헬리콥터 무베어링 허브시스템의 사례분석을 통한 상쇄 연구

김덕관,김민환,김태주,윤철용,기영중,김승호 한국항공우주학회 2011 한국항공우주학회 학술발표회 논문집 Vol.2011 No.4

본 논문에서는 헬리콥터 허브 시스템 중의 하나인 무베어링 허브시스템의 기술 현황을 기술하고 기존개발 사례 분석을 통해 현재 개발업무가 진행되고 있는 무베어링 허브시스템의 상쇄 연구결과를 제시하였다. 먼저 무베어링 허브시스템의 장단점을 기술하였다. 다음으로 무베어링 허브의 다양한 유연보 단면형상 개념의 발전추세를 기존 개발 사례 분석을 통해 기술하였으며, 마지막으로 현재 진행되고 있는 무베어링 허브시스템의 상쇄연구 결과를 제시하였다. 상쇄연구결과, 분리형과 교차형 허브의 2가지 허브형상을 선정하였으며, 각 형상별로 허브시스템의 부품수 및 중량 등을 예측하였다. 또한 유연보 형상은 직사각형 단면 형상과 Double H 형상 구조의 2가지 형상을 선정하였다. In this paper, it was described the current technology status of bearingless rotor hub system for helicopter which is one of major rotor hub system. Also, a trade-off study on the new bearingless rotor hub system of helicopter through the investigation of the previous existing bearingless hub system was described. First, the advantages and disadvantages of major helicopter rotor hub system are described in comparison to each other types of rotor hub system. The current status of flexbeam section geometry of bearingless rotor hub system are described. Next, the current result of trade-off study of bearingless rotor hub system are described. This trade-off study shows that double-H sectional construction and rectangular construction of flexbeam are candidates of the new bearingless rotor system. Also it shows that separate type and cross-strap type of hub systems are chosen as a candidate of bearingless hub system.

헬리콥터 무베어링 로터 허브시스템의 개념 연구

김덕관(Deog-Kwan Kim),김민환(Min-Hwan Kim),윤철용(Chul Yong Yun),김태주(Taejoo Kim),김승호(Seungho Kim) 한국소음진동공학회 2011 한국소음진동공학회 학술대회논문집 Vol.2011 No.4

In this paper, it was described the current technology status of bearingless rotor hub system for helicopter which is one of major rotor hub system. Also, a conceptual study on the new bearingless rotor hub system of helicopter was described. First, the advantages and disadvantages of major helicopter rotor hub system are described in comparison to each other types of rotor hub system. The unique characteristics of bearingless rotor hub system are described compared to other types of rotor hub systems. Next, the main function, role and characteristics of the sub-components of bearingless rotor hub system are described. Recent helicopters which adopt this bearingless rotor hub system are described and introduced. This conceptual study shows that double-H sectional construction and rectangular construction of flexbeam are the most effective candidates of this new bearingless rotor system. This bearingless rotor hub system can be used for 7,000lbs class helicopter. Now, a further trade-off study will show.

덕트형상에 따른 동축반전 로터블레이드 주위의 전산유동해석

김수연(Suyean Kim),최종욱(Jongwook Choi),김성초(Sungcho Kim) 한국가시화정보학회 2010 한국가시화정보학회지 Vol.8 No.2

Regarding the aircrafts with a rotor blade system, the miniaturization of them is limited due to the rotor blade length and the tail rotor system. To miniaturize an aircraft, an equipment is required that increases thrust and also shortens the length of the rotor blade. The present study will conduct the flow analysis for miniaturizing the aircraft by applying a duct to the coaxial rotor blade system without tail rotor. First, the verification on the calculated results was conducted through the computational flow analysis on the coaxial rotor blade system without a duct. Then, the flow analysis for the coaxial rotor blade systems was performed including Ka-60 duct, Single duct, Twin duct, and Double duct, respectively. From the numerical results, the thrust coefficient appeared higher with the duct than without a duct for the coaxial rotor blade system. Especially, in the case of Double duct, the thrust was improved due to the increase of incoming flow and the extension of the wake area. These results will be used as the basic concepts for miniaturizing the aircraft with the rotor blade system. The flow analysis on the coaxial rotor blade system including the fuselage remains as a future work.

