flows and aerodynamic characteristics according to variation of tilting angle of rotor is essential step in development of tilt-rotor. In the present study, the computation domain is divided into the rotating and stationary regions in order to consider the rotating blades. For the convenient realization of various tilting angle as well as application of boundary condition, the whole computation region is constructed into sphere domain. The near farfield boundary condition is adopted. The airfoil used in computation is NACA 0012. The computation results for the hovering mode are validated by comparing with previously conducted experimental results. From the results, the flow fields around rotor blade and the aerodynamic characteristics in transition mode are observed. The computational result will provide the basis for development and performance evaluation of tilt-type aircraft.

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Design of Control Mixer for 40% Scaled Smart UAV (스마트무인기 축소모형의 조종면 혼합기 설계)

  • Gang, Yeong-Sin;Park, Beom-Jin;Yu, Chang-Seon
    • Aerospace Engineering and Technology
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    • v.5 no.2
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    • pp.240-247
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    • 2006
  • Tilt rotor aircraft is a multi-configuration airplane which has three independent flight modes; helicopter, conversion, and aiplane. The control surface mixer resign is reqctired to generate and distribute efficient control forces and moments in each flight mode. In the conversion mode, the thrust vector is changed from helicopter mode to airplane, therefore the thrust vector makes undesired forces and moments which affect on pitch, roll and yaw dynamics. This paper describes the design results of control surface mixer design which minimize the undesired forces and moments due to nacelles tilting angle change for 4O% scaled model.

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