• 한국항공우주학회지
• /
• 제45권5호
• /
• pp.359-366
• /
• 2017

본 논문에서는 가오리 연의 비행 중에 형성되는 모든 받음각 변화를 고려한 풍동 실험을 통해 가오리연의 공력 자료를 구축하였다. 이 공력 자료로부터 가오리연이 받음각 또는 연실-지평각이 변함에 따라 평형 비행 상태를 이루는데 필요한 목줄에 대한 꽁수줄의 상대적 길이를 해석하였다. 해석 결과 목줄에 대한 꽁수줄의 상대적 길이는 연의 시위 길이와 풍속에 전적으로 의존하고 받음각에 따라 모핑 변화하고 있음을 알 수 있었다. 본 자료를 활용하면 비행환경과 연의 자세에 맞게 방줄의 상대길이를 조정할 수 있으며 최적성능을 유지하는 연을 다룰 수 있게 될 것이다.

• 한국항공우주학회지
• /
• 제34권3호
• /
• pp.1-5
• /
• 2006

자연에 존재하는 새나 곤충들은 양력 및 추력을 발생하기 위하여 평균캠버선의 형상을 변화시킨다. 기존의 비정상 박익 이론들은 주로 강체 플랩핑 에어포일에 관하여 유도되어 왔다. 생체형상가변익의 비정상 공력특성을 파악하기 위하여 변형 가능한 에어포일에 대한 확장된 비정상 박익이론이 필요하다. 생체형상가변익의 비정상 공력특성을 계산하기 위해 Theodorsen의 접근방법을 확장하였다. 에어포일의 평균 캠버선은 다항식으로 나타내었다. 형상 가변익에 작용하는 비정상 공력특성을 순환항 및 비순환항으로 나누어 나타내었다. 본 이론은 플래핑운동을 하는 생체형상가변 에어포일의 비정상 공력해석 및 모핑날개의 공탄성 해석에 적용가능하다.

• 한국CDE학회논문집
• /
• 제17권6호
• /
• pp.443-455
• /
• 2012

The configuration of a musculoskeletal (MS) system is closely related to the individual motions of the human body. Many researches have been focused on evaluating the associations between the MS configuration and the individual motion using patient-specific MS models, but it still remains a challenging issue to accurately predict the motion by differed configurations of the MS system. The main objective of this paper is to predict the changes of a patient-specific gait by altering the geometric parameters of the hip joint using function-based morphing method (FBM). FBM is suitable for motion analysis since this method provide a robust way to morph a MS model while preserving the biomechanical functions of the bones. Computed-muscle control technique is used to calculate the muscle excitations to reproduce the targeted motion within a digital MS model without the motion-captured data. We applied this approach to a patient who has an abnormal gait pattern. Results showed that the femoral neck length and the angle significantly affect to the motion especially for the hip abduction angle during gait, and that this approach is suitable for gait prediction.

• International Journal of Aeronautical and Space Sciences
• /
• 제12권4호
• /
• pp.305-317
• /
• 2011

This paper presents an overview on flutter boundary prediction in tests which is principally based on a system stability measure, named Jury's stability criterion, defined in the discrete-time domain, accompanied with the use of autoregressive moving-average (AR-MA) representation of a sampled sequence of wing responses excited by continuous air turbulences. Stability parameters applicable to two-, three- and multi-mode systems, that is, the flutter margin for discrete-time systems derived from Jury's criterion are also described. Actual applications of these measures to flutter tests performed in subsonic, transonic and supersonic wind tunnels, not only stationary flutter tests but also a nonstationary one in which the dynamic pressure increased in a fixed rate, are presented. An extension of the concept of nonstationary process approach to an analysis of flutter prediction of a morphing wing for which the instability takes place during the process of structural morphing will also be mentioned. Another extension of analytical approach to a multi-mode aeroelastic system is presented, too. Comparisons between the prediction based on the digital techniques mentioned above and the traditional damping method are given. A future possible application of the system stability approach to flight test will be finally discussed.

• Advances in aircraft and spacecraft science
• /
• 제10권5호
• /
• pp.419-437
• /
• 2023

This paper presents the study of the effects of rigid-body motion simultaneously with the presence of the effects of temporal variation due to the existence of morphing speed on the aeroelastic stability of the two-stage telescopic wings, and hence this is the main novelty of this study. To this aim, Euler-Bernoulli beam theory is used to model the bending-torsional dynamics of the wing. The aerodynamic loads on the wing in an incompressible flow regime are determined by using Peters' unsteady aerodynamic model. The governing aeroelastic equations are discretized employing a finite element method based on the beam-rod model. The effects of rigid-body motion on the length-based stability of the wing are determined by checking the eigenvalues of system. The obtained results are compared with those available in the literature, and a good agreement is observed. Furthermore, the effects of different parameters of rigid-body such as the mass, radius of gyration, fuselage center of gravity distance from wing elastic axis on the aeroelastic stability are discussed. It is found that some parameters can cause unpredictable changes in the critical length and frequency. Also, paying attention to the fuselage parameters and how they affect stability is very important and will play a significant role in the design.

