• International Journal of Aeronautical and Space Sciences
• /
• 제17권1호
• /
• pp.132-138
• /
• 2016

Korea Aerospace Research Institute (KARI) is developing an electric-driven HALE UAV in order to secure system and operational technologies since 2010. Based on the flight tests and design experiences of the previously developed electric-driven UAVs, KARI has designed EAV-3, a solar-powered HALE UAV. EAV-3 weighs 53kg, the structure weight is 22kg, and features a flexible wing of 19.5m in span with the aspect ratio of 17.4. Designing the main wing and empennage of the EAV-3 the amount of the bending due to the flexible wing, 404mm at 1-G flight condition based on T-800 composite material, and side wind effects due to low cruise speed, $V_{cr}=6m/sec$, are carefully considered. Also, unlike the general aircraft there is no center of gravity shift during the flight because of the EAV-3 is the solar-electric driven UAV. Thus, static margin cuts down to 28.4% and center of gravity moves back to 31% of the Mean Aerodynamic Chord (MAC) comparing with the previously designed the EAV-2 and EAV-2H/2H+ to upgrade the flight performance of the EAV-3.

• International Journal of Aeronautical and Space Sciences
• /
• 제12권2호
• /
• pp.134-148
• /
• 2011

In general, forces acting on aerospace structures can be divided into two categories-a) conservative forces and b) nonconservative forces. Aeroelastic effects occur due to highly flexible nature of the structure, coupled with the unsteady aerodynamic forces, causing unbounded static deflection (divergence) and dynamic oscillations (flutter). Flexible wing panels subjected to jet thrust and missile type of structures under end rocket thrust are nonconservative systems. Here the structural elements are subjected to follower kind of forces; as the end thrust follow the deformed shape of the flexible structure. When a structure is under a constant follower force whose direction changes according to the deformation of the structure, it may undergo static instability (divergence) where transverse natural frequencies merge into zero and dynamic instability (flutter), where two natural frequencies coincide with each other resulting in the amplitude of vibration growing without bound. However, when the follower forces are pulsating in nature, another kind of dynamic instability is also seen. If certain conditions are satisfied between the driving frequency and the transverse natural frequency, then dynamic instability called 'parametric resonance' occurs and the amplitude of transverse vibration increases without bound. The present review paper will discuss the aeroelastic behaviour of aerospace structures under nonconservative forces.

• 한국항공우주학회지
• /
• 제36권10호
• /
• pp.1032-1037
• /
• 2008

항공기의 기체 생존성에 있어서 연료탱크는 중요한 부분이다. 회전익 항공기의 연료탱크는 자기 밀폐성과 내충돌성의 기능을 필요로 한다. 이에 따라 고기능유연연료탱크를 필요로한다. 이 논문에서는 상용 소프트웨어인 MSC.DYTRAN을 이용하여 연료탱크의 낙하시험을 시뮬레이션 하였다. 연료탱크 낙하 시험 시 시험 큐브의 파손 없이 내충돌성 요구조건을 만족하는지 알아보았다.

• 한국항공우주학회지
• /
• 제37권9호
• /
• pp.837-842
• /
• 2009

구성 모드(Component mode) 합성법을 이용하여, 태양전지판의 유연구조 진동특성을 고려한 위성의 축약된 동적 모델링 기법을 수립하였다. 유연구조 위성의 본체와 태양전지판을 서로 다른 두 개의 부구조물로 나누고, 각각의 국부좌표계에 대하여 유도된 부구조물 표현식들을 위성 전체의 기준좌표계에 대해서 합성하였다. 수립된 부구조물 합성법은 단일 태양전지판을 갖는 유연구조 위성의 수치적 예제에 적용되었으며, 태양전지판의 회전을 고려한 전달함수 결과의 고찰을 통하여 동적 모델링 기법의 타당성을 확인하였다.

