• Journal of computational fluids engineering
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• v.19 no.3
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• pp.62-68
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• 2014

The aerodynamic and noise calculations were performed through the CFD-CSD loose coupling methodology. In the loose coupling process, the trimmed rotor airloads were predicted by the in-house CFD code based on unstructured overset meshes, and the trim of the rotorcraft and the aeroelastic deformation of rotor blades were accounted with the CAMRAD II rotorcraft comprehensive code. The set of codes was used to analyze the HART-II baseline test condition. The effect of grid resolution and time step was examined and the loose coupling approach was found to be stable and convergent for the case. Comparison of the resulting sectional airloads, structural deformations, the noise carpets and the wake geometry with experimentally measured data was presented and showed the good agreement.

• International Journal of Aeronautical and Space Sciences
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• v.8 no.2
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• pp.44-53
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• 2007

A three-dimensional viscous flow solver has been developed for the prediction of the aerodynamic performance of hovering helicopter rotor blades using unstructured hybrid meshes. The flow solver utilized a vertex-centered finite-volume scheme that is based on the Roe's flux-difference splitting with an implicit Jacobi/Gauss-Seidel time integration. The eddy viscosity are estimated by the Spalart- Allmaras one-equation turbulence model. Calculations were performed at three operating conditions with varying tip Mach number and collective pitch setting for the Caradonna-Tung rotor in hover. Additional computations are made for the UH-60A rotor in hover. Reasonable agreements were obtained between the present results and the experiment in both blade loading and overall rotor performance. It was demonstrated that the present vertex-centered flow solver is an efficient and accurate tool for the assessment of rotor performance in hover.

• Journal of the Korean Society for Precision Engineering
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• v.12 no.11
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• pp.5-19
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• 1995

항공기 기술의 발전은 다양한 과학기술 분야의 발달에 끊임없이 큰 영향을 주어왔고, 또 기기서 파생된 신 기술도 수없이 발생하였다. NC 공작기계도 그 하나이다. 제 2차 세계대전 후 미공군은 복잡한 형상의 항공기 부품가공과 고정밀도의 검사용 Gauge를 제작할 필요성을 얻게 되었다. Helicopter의 Rotor blade의 Prifile 검사용 Plate gauge를 가공할 수 있는 기계를 개발 중에 있었던 J.T.Person이 Jig boring machine을 저자적으로 제어하면서 Gauge를 가공하는 방법을 1947년 미공군에 제안하게 되었다. 이것이 NC 발달사에 기록된 역사적인 사실이며 이 Project는 후에 MIT로 넘아가고 1952년에 NC milling machine을 완성시켰다. 그 후, 1955년 Gidding & Lewis사가 최초로 NC 공작기계를 공업화한 제1호기 Numericord를 시장에 내 놓게 되었다.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2001.05a
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• pp.115-120
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• 2001

A gyroscope is a rotating body possessing one axis of symmetry and whose rotation about the symmetry axis is relatively large compared with the rotation about any other axis. Tuning fork is this type of structure that various modem gyro-sensors are based on. In this paper, dynamic behavior of a cantilevered beam subjected ta a base rotation with respect to the eccentric axis that is parallel to the beam axis is analyzed. The final equations of motion in terms of generalized coordinates can be solved with numerical scheme with various values of angular velocities and angular accelerations of the rotating axis. In contrast to the case of rotating cantilever beam like helicopter blade, the rotational motion with respect to the beam axis has effect to decrease the stiffness of the beam and has unstable region depending on the magnitude of the rotational angular velocity and angular acceleration.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2000.06a
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• pp.1222-1227
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• 2000

The optimization study are carried out for helicopter rotor blades with composite box-beam spar. The objective function is to minimize the weight of rotor blades subject to frequency, aeroelastic stability and failure constraints. Design variables include the number of ply and ply angles of the laminated walls. The beam model of a hinge less rotor blade is based on a large deflection beam theory to describe the arbitrary large deflections and rotations. The p-k method and unsteady two dimensional strip theory are used to calculate aeroelastic stability boundary.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.21 no.6
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• pp.981-987
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• 1997

Modern helicopter rotor blades with non-homogeneous cross section composed of anisotropic material rquire highly sophisticated structural analysis. Variation in cross section geometry makes this task of analysis more complicated. Since rotor blades generally are much longer than their lateral dimensions, one-dimensional models seem feasible, at least from a computational point of view. Therefore determination of the principal coordinate system is very important to remove the structural coupling for one-dimensional beam modelling. In this study, shear center, and principal direction. The method will be verified by comparing the results with confirmed experimental results.