헬리콥터 무베어링 로터 허브 시스템 기술동향

송근웅(Song Keun-Woong),김승범(Kim Seung-Bum),김승호(Kim Seung-Ho),김덕관(Kim Deog-Kwan),윤철용(Yun Cheol-Yong) 한국항공우주연구원 2010 항공우주산업기술동향 Vol.8 No.1

본 논문에서는 헬리콥터 로터 허브 시스템 중 최신의 기술이 적용된 무베어링 허브 시스템에 대하여 적용된 기술에 대한 동향을 기술하였다. 먼저 헬리콥터 로터 허브시스템의 형태별 장단점을 분석하였으며, 무베어링 로터 허브 시스템이 타 허브 시스템에 비하여 갖는 고유의 특징에 대하여 기술하였다. 다음으로 무베어링 로터 허브 시스템의 주요 구성품에 대한 기능 및 역할, 특성에 대하여 기술하였다. 나아가 무베어링 로터 허브를 적용하고 있는 기 개발된 헬리콥터들의 사례에 대하여 기술하였다. In this paper, it is described the current technology status of bearingless rotor hub system for helicopter which is one of major rotor hub system. First, the advantages and disadvantages of major helicopter rotor hub system are described and compared each other. The unique characteristics of bearingless rotor hub system are described compared to other types of rotor hub systems. Next, the main function, role and characteristics of the sub-components of bearingless rotor hub system are described. Furtherly, recent helicopters which adopt this bearingless rotor hub system are described and introduced.

헬리콥터 반 토크 시스템의 피치제어기 설계 및 성능 시험 평가

안경민(Kyoung Min Ahn),김승범(Seung Bum Kim),송근웅(Keun woong Song),김승호(Seung Ho Kim),주진(Joo Jin) 대한기계학회 2007 대한기계학회 춘추학술대회 Vol.2007 No.10

The Helicopter Anti-torque System, namely Tail Rotor System is generated a horizontal force to counterbalance with a torque from the main rotor system. It is required that the initial design of Tail rotor should have a thrust margin of 10% to a direction control ability after counterbalance with a torque from the main rotor system when the maximum power rise. At this time, Pitch Control System is enable to a direction control ability at the tail rotor System. This paper introduces the design of pitch control system and manufacture and carry out a experimental performance test at the real size scale of Tail rotor system.

능동거니플랩 축소 로터 시스템의 동특성 해석

임규백,기영중,김덕관 한국항공우주학회 2015 한국항공우주학회 학술발표회 논문집 Vol.2015 No.11

본 논문에서는 헬리콥터 로터 시스템의 진동과 소음을 저감시키기 위해 개발이 진행 중인 능동 거니플랩(AGF)의 회전시험을 수행하기 위한 로터 시스템에 대하여 유한요소법을 이용한 동특성 해석결과를 검토하였다. 이 축소로터 시스템은 에어포일 단면 형상이 NACA23012인 2개의 더미블레이드를 이용하여 회전반경 2.3m인 축소로터 시스템을 구성하였다. 능동거니플랩과 로터 시스템에 대한 유한요소 모델은 상용 프로그램인 Midas –NFX를 이용하였다. 본 연구에서는 비회전 상태에서의 모드 해석 결과와 모달 시험을 통한 고유진동수를 비교하여 해석모델의 적절성을 확인하였다. 또한 검증된 유한요소 모델을 이용하여 축소로터 시스템 지상시험에 앞서 운용 회전수에 대한 공진 발생여부를 검토 하였다. In the present study, a finite element analysis is carried out to investigate the dynamic characteristics of a small-scaled rotor system with active Gurney flap (AGF) in a rotating condition to reduce the vibration and noise of the helicopter rotor system. The small-scaled rotor system consists of two hingeless rotor blades with 2.3 m diameter and NACA 23012 airfoil section. The finite element model of the rotor system with AGF is prepared using a commercial software called Midas-NFX. In order to validate the analysis procedures, modal analysis results of the rotor system obtained using Midas-NFX are compared with the experimentally measured natural frequencies and mode shapes. In addition, the resonance phenomenon for the small-scaled rotor system is confirmed to be present before the operating speed using the verified finite element model.

