• 한국소음진동공학회논문집
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• 제14권11호
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• pp.1129-1136
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• 2004

The structural modification to install a heavy sensor was made at the front extremities of the foreign-produced helicopter operated in the Korea Navy Mounting the sensor directly to the nose structure is unlikely to be practical because it lowers a dynamic mode of the airframe close to rotor blade passing frequencies, leading to increased helicopter vibration. Unfortunately we have no information on dynamic characteristics of the imported helicopter. So the experimental modal model derived from shake testing on the overall airframe of a working helicopter was used to solve the sensor Installation problems. The sensitivity analysis was done to evaluate what the best of modification woo)d be. Simple ID model and experimental modal data for mount system with sensor were Incorporated into overall dynamic model to assess the effects of the sensor installation on helicopter. Modal testing for the modified helicopter shows that the airframe modes are sufficiently displaced from rotor passing frequencies. The mount system has been proven fight to be sufficiently stable to meet vibration-level requirement for all required operational profiles.

• 한국항공우주학회지
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• 제43권4호
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• pp.368-376
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• 2015

본 논문은 헬리콥터 초기 설계를 위해 수정된 추정식을 적용한 헬리콥터 초기 설계 모델 정립 연구의 응용에 대한 내용으로 헬리콥터 초기 설계의 효율성을 제고하고 개선하고자 하였다. 헬리콥터 설계 시 중량계수 영향성을 확인하고 적정한 중량계수 적용방법을 제시하였으며, 중량계수 및 회전면 하중, 블레이드 개수, 블레이드 종횡비와 같은 주요 매개변수에 대한 민감도 분석과 연관관계에 대해 고찰하였다. 연구 결과, 설계 시 변수에 대한 연관관계 및 민감도의 양을 고려하여 설계 할 헬기 특성을 최적화해야하며, 주요 매개변수들 사이에는 복합적인 연관관계가 존재하므로 설계 시 설계자는 설계 인자들에 대한 신중한 고려가 필요한 것으로 분석되었다.

• 한국군사과학기술학회지
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• 제16권6호
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• pp.779-788
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• 2013

The load requirements should be known to design mechanical structure. This paper proposes a generation method of load requirements using U.S. military specification to design the external mounting structure of the helicopters of which the flight environments such as aerodynamic forces and inertia forces are unknown. In this study, the load requirements which were applied at the design of the pod structure for helicopter captive flight test could be computed by using this method. The validation of proposed method was confirmed from the test flight using developed pod system.

• 한국정보통신학회:학술대회논문집
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• 한국해양정보통신학회 2006년도 춘계종합학술대회
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• pp.139-142
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• 2006

Numerous simulation studies and researches have recently revealed the rapid development and evolution in the emerging area of intelligent unmanned aerial vehicle (UAV). This study aims to develop a flight performance evaluation about the wireless unmanned helicopter. The process includes the design and testing of flight hardware and software that interprets sensor data. For the unmanned helicopter used in this research, an inertial sensor that provides posture (roll, pitch and yaw angles) and a Bluetooth is used to provide wireless connection between the user's pc and the helicopter were installed in the helicopter the helicopter's pitch, roll and yaw were the communication data. The accuracy of the system was confirmed by a computer simulation. The software also has been developed to support operators and displays helicopter position and posture by graphics.

• 대한기계학회논문집B
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• 제26권1호
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• pp.55-65
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• 2002

In this study, the procedures for the preliminary design of the turbo-shaft engine for the light multi-purpose helicopter are established. The engine specifications are determined through the performance analysis on the on-design and off-design conditions by the use of simulation program. In addition, the effect of humidity on the engine performance is examined by considering the change of the gas properties and characteristic maps due to moisture contents. The calculation results show that the engine power is reduced by the existence of moisture in working fluid.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2005년도 ICCAS
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• pp.265-270
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• 2005