• International Journal of Aerospace System Engineering
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• v.2 no.1
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• pp.24-30
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• 2015

In helicopter bearingless rotor design, the flexbeam is the key component of rotor system, which plays an importantrole in the blade flapping, lead-lag movement, torsion, and load transfer. Flexbeam must have the minimum torsion stiffness with enough tension strength. In this paper, we first investigated the torsion stiffness of different cross section configurations of the flexbeam through some simple experiments. Then we analyzed a rotor's dynamical characteristics with finite element method and got the rotor's fan plot. After that, we studied the relationship between the frequency changes with the spanwise distribution of mass and stiffness in bearingless rotor. Finally, we analyzed the influence of the flexbeam on dynamical characteristics of the bearingless rotor system, and completed the design of this type of rotor flexbeam.

• Journal of Aerospace System Engineering
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• v.3 no.3
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• pp.17-23
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• 2009

KARI SUAV (Smart Unmanned Aerial Vehicle) program is currently on the phase of ground and flight test. SUAV is a tilt rotor aircraft having the capability of vertical take-off/landing and high speed forward flight. The SUAV rotor system is 3-bladed, gimbaled hub type, which is not common for conventional helicopter configuration. In this paper, detailed procedure and method of rotor pitch rigging, tracking and balancing were described based on the experience of SUAV ground test.

• Proceeding of EDISON Challenge
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• 2016.03a
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• pp.190-194
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• 2016

자연에서 안정적이고 경제성이 높은 구조로 벌집 구조가 많이 언급이 된다. 이러한 벌집 구조의 특징으로 인해 많은 공학자들이 그 구조를 모방하여 적용하고 있다. 벌집 구조에도 다양한 종류가 존재하지만 그 중 음의 푸아송 비(Poisson's ratio)를 갖는 Chiral Honeycomb 구조가 많이 연구되고 있다. 푸아송 비는 물질이나 구조의 고유한 물성치로 종, 횡 방향의 변형율로 나타내며 이 값으로 외부 조건으로부터의 변형을 예측 할 수 있게 된다. 흔히 푸아송 비는 양의 값을 가지지만 Chiral Honeycomb 구조는 음의 푸아송 비를 가져 기존의 구조와는 다른 기계적 성질을 가지게 된다. 이 논문에서는 Chiral Honeycomb 구조 중에서도 4개의 관절(ligament)를 가지는 Tetra Chiral Honeycomb 구조에 대해 EDISON용 CASADsovler 프로그램을 통해 유한 요소 해석을 수행하여 등가 물성치를 구해 보았으며 기존 실험의 값들과 비교를 통해 해석을 위해 필요한 적절한 대표 체적에 대해 확인해 보았다.

• Journal of the Korean Society for Precision Engineering
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• v.13 no.3
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• pp.9-25
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• 1996

수치제어(Numerical control)의 개념은 1800년대부터 시작되었다. 프랑스의 Joseph Jacquard는 1801년에 구멍을 낸 카드(Perforated cards)를 이용하여 베틀기계에 직물의 모양을 Design하는데 자동적으로 Control 하는 방법을 창조해냈다. 그 후 구멍을 낸 카드를 이용하여 페달을 밟아 얻어진 공기를 Air motor와 Valve 를 조정하므로서 자동적으로 Piano를 연주하게 하는 방법도 역시 수치제어다. 이 NC의 개념이 실제 공작기계 에 적용된 것은 제2차 대전후의 일이다. 미공군(US Air force)에서는 복잡한 형상의 항공기부품가공과 그것을 검사할 검사용 Gauge를 고정밀도로 효율있게 제작할 필요성이 절실해졌다. 미국 Michigan주 Traverse시에 있던 Parsons회사도 Helicopter의 Rotor blade의 윤곽을 정확하게 검사하는 Plate gauge를 가공할 수 있는 기계를 개발하고 있었으며 그 회사의 사장 John T. Parsons씨는 Jig boringmachine을 전자적으로 제어하는 Plate gauge를 가공하는 방법을 미공군에 제안을 하였다. 1948년 미공군에서는 설계번경이 수없이 일어나는 Missile 의 부품을 단시간 내로 제작하기 위해서 Persons사와 기술계약을 맺고 새로운 공작기계 개발에 착수하므로서 NC공작기계 연구를 시작한 역사적인 시발점이 되었다.