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

• 한국항공우주학회지
• /
• 제41권6호
• /
• pp.488-494
• /
• 2013

전자식 비행제어시스템(Fly-By-Wire Flight Control System)에 적용되는 헬리콥터의 제어법칙 설계 및 해석은 모델기반 설계기법(Model Based Design)을 사용하여 개발되고 있다. 모델기반 설계기법은 회전익뿐만 아니라 고정익, 무인항공기, 자동차 산업에서도 널리 사용되고 있다. 모델기반 설계기법은 핵심기술인 시뮬레이션과 자동생성코드를 이용하여 개발기간 단축 및 개발리스크 감소라는 장점을 제공한다. 본 논문에서는 FBW 헬리콥터 비행제어법칙의 자동생성코드에 대해서 체계적인 기능검증을 위한 프로세스를 개발하였다. 그리고 지식경제부 과제로 진행하고 있는 FBW 헬리콥터 개발에 적용하여 비행제어법칙 자동생성코드의 기능 검증을 수행 결과, 요구 조건을 충족하는 것으로 확인할 수 있었다.

• 제어로봇시스템학회논문지
• /
• 제11권3호
• /
• pp.207-213
• /
• 2005

This paper deals with an autonomous flight guidance and control algorithm design for TR301 tilt-rotor airplane under development by Korea Aerospace Research Institute for simulation purpose. The objective of this study is to design autonomous flight algorithm in which the tilt-rotor airplane should follow the given waypoints precisely. The approach to this objective in this study is that, first of all, model-based inversion is applied to the highly nonlinear tilt-rotor dynamics, where the tilt-rotor airplane is assumed to fly at helicopter flight mode(nacelle angle=0 deg), and then the control algorithm, based on classical control, is designed to satisfy overall system stabilization and precise waypoint following performance. Especially, model uncertainties due to the tiltrotor model itself and inversion process are adaptively compensated in a simple neural network(Sigma-Phi NN) for performance robustness. The designed algorithm is evaluated in the tilt-rotor nonlinear airplane in helicopter flight mode to analyze the following performance for given waypoints. The simulation results show that the waypoint following responses for this algorithm are satisfactory, and control input responses are within control limits without saturation.

• 한국항공우주학회지
• /
• 제33권9호
• /
• pp.9-15
• /
• 2005

국방과학연구소 풍동실험실에서는 회전익 항공기 개발에 소요되는 관련 풍동시험 기법의 확립과 형상연구 관련 시험자료의 확보를 위한 실험적 연구를 수행하였다. 본 연구는 회전익 항공기 동체구성품의 형상조합에 따른 항력증분과 안정성 평가를 위한 공기역학적 특성의 추출을 목적으로 하였으며, 풍동시험에는 모듈화된 1:8 축척의 회전익 항공기 동체형상과 500 rpm으로 회전하는 로터허브의 부분모형이 사용되었다. 시험결과들을 기존의 유사 항공기 시험결과들과 비교하였으며, 기존 연구결과들과 잘 부합됨을 확인하였다.

• Advances in aircraft and spacecraft science
• /
• 제6권1호
• /
• pp.31-49
• /
• 2019

Flutter is a dangerous phenomenon encountered in flexible structures subjected to aerodynamic forces. This includes aircraft, helicopter blades, engine rotors, buildings and bridges. Flutter occurs as a result of interactions between aerodynamic, stiffness and inertia forces on a structure. The conventional method for designing a rotor blade to be free from flutter instability throughout the helicopter's flight regime is to design the blade so that the aerodynamic center (AC), elastic axis (EA) and center of gravity (CG) are coincident and located at the quarter-chord. While this assures freedom from flutter, it adds constraints on rotor blade design which are not usually followed in fixed wing design. Periodic Structures have been in the focus of research for their useful characteristics and ability to attenuate vibration in frequency bands called "stop-bands". A periodic structure consists of cells which differ in material or geometry. As vibration waves travel along the structure and face the cell boundaries, some waves pass and some are reflected back, which may cause destructive interference with the succeeding waves. In this work, we analyze the flutter characteristics of a helicopter blades with a periodic change in their sandwich material using a finite element structural model. Results shows great improvements in the flutter forward speed of the rotating blade obtained by using periodic design and increasing the number of periodic cells.