This paper presents a new attitude stabilization and control of an unmanned helicopter based on neural network compensation. A systematic derivation on the dynamics of an unmanned small-scale helicopter is performed. Combined rotor-fuselage-tail dynamics is derived in body-fixed reference frame with its origin at the C.G. of the helicopter. And the resulting nonlinear equation of motion consists of 6-DOF air vehicle dynamics as well as the rotor flapping and engine torque equations. A simulation model was modified using the existing simulator for an unmanned helicopter dynamic model, which reflects the unmanned test helicopter(CNUHELI). The dynamic response of the refined model was compared with the flight test data. It can be shown that a good coincidence was accomplished between the real unmanned helicopter system and the mathematical model. This dynamic model was linearized for classical controller design using small perturbation method. A Neuro-PD control system was designed for both longitudinal and lateral flight modes, and the results were compared with the PD-only control response. Simulation results show that the proposed Neuro-PD control system demonstrates better performance.

• 한국화재소방학회:학술대회논문집
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• 한국화재소방학회 2008년도 추계학술논문발표회 논문집
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• pp.105-110
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• 2008

Unmanned helicopter has several abilities such as vertical take off, hovering, low speed flight at a specific altitude. Such vehicles are becoming popular in actual applications such as search and rescue, aerial reconnaissance and surveillance in the case of a large size disaster and forest fire. In this paper, a flight control system was designed for an unmanned helicopter. This paper was concentrated on describing the systematic design, electronic equipments and their interconnections for realizing the autonomous flight and aerial monitoring. A study on the autonomous waypoint navigation and altitude control performance were performed and tested on a test unmanned helicopter and the performance and the feasibility were represented.

• 한국복합재료학회:학술대회논문집
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• 한국복합재료학회 2002년도 추계학술발표대회 논문집
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• pp.220-223
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• 2002

This paper introduces the development procedure of paddle type small-scaled composite rotor blade for helicopter hingeless rotor system. Paddle type composite blade design was done by using CORDAS program developed by KARI and dynamic analysis for hingeless hub with blade is done by using FLIGHTLAB which is commercial software for helicopter comprehensive analysis. The procedure to manufacture complicated shape of paddle type blade tip was developed and composite blades were manufactured after establishing the effective curing method. Through this research, the development technology of composite rotor blade with complex aerodynamic shape were accumulated and these will be applied to the related research field, for example, full size composite blade development, etc.

• 한국복합재료학회:학술대회논문집
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• 한국복합재료학회 2003년도 춘계학술발표대회 논문집
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• pp.57-60
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• 2003

This Paper contains the development procedure of Mach small-scaled composite rotor blade for helicopter articulated rotor system. This mach small-scaled composite blade design is conducted by using CORDAS program developed by KARI. The Dynamic analysis for an articulated rotor system with this blade is conducted by using FLIGHTLAB which is commercial software for helicopter analysis. Also the optimizing procedure of iterative design was described. The designed composite blades were manufactured after establishing the effective curing method. For small-scaled rotor test, strain gauges were embedded in composite blade spar to obtain bending & torsion strain value. To verify sectional properties of a blade, the bench test is accomplished. After comparing a designed data and tested data, Dynamic Calculation was repeated using tested data. Through this research, experiences of mach small-scaled composite blade development were accumulated and will be applied to the related research field.

• 한국소성가공학회:학술대회논문집
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• 한국소성가공학회 2008년도 춘계학술대회 논문집
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• pp.551-554
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• 2008

In the recent year, Unmanned helicopters of airline industries are using in various industries such as monitoring system, agriculture and forest fire. A unmanned helicopter is needed a powerful engine for transport weighty payload and have to need a light weight. Therefore it is necessary a light weight transmission of the unmanned helicopter. Initially a rectangular transmission housing has been considered, but an empty space in the housing is not useful for light weight design. In this study, new model has been introduced into the transmission housing by using rapid prototyping. As a result, the weight of new transmission housing can be reduced very much as 67%.