Design, Control, and Implementation of Small Quad-Rotor System Under Practical Limitation of Cost Effectiveness

Seungho Jeong,Seul Jung 한국지능시스템학회 2013 INTERNATIONAL JOURNAL of FUZZY LOGIC and INTELLIGE Vol.13 No.4

This article presents the design, control, and implementation of a small quad-rotor system under the practical limitation of being cost effective for private use, such as in the cases of control education or hobbies involving radio-controlled systems. Several practical problems associated with implementing a small quad-rotor system had to be taken into account to satisfy this cost constraint. First, the size was reduced to attain better maneuverability. Second, the main control hardware was limited to an 8-bit processor such as an AVR to reduce cost. Third, the algorithms related to the control and sensing tasks were optimized to be within the computational capabilities of the available processor within one sampling time. A small quad-rotor system was ultimately implemented after satisfying all of the above practical limitations. Experimental studies were conducted to confirm the control performance and the operational abilities of the system.

Development of the Support System for Manual Operations of a Multi-rotor Helicopter

Masanori Tsuzaki,Takashi Takimoto 제어로봇시스템학회 2013 제어로봇시스템학회 국제학술대회 논문집 Vol.2013 No.10

In this paper, we consider an operator support system for a class of manual control systems that a human operator manually control a multi-rotor helicopter. The multi-rotor helicopter is used in environmental observations, pesticide applications, disaster damage tracking systems, and so on. However, skillful techniques are required for operations of the multi-rotor helicopter. In fact, serious accidents are caused by human errors. In order to prevent serious accidents, it is important to detect any symptoms of the human error in real time. In this paper, we have proposed a human error detection method and an operator support system which alert the human operator to abnormal operations. The proposed support system is based on the identification method for a smallest model set which are consistent with the input and output data of the manual control system.

Design and Control of a Small Quad-rotor System under Practical Limitations

Seung Ho Jeong,Seul Jung 제어로봇시스템학회 2011 제어로봇시스템학회 국제학술대회 논문집 Vol.2011 No.10

This paper presents design and control of a small quad-rotor system for control education. Our goal is to develop a low cost quad-rotor system that is affordable for public use such as education or RC hobby. Based on experiences gained from the previous Flymobile system that has capabilities of both flying and driving, a new quad-rotor system is designed to fit practical cost. Several limitations on implementing a quad-rotor system are taken into account to reduce the cost. Firstly, the size is reduced to have the better maneuverability. Secondly, control hardware is limited to an 8 bit processor such as an AVR to reduce the cost as well. Thirdly, algorithms related with control and sensing tasks are required to be shortened in order to minimize the calculation time to fit the sampling time for the available processor. A small quad-rotor system is implemented after satisfying all the practical limitations. Experimental studies are conducted to confirm control and operational abilities of the system.

팁제트 로터의 성능/구조 해석에 관한 연구

백상민,권혁준 한국항공우주학회 2015 한국항공우주학회 학술발표회 논문집 Vol.2015 No.11

로터는 블레이드를 고속으로 회전시켜 추력을 얻는 시스템으로써, 블레이드를 비롯하여 다양한 부품들이 복잡하게 구성되어 있다. 이러한 구조의 복잡성으로 인하여 로터는 운용 중 과도한 진동, 공탄성적 불안정성 등을 겪게 되어, 포괄적인 해석을 필요로 한다. 팁제트 로터는 중앙의 엔진으로부터 배기가스 또는 압축공기를 로터 블레이드 내부에 삽입된 덕트를 통해 유입하고, 블레이드 팁의 노즐에서 분사시켜 발생하는 회전력으로 로터의 추력을 얻게 된다. 이 경우, 동력전달장치가 필요하지 않으므로 회전익기 설계 시 반 토크장치가 필요 없다는 장점이 있다. 본 연구에서는 CAMRAD Ⅱ를 이용하여 팁제트로터의 성능 및 구조 해석에 관한 연구를 다루었다. 이를 활용하여 기존의 로터시스템의 해석 결과와 비교하였다. Rotor gets thrust from high speed rotating blades. There are many components to construct complicated rotor system. Rotor system needs comprehensive analysis because these complex rotor structures cause excessive vibration and aeroelastic instability in rotating condition. In case of a tip-jet driven rotor, the compressed air or the combustion gas passes through a duct that is inserted in rotor blade. The nozzle at blade tip jets out the gas to produce the enough torque for rotating blades, then the thrust is obtained. At that cases, the rotorcraft doesn’t have power transmission equipment. Therefore anti-torque system may not be needed and driven system has a considerably simpler construction. In this paper, performance and structural analysis of tip-jet rotor are studied using CAMRADⅡand compared with analysis of conventional rotor system.