• Wind and Structures
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• 제34권3호
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• pp.259-274
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• 2022

The present paper is focused on analyzing a set of Computational Fluid Dynamics (CFD) simulation data on reducing orthogonal peak base moment coefficients on a high-rise rectangular building with wings. The study adopts an aerodynamic optimization procedure (AOP) composed of CFD, artificial neural network (ANN), and genetic algorithm (G.A.). A parametric study is primarily accomplished by altering the wing positions with 3D transient CFD analysis using k - ε turbulence models. The CFD technique is validated by taking up a wind tunnel test. The required design parameters are obtained at each design point and used for training ANN. The trained ANN models are used as surrogates to conduct optimization studies using G.A. Two single-objective optimizations are performed to minimize the peak base moment coefficients in the individual directions. An additional multiobjective optimization is implemented with the motivation of diminishing the two orthogonal peak base moments concurrently. Pareto-optimal solutions specifying the preferred building shapes are offered.

• 제어로봇시스템학회논문지
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• 제6권8호
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• pp.727-731
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• 2000

This paper presents a new practical autopilot design approach to acceleration control for tail-controlled STT(Skid-to-Turn) missiles. The approach is novel in that the proposed parametric affine missile model adopts acceleration as th controlled output and considers the couplings between the forces as well as the moments and control fin deflections. The aerodynamic coefficients in the proposed model are expressed in a closed form with fittable parameters over the whole operating range. The parameters are fitted from aerodynamic coefficient look-up tables by the function approximation technique which is based on the combination of local parametric models through curve fitting using the corresponding influence functions. In this paper in order to employ the results of parametric affine modeling in the autopilot controller design we derived a parametric affine missile model and designed a feedback linearizing controller for the obtained model. Stability analysis for the overall closed loop sys-tem is provided considering the uncertainties arising from approximation errors. the validity of the proposed modeling and control approach is demonstrated through simulations for an STT missile.

• 한국항공운항학회지
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• 제23권2호
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• pp.7-14
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• 2015

This paper deals with an optimal determination process for the built-in location of localizer under restrictive siting area conditions of a domestic P-airport. Aerodynamic forces and moments acting on the localizer structure can be used a reference to find the safe distance from jet blast and the position at which the reasonable structural loading is applied. Wind tunnel experiment is conducted to measure aerodynamic loadings. The finite element analysis for structural deformation is employed to get the information of structural failure. A new localizer's position is determined by considering aerodynamic loading, structural strength and thermal loading due to jet blast. Deflector effect was also investigated in this study. In conclusion, the location of localizer can be placed at shorter than the current position and greatly decreased if the deflector is applied at the front of localizer.

• Wind and Structures
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• 제13권2호
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• pp.127-144
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• 2010

Pressure measurements on static and autorotating flat plates have been recently reported by Lin et al. (2006), Holmes, et al. (2006), and Richards, et al. (2008), amongst others. In general, the variation of the normal force with respect to the angle of attack appears to stall in the mid attack angle range with a large scale separation in the wake. To date however, no surface pressures have been measured on auto-rotating plates that are typical of a certain class of debris. This paper presents the results of an experiment to measure the aerodynamic forces on a flat plate held stationary at different angles to the flow and allowing the plate to auto-rotate. The forces were determined through the measurement of differential pressures on either side of the plate with internally mounted pressure transducers and data logging systems. Results are presented for surface pressure distributions and overall integrated forces and moments on the plates in coefficient form. Computed static force coefficients show the stall effect at the mid range angle of attack and some variation for different Reynolds numbers. Normal forces determined from autorotational experiments are higher than the static values at most pitch angles over a cycle. The resulting moment coefficient does not compare well with current analytical formulations which suggest the existence of a flow mechanism that cannot be completely described through static tests.

• 한국항공우주학회지
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• 제40권10호
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• pp.882-887
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• 2012

본 논문은 한국 최초 국산 비행기라 할 수 있는 부활호의 개량 복원을 위하여 부활호 비행기의 공력특성을 연구한 것이다. 공력특성의 예측은 전산유체역학과 풍동시험기법을 적용하였다. 부활호의 기본 형상에 대하여 공력특성을 예측하고 비행기의 자세변화와 조종면 변위각에 따른 공력을 구하였다. 플랩과 엘리베이터의 변위각과 받음각의 변화에 따른 양력, 항력 및 피칭모멘트의 변화를 분석하였고, 에일러론과 러더의 변위각과 옆 미끄럼각의 변화에 따른 측력, 요잉모멘트 및 롤링모멘트의 변화를 분석하여 비행 안정성 및 특성에 대하여 논하였다. 연구 결과 부활호의 공력 특성이 CFD와 풍동시험에서 의미있는 유사한 결과를 얻었으며, 이에 따른 비행시험에서 원활하게 증명이 되었다.