• Journal of Astronomy and Space Sciences
• /
• 제14권2호
• /
• pp.386-394
• /
• 1997

본 연구에서는 유연모드를 고려한 위성체 모델링 방법들을 소개하고, 이에 따라 3축 안정화 위성의 유연모드를 모델링하였다. 이 모델을 강체에 대해 설계되었던 반작용휠을 이용한 자세제어루프에 적용하였다. 본 연구에서는 유한요소모델이 완성되기 전 단계에서 집합모드모델 중 전역모드모델을 이용하는 것을 제안하였고, 이를 유한요소법을 이용하여 계산된 모델과 제어기 필터 설계의 관점에서 비교하였다. 새로운 유연모드가 적용됨에 따라 제어기 요구조건을 만족시키기 위한 필터가 필요하여 반작용휠의 모터제어기 루프와 축제어기 루프에 각각 1차 필터를 설계하여 추가하였다. 제어루프 설계 및 시뮬레이션을 위해 MATLAB/Simulink를 사용하였다.

• International Journal of Aeronautical and Space Sciences
• /
• 제17권2호
• /
• pp.184-194
• /
• 2016

In existing identification methods for on-orbit spacecraft, such as eigensystem realization algorithm (ERA) and subspace method identification (SMI), singular value decomposition (SVD) is used frequently to estimate the modal parameters. However, these identification methods are often used to process the linear time-invariant system, and there is a lower computation efficiency using the SVD when the system order of spacecraft is high. In this study, to improve the computational efficiency in identifying time-varying modal parameters of large spacecraft, a faster recursive algorithm called fast approximated power iteration (FAPI) is employed. This approach avoids the SVD and can be provided as an alternative spacecraft identification method, and the latest modal parameters obtained can be applied for updating the controller parameters timely (e.g. the self-adaptive control problem). In numerical simulations, two large flexible spacecraft models, the Engineering Test Satellite-VIII (ETS-VIII) and Soil Moisture Active/Passive (SMAP) satellite, are established. The identification results show that this recursive algorithm can obtain the time-varying modal parameters, and the computation time is reduced significantly.

• 한국실내디자인학회:학술대회논문집
• /
• 한국실내디자인학회 2006년도 춘계학술발표대회 논문집
• /
• pp.193-196
• /
• 2006

The storage style has changed because of diversity of family types, improvement of cost of living, and increase of leisure time. In spite of this change, storage space has still caused discomfort since it did not consider residents' convenience. Therefore, in this study, Brand Apartments were selected, furniture detail drawing was analyzed by plan of housing size and zone to calculate storage area and capacity, and finally needs of storage space were analyzed using survey. Satisfaction of storage space was generally low and $20{\sim}30%$ increase of storage space was demanded. The reasons why the storage space was not satisfied are followed. First, storage space was insufficient. Second, the inner structure of storage space was unified. According to change of life style, needs have changed. To satisfy these needs, the inner division of storage space is planned with considering various items. In addition, development of hardware, flexible division, and priority of storage space with considering user's convenience are needed.

• 한국경영과학회지
• /
• 제19권2호
• /
• pp.107-118
• /
• 1994

This research is concerned with production scheduling for a flexible manufacturing cell which consists of two machine centers with unlimited buffer space and a single automatic guided vehicle. The objective is to develop and evaluate heuristic scheduling procedures that minimize maximum completion time. A numerical example illustrates the proposed algorithm. The heuristic algorithm is implemented for various cases by SLAM II. The results show that the proposed algorithm provides better solutions than Johnson's. It also gets good solutions to minimize mean flowtime.

• 한국정보디스플레이학회:학술대회논문집
• /
• 한국정보디스플레이학회 2007년도 7th International Meeting on Information Display 제7권2호
• /
• pp.1119-1120
• /
• 2007

Nano-sized metal patterns were successfully fabricated on flexible PET substrate using nanoimprint lithography. 70nm line and space PMMA resist pattern was formed on PET substrate without residual layer by 'artial filling effect' and 20nm thin Cr metal layer was deposited by e-beam evaporation. Then, PMMA resist was selectively removed by acetone and 70nm narrow Cr pattern was formed.

• 제어로봇시스템학회:학술대회논문집
• /
• 제어로봇시스템학회 1989년도 한국자동제어학술회의논문집; Seoul, Korea; 27-28 Oct. 1989
• /
• pp.600-605
• /
• 1989

A theoretical study is presented for the end-point holding control of a one-link flexible arm, whose base is subjected to a lateral fluctuation. The arm is clamped on a rigid hub mounted directly on the shaft of d.c. servomoter. The tip position is measured by a gap sensor fixed in space isolated from the system vibration. The arm is controlled so as to make the end point stay precisely at its initial position even if the base is fluctuated.