• 한국가족관계학회지
• /
• 제22권2호
• /
• pp.3-25
• /
• 2017

Objective: The purpose of this study was to examine the reliability and validity of the Korean version of the Helicopter Parenting Scale (HPS) using a sample of Korean young adults aged 19-34. This study is to expand the previous validation studies that exclusively focused on college students. Method: The survey data came from 1,140 young adults (398 19-24 year olds, 376 25-29 year olds, and 366 30-34 year olds) who had never been married and had at least one living parent. The young adults' perceived helicopter parenting was assessed by 10 items of the HPS for the mother and the father separately. All of the analyses including exploratory and confirmatory factor analyses were conducted for three age groups (19-24, 25-29, and 30-34 years) and for the mother and the father separately. Results: We found that three items were problematic for all age groups and for both the fathers' and mothers' helicopter parenting. After removing these three items, confirmatory factor analyses showed that the one-factor model fit our data well and the estimated factor loadings were suitable. The results were consistent throughout the age groups and the parent's gender. We also confirmed criterion-related validity using correlations between paternal and maternal helicopter parenting and three dimensions of parental career expectations indicated a reliable. Conclusion: The Korean version of HPS with seven items was found to be a reliable and valid measure for Korean young adults aged 19-34 years old.

• 시스템엔지니어링학술지
• /
• 제11권2호
• /
• pp.75-83
• /
• 2015

This paper describes modeling & simulation(M&S) model for dynamic analysis of helicopter rotor blades. Simulation model is developed using Dymola tool which implements the open source language - Modelica. Modelica is appropriate for developing multibody dynamic analysis model. To develop an M&S model efficiently, model based systems engineering(MBSE) is applied. Some diagrams such as requirement diagram, block definition diagram and sequence diagram etc. are drawn to capture the concept of M&S model. This activity is done utilizing the open source tool - Papyrus.

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

• 한국항공우주학회지
• /
• 제48권3호
• /
• pp.217-224
• /
• 2020

고-대역폭(High Bandwidth)의 헬리콥터 반응특성을 위한 높은 수준의 피드백 제어 게인의 사용은 로터 모드에 의해 항공기의 불안정성이 증가한다. 본 논문에서는 EC155B1 헬리콥터 모델링을 수행하고 이를 이용하여 롤 축의 각속도 및 자세 피드백 게인의 증가에 따른 항공기의 안정성을 분석하였다. 그리고 로터 플랩 모드에 의해 제한되는 롤 축 각속도 및 자세 피드백 제어 게인을 검토하였다. 또한 노이즈 제거 필터의 사용으로 비행 제어시스템의 위상지연이 증가 시 헬리콥터 안정성에 영향을 주는 피드백 제어 게인의 한계를 검토하였다.

• Smart Structures and Systems
• /
• 제18권1호
• /
• pp.1-16
• /
• 2016

Model Order Reduction (MOR) denotes the theory by which one tries to catch a model of order lower than that of the real model. This is conveniently pursued in view of the design of an efficient structural control scheme, just passive within this paper. When the nonlinear response of the reference structural system affects the nature of the reduced model, making it dependent on the visited subset of the input-output space, standard MOR techniques do not apply. The mathematical theory offers some specific alternatives, which however involve a degree of sophistication unjustified in the presence of a few localized nonlinearities. This paper suggests applying standard MOR to the linear parts of the structural system, the interface remaining the original unreduced nonlinear components. A case study focused on the effects of a helicopter land crash is used to exemplify the proposal.