• 한국산학기술학회논문지
• /
• 제22권5호
• /
• pp.128-135
• /
• 2021

박판관은 충돌안전을 위한 에너지 흡수장치 중의 하나로써 가벼우면서도 에너지 흡수 효율이 좋아 널리 이용되어 왔다. 그러나 일반적인 박판관은 충돌 초기 피크하중(IPCF: Initial Peak Crushing Force)이 높게 유발될 뿐 아니라 반복적으로 나타나는 피크하중으로 인하여 충돌에너지 흡수장치로써의 안정성이 다소 떨어진다는 단점이 있다. 충돌 초기 피크하중을 감소시키고 충돌에너지 흡수장치의 안정성을 키우기 위하여 박판 파형관이 도입되었다. 파형관의 성능은 기하 형상에 큰 영향을 받기 때문에 최적설계 기법을 적용하여 파형관의 성능을 최적화할 수 있다. 본 논문에서는 충돌안전도 해석에 기반한 형상 최적설계를 수행하기 위하여 적응 근사모델(adaptive surrogate model)을 활용한 최적설계 기법을 활용하였다. 파형의 진폭 및 파장 뿐 아니라 형상의 곡률 변화를 설계 변수로써 고려하였다. 형상 설계 매개변수화를 수행하기 위하여 몰핑(morphing) 방법을 채택하였다. 수치 예제를 통해서 적응 근사모델에 기반한 최적설계 결과와 기존 근사모델에 기반한 최적설계 결과를 비교하고 적응 근사모델에 기반한 최적설계 방법이 좀 더 효율적인 결과를 도출함을 보였다.

• 소성∙가공
• /
• 제21권7호
• /
• pp.441-446
• /
• 2012

A sequential coupled field analysis of electromagnetic free bulging was performed by using FEM. A 2D axi-symmetric electromagnetic model based on the magnetic vector potential is proposed for the calculation of magnetic field and Lorentz's forces. The Newmark integration method is used to calculate the transient dynamic plastic deformation of sheet during free bulging. In the finite element model, the effect of sheet deformation on the electromagnetic field analysis is taken into consideration. In order to confirm the sequential electromagnetic-mechanical coupling analysis, an experiment with an electromagnetic forming apparatus was conducted. The results showed that the final bulge height of the sheet predicted from the proposed method is in good agreement with experimentally measured height.

• 한국CDE학회논문집
• /
• 제10권5호
• /
• pp.314-327
• /
• 2005

This paper describes the volumetric data modeling and analysis methods that employ volumetric NURBS or VNURBS that represents heterogeneous objects or fields in multidimensional space. For volumetric data modeling, we formulate the construction algorithms involving the scattered data approximation and the curvilinear grid data interpolation. And then the computational algorithms are presented for the geometric and mathematical analysis of the volume data set with the VNURBS model. Finally, we apply the modeling and analysis methods to various field applications including grid generation, flow visualization, implicit surface modeling, and image morphing. Those application examples verify the usefulness and extensibility of our VNUBRS representation in the context of volume modeling and analysis.

• 대한기계학회논문집A
• /
• 제35권7호
• /
• pp.821-826
• /
• 2011

CAE 기반 구조최적설계법인 위상최적설계와 형상최적설계를 크레인의 경량화에 적용하였다. 붐은 단면 형상을 설계 변수로 변화시키면서 질량의 최소화를 최적설계의 목적함수로 하고 붐의 정적강도와 동적강성이 초기 모델의 성능에 비해서 저하되지 않아야 한다는 제한조건을 설정하였다. 구조해석 및 최적설계는 상용소프트웨어인 Hyperworks를 이용하여 수행하였으며 붐의 단면 형상의 변형에 따르는 요소망의 변동은 모핑 기능을 사용하여 수치 안정성을 확보하였다. 붐의 지지부는 초기 모델을 단순화시킨 설계 영역을 설정하고 이를 삼차원 솔리드 요소로 이산화한 후 위상최적설계를 수행하였다. 최적설계 결과 시스템의 전체 동적, 정적 강성을 저하시키지 않은 채로 붐은 19%, 지지부는 17% 경량화시킬 수 있었다.

• 한국분무공학회지
• /
• 제22권4호
• /
• pp.210-217
• /
• 2017

A gasoline direct injection engine has an intake air temperature can be lowered by the fuel vaporization in the combustion chamber increase the volume efficiency is high compression ratio. Therefore, study for injection rate and characteristics which influence mixture formation in combustion chamber is important. Movement of the injector needle has a direct effect on the injection of the fuel, such as formation of cavitation, the fuel injection rate, etc. Therefore, recent studies on the dynamic characteristics of the injector considering the movement of the needle have been reported, but it takes a lot of time and cost to experimentally confirm the movement of the needle inside the injector. In this study, AMESim, a commercial 1-D code, and Star-CCM+, a 3-D CFD code, were used to predict the dynamic performance of the injector with needle motion. In order to predict the movement of the needle under the high pressure, the result of the surface pressure distribution according to the movement of the needle was derived by using the morphing technique of flow analysis. In addition, we predicted the injection rate of the injector considering the movement of the needle in conjunction with the 1-D code. The injection rate of the injector was measured by the BOSCH's method and the results were similar to those of the simulation results. This method can predict the injection rate and injection characteristics and this result is expected to be used to predict the performance of gasoline direct injection engines with low cost and time in the future.