• Current Industrial and Technological Trends in Aerospace
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• v.5 no.1
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• pp.75-92
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• 2007

2002년 프론티어사업의 일환으로서, 10년간 1200억의 예산으로 미래형 신개념비행체 기술개발사업을 시작한 스마트무인기사업은, $2002{\sim}2003$년 수행한 개념연구를 통해 미래형 신개념 고속 수직이착륙 항공기 개념으로서 틸트로터 개념을 선정하고 이의 개발에 매진하고 있다. 사업단에서는 우선, 항공 선진국에서 지난 반세기 동안 시행한 다양한 비행체 개념연구결과에 대해 자체적인 비교 분석 및 국제공동 연구를 근간으로하여, 당시 틸트로터에 필적하는 가능성을 보였던 스탑트로터(보잉사), 복합자이로콥터(카터콥터사) 개념이 아닌, 틸트로터 비행체의 기술개발을 결정하게 되었다. 각각의 비행체 개념이 갖는 위험성과 도전성, 그리고 소요기술, 설계특성, 개발 위험도 등에 대한 면밀한 분석을 기초로 한 사업단의 체계적 의사결정은 주효했다. 스탑트로터개념은 비행시험의 잇단 실패와 지연/잠정 중단사태가 이어졌고, 복합자이로콥터 또한 잇단 비행사고로 2002년 기록한 148kts를 능가하는 고속성능 시현에 지금까지 실패함으로써, 실용화 가능한 고속수직이착륙기로서의 검증을 위해서는 해결해야할 기술적 과제가 많이 남아있음을 보여주고 있다. 반면, 틸트로터 개념의 경우 V-22의 설계 수정형에 대한 성공적인 비행시험완료 및 인증획득으로 전면양산승인이 2005년 결정되어 458대가 (미해병대(360), 해군(48), 공군(50)) 납품될 예정이고, 2010년 인증획득을 목표로 민수용으로 개발중인 BA609의 순조로운 비행시험진행, 무인기로 개발된 Eagle Eye 기술시현기의 비행 시험성공과 2003년 미 해양경찰청으로부터 Deep Water 프로그램의 장거리 순찰임무 주력기종 선정과 같이 군용, 상용, 무인용 고속 수직이착륙 시장의 전 방위적 진입이 현실화되고 있다. 이에 따라 항공업계의 반응은 2가지 방향으로 나뉘고 있다. 하나는 유럽의 ERICA 프로그램과 같이 틸트로터 기술 개발을 서두르자고 주장하는 방향이고, 다른 하나는 시콜스키의 X2 프로그램과 같이 틸트로터와는 차별화된 독자적인 고속 수 직이착륙 비행체 개념 개발을 시도하는 것이다. 이러한 배경으로 국내 독자적인 기술력으로 지난해까지 일구어낸 성공적인 스마트무인기 상세설계 종료 및 축소형 비행체 전환비행성공은 그 의의가 매우 크다고 할 수 있다. 본 논문은 틸트로터 개발사를 통해, 신개념 비행체 개발의 어려움과 교훈을 알아보고, 세계에서 2번째로 틸트로터 기술을 개발하고 있는 스마트무인기 사업의 현황과 기술적 특징 및 의의의 정리, 그리고 틸트로터의 대안으로 진행중인 새로운 고속 VTOL 비행체 연구현황에 대한 소개 와 간단한 기술적 평가를 포함시켰다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.41 no.4
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• pp.261-267
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• 2013

In this paper, wind tunnel test and analytical prediction are compared for result of flapping motion in helicopter forward flight condition. Tests were performed at low speed wind tunnel at Chungnam National University, test section of wind tunnel has 1.8 by 1.8 meter open-jet test section area. According to the results of measured data for aerodynamic performance of model rotor in forward flight. It has to observed the difference of analytical and measured results of power coefficient for fixed thrust coefficient. And calculated and measured data of helicopter rotor flapping angles in forward flight are compared for a model rotor in a wind tunnel. A test was conducted to verify the measured data of coning and lateral/longitudinal flapping angle with predicted values.

• 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.

