• 대한인간공학회지
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• 제27권4호
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• pp.37-44
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• 2008

To design the cockpit of Korean helicopter, anthropometric data for Korean helicopter pilots as a target population is necessary. The present study measured the body sizes of Korean helicopter pilots to design the cockpit of Korean helicopter, and compared the measurements with those of Korean civilian and the US Army. The sample size was 100 which determined by a statistical analysis. Anthropometric measurements were collected for 100 samples (male = 94, female = 6; age group = 20~40) of Korean helicopter pilots by applying standard measurement protocol. To compare three anthropometric data, Korean civilian and US Army data were controlled by considering age group (20~40) and gender ratio (male: female = 9:1) of Korean helicopter pilots. The average body sizes of Korean helicopter pilots were mostly similar to those of Korean civilian, however, lower limb related variables (hip breadth, popliteal height and thigh clearance) and shoulder-to-elbow length were significantly greater (1~7%) at α=0.05. Furthermore, the average body sizes for Korean helicopter pilots regarding lower limb length and thickness were significantly smaller than those of the US Army (1~12%); however, the average body sizes for Korean helicopter pilots regarding upper body related variables (sitting height, sitting eye height, and acromial height) and hip breadth were significantly greater (0.7~1.9%). Lastly, size variability for Korean helicopter pilots was significantly smaller than those of Korean civilian and the US Army. Anthropometric data for Korean helicopter pilots of the present study was applied to design and evaluate a Korean helicopter cockpit.

• 대한인간공학회지
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• 제29권2호
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• pp.203-210
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• 2010

For the development of a better product which fits to the target user population, physical workloads such as reach and visibility are evaluated using digital human simulation in the early stage of product development; however, ergonomic workload assessment mainly relies on visual observation of reach envelopes and view cones generated in a 3D graphic environment. The present study developed a quantitative assessment method of physical workload in a digital environment and applied to the evaluation of a Korean utility helicopter (KUH) cockpit design. The proposed assessment method quantified physical workloads for the target user population by applying a 3-step process and identified design features requiring improvement based on the quantified workload evaluation. The scores of physical workloads were quantified in terms of posture, reach, visibility, and clearance, and 5-point scales were defined for the evaluation measures by referring to existing studies. The postures of digital humanoids for a given task were estimated to have the minimal score of postural workload by finding all feasible postures that satisfy task constraints such as a contact between the tip of the index finger and a target point. The proposed assessment method was applied to evaluate the KUH cockpit design in the preliminary design stage and identified design features requiring improvement. The proposed assessment method can be utilized to ergonomic evaluation of product designs using digital human simulation.

• 한국항공우주학회지
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• 제41권12호
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• pp.987-993
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• 2013

한국형기동헬기(KUH)는 국내 최초로 개발된 헬기로서, 2010년 3월 초도 비행을 시작으로 2012년 6월 체계 개발을 성공적으로 종료하였다. 비행시험 단계에서 다양한 진동문제가 발생하였으며 이를 제어하기 위해 적절한 진동저감장치를 설계하고 적용하였다. 한국형 기동헬기의 주요 진동 성분인 $4{\Omega}$ 주파수 진동 저감을 위해 주로터 블레이드, 주기어박스 지지부, 조종실, 승객실 그리고 조종좌석에 진동저감장치를 적용하였다. 또한, 테일-쉐이크 진동 제어를 위해 돔페어링을 적용하였다. 본 논문에서는 한국형 기동헬기에 적용된 진동저감장치들의 해석 및 설계 기법과 비행시험 결과를 제시한다.

• 한국항공우주학회지
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• 제38권8호
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• pp.813-822
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• 2010

안전성 요구수준이 서로 다른 비행필수 데이터(Flight Critical Data)와 임무필수 데이터(Mission Critical Data)의 시현을 처리하기 위해 별도의 독립된 계기를 사용하지 않고 Glass Cockpit 설계를 적용하여 데이터를 통합처리하였다. 본 논문에서는 독립적으로 설계 진행되어온 비행조종계통과 임무탑재시스템의 통합설계를 위해 설계변경을 최소화하면서 비행조종계통에서 요구되는 비행필수 데이터처리의 안전성 요구수준을 만족시키는 최적화 설계를 제안하였다. 비행필수 데이터의 시현을 처리하기 위해 KUH 임무탑재시스템의 핵심구성품인 임무컴퓨터(Mission Computer)의 하드웨어 및 소프트웨어 설계변경을 최소화하였다. 임무탑재시스템의 안전성 요구도(Safety Requirement)를 검증하기 위한 시험절차를 개발하여 임무탑재시스템 통합시험장비(SIL)를 이용한 시험 수행 결과 안전성 요구도가 만족됨을 확인하였다.

• 품질경영학회지
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• 제43권3호
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• pp.341-358
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• 2015

Purpose: This paper presents graphic methods and desirability function approach to determine best vibration reducing configuration for Surion helicopter. Many flight tests were executed and nine vibration levels in cockpit, cabin, and engine room were measured in each test and analyzed to find optimal configuration. Methods: Graphic analysis methods such as matrix, scatter, and box plots are used to identify better vibration-reducing flight test conditions. As an integrated measure of the performance of 9 vibration levels desirability function approach is adopted. Results: Three vibration reducing configurations are found to be proper and one configuration is recommended. Conclusion: It is expected to be helpful to adopt graphic and desirability function methods presented in this paper in developing new products or systems like helicopters. For efficient and effective flight testing of helicopters, it will be necessary to have consistently homogeneous environment for flight testing and applying design of experiments techniques and analyzing test data.

• 한국항공우주학회지
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• 제31권4호
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• pp.99-104
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• 2003

본 논문은 헬리콥터 로터 시스템 설계시 고려해야 할 구조동역학 분야와 차세대 저진동 블레이드를 설계하는 과정을 소개하였다. 일반적으로 로터 시스템 설계시 허브 하중 최소화, 지상공진 방지 및 저진동 특성 등을 만족하도록 고유 진동수 범위를 정하게 된다. 먼저 로터 시스템에 대한 회전수별 고유 진동수 도표를 통해 로터 회전 속도와 공진영역이 생기지 않도록 설계하며 다음으로 동체에 전달되는 진동 하중 크기를 예측하기 위해 회전시 블레이드에서 발생되는 하중을 허브 중심의 비회전계 좌표축 성분으로 전환한다. 헬리콥터 전진 비행속도에 따라 동체에 전달되는 하중 크기를 구하고 동체를 강체로 모델링하여 조종속에서 발생되는 가속도를 계산함으로써 저진동 특성을 예측하였다. 본 설계기법은 현재 수행중인 차세대 로터 시스템 개발에 적용되고 있으며 향후 국내 개발 로터 시스템에 유용하게 적용될 것이다.