• Composites Research
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• v.32 no.4
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• pp.191-198
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• 2019

The basic mechanical properties of helicopter rotor blade are important parameters for the analysis of helicopter performance. However, it is difficult to estimate these properties because the most of rotor blades consist of various materials such as composite materials and metals, etc. In this paper, the bending/torsional stiffness for composite rotor blade of unmanned helicopter were evaluated through experimental and analytical studies. In finite element analysis, the bending/torsional stiffness were evaluated through the relationship of load-displacement and element stiffness matrix. The evaluated stiffness from the measured strains and displacements in bending and torsional test agreed well with the derived results of FEA.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.6
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• pp.87-95
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• 2004

In this paper, an efficient method for modeling a dual-rotor type wind turbine generator system and simulation results are presented. The wind turbine is treated as a collection of several rigid bodies, each of which represents, respectively, main and auxiliary rotor blades, high/low speed shafts, generator, and gear system. Simulation software WINSIM is developed to implement the proposed modeling method and is used to investigate the transient and steady-state performance of the wind turbine system.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.40 no.2
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• pp.118-128
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• 2012

The goal of this paper is to design the target tracking controller for a quadrotor micro UAV using a vision sensor. First of all, the mathematical model of the quadrotor was estimated through the Prediction Error Method(PEM) using experimental input/output flight data, and then the estimated model was validated via the comparison with new experimental flight data. Next, the target tracking controller was designed using LQR(Linear Quadratic Regulator) method based on the estimated model. The relative distance between an object and the quadrotor was obtained by a vision sensor, and the altitude was obtained by a ultra sonic sensor. Finally, the performance of the designed target tracking controller was evaluated through flight tests.

• Journal of Aerospace System Engineering
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• v.11 no.4
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• pp.36-43
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• 2017

Blade design optimization of QTP-UAV prop-rotor was conducted using ModelCenter(R). Performance efficiency of the blade in hover and forward flight were adopted as the multi-objective function. Required power and pitch link force applied to constraint in each flight mode and limited lower than the value of the baseline blade. Design variables of root chord length of the blade, taper ratio, twist slope, twist angle at 0.5R of the blade, anhedral angle, parabolic coefficient of a tip shape and location of airfoil were used to generate the blade planform. CAMRAD-II, the comprehensive analysis program of rotorcraft, was used for performance analysis of prop-rotor blade in design process. Performance of the optimized blade improved 1.6% of figure of merit in hover and 13.6% of propulsive efficiency in forward flight. Pitch link force also reduced approximately 30% less than that of the baseline blade.

• Journal of the Institute of Convergence Signal Processing
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• v.23 no.4
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• pp.185-193
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• 2022

This paper proposes an adaptive sliding mode control with radial basis function neural network(RBFNN) scheme to enhance the performance of position and attitude tracking control of quadrotor UAV. The RBFNN is utilized on the approximation of nonlinear function in the UAV dynmic model and the weights of the RBFNN are adjusted online according to adaptive law from the Lyapunov stability analysis to ensure the state hitting the sliding surface and sliding along it. In order to compensate the network approximation error and eliminate the existing chattering problems, the sliding mode control term is adjusted by adaptive laws, which can enhance the robust performance of the system. The simulation results of the proposed control method confirm the effectiveness of the proposed controller which applied for a nonlinear quadrotor UAV is presented. Form the results, it's shown that the developed control system is achieved satisfactory control performance and robustness.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.5
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• pp.1-9
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• 2003

Detailed flow of a shrouded tail rotor in hover is studied by using a compressible inviscid flow solver on unstructured meshes. The numerical method is based on a cell-centered finite-volume discretization and an implicit Gauss-Seidel time integration. Numerical simulation is made for a single blade attached to the center body and guide by the duct by imposing a periodic boundary condition between adjacent rotor blades. The results show that the performance of an isolated rotor without shroud compares well with experiment. In case of a shrouded rotor, correction of the collective pitch angle is made such that the overall performance matches with experiment to account for the uncertainties of the experimental model configuration. Details of the flow field compare well with the experiment confirming the validity of the present method.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.42 no.4
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• pp.305-316
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• 2014

As avionics and mechanical devices have been developed, the size of unmanned aerial vehicle (UAV) is getting smaller. However, the complicated and accurate missions are provided to the UAV. Among various types of UAVs, quadrotors are widely used for their availability by virtue of simple structure and hovering function. However, the control of quadrotor is highly constrained, because the quadrotor is an under-actuated system which has only 4 actuator inputs. To deal with this under-actuated problem, a new quadrotor model with two more actuators in addition to the 4 propeller inputs is provided to make the system fully-actuated. For the proposed model, a controller is designed using feedback linearization methods. To validate the model and to verify the performance of the proposed controller, numerical simulation is performed.