• 한국항공우주학회지
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• 제41권11호
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• pp.849-854
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• 2013

본 연구에서는 편대비행하는 고속 항공기의 날개 끝 와류의 공력 간섭 효과를 연구하기 위해서 풍동실험기법이 적용되었다. 편대비행에서 앞선 항공기의 날개 끝에서 발생하는 와류가 뒤따르는 항공기의 공력 특성에 영향을 미칠 수 있다. 흐름의 간섭 효과는 앞선 항공기와 뒤따르는 항공기의 날개 끝 사이의 거리에 따라서 변화된다. 본 연구의 실험결과 앞선 항공기에서 발생되는 날개 끝 와류는 뒤따르는 항공기의 공력 및 모멘트 계수를 변화시킴을 확인하였다. 특히, 후방 항공기의 양력계수는 수직 및 수평 위치에 따라 y/b=-0.125, z/b=0.0에서 가장 많이 증가되거나 y/b=-0.5, z/b=0.38에서 가장 크게 감소됨을 확인하였으며, 두 항공기로부터 발생된 날개 끝 와류의 간섭 현상이 자세히 관찰되었다.

• Journal of Astronomy and Space Sciences
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• 제1권1호
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• pp.5-21
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• 1984

The airflow along the surface of a launch vehicle together with base flow of clustered nozzles cause problems which may affect the stability or efficiency of the entire vehicle. The problem may occur when the vehicle is on the launching pad or even during flight. As for such problems, local steady-state loads, overall steady-state loads, buffet, ground wind loads, base heating and rocket-nozzle hinge moments are examined here specifically.

• 대한기계학회논문집B
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• 제34권6호
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• pp.649-654
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• 2010

DUP (direct underside pressurization)-장치와 프로펠러가 있는 3 차원 형상의 위그선(WIG-craft) 주위의 유동특성을 수치적으로 해석하였다. 이를 통하여 위그선 주위의 공기역학 관점의 힘들과 모멘트에 대해 고찰하였다. 이 연구의 해석에 사용된 모델은 프로펠러, 동체, 날개와 동체아래의 압력실 (air chamber)을 포함한 전 영역에 대하여 수행하였다. DUP 장치는 추력의 일부를 동체 아래의 압력실에 정체시킴으로 이륙 시와 같이 낮은 속도에도 효과적으로 양력을 증가시켜 이륙 속도를 줄이는 장치이다. 이러한 DUP 장치는 동압의 증가로 인하여 항력이 증가하고 공기의 회전성분으로 인하여 추가적인 모멘트를 생성하게 된다. 위그선의 비대칭 유동에 의해 발생하는 요잉 및 롤링 모멘트가 위그선의 안정성에 미치는 영향은 매우 미미하였다.

• 한국항공우주학회지
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• 제38권9호
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• pp.856-861
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• 2010

본 연구에서는 하이브리드 과학로켓의 공력특성을 파악하고 정적 세로 안정성에 대한 판단을 하기 위해서 초음속 풍동실험을 하였다. 과학로켓의 10% 축소모델에 대해서 마하수 1.75~2.5, 받음각 $0^{\circ}{\sim}6^{\circ}$의 조건에서 실험을 수행하였으며, 4분력 내장형 밸런스를 사용하여 실험모델의 공력과 모멘트를 측정하였다. 측정된 자료를 바탕으로 로켓의 안정성을 판단하였으며, 로켓의 길이효과를 분석하기 위하여 길이가 다른 3개의 모델에 대하여 실험을 수행하였다. 또한, 쉴리렌 광학장치를 이용하여 초음속 비행 시 발생하는 충격파를 가시화하고 속도 및 받음각 변화에 따른 충격파의 변화를 관찰하였다.

• 한국유체기계학회 논문집
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• 제10권6호
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• pp.32-37
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• 2007

Aerodynamic forces and moments have been used to control rocket propelled vehicles. If control is required at very low speed, Those systems only provide a limited capability because aerodynamic control force is proportional to the air density and low dynamic pressure. But thrust vector control(TVC) can overcome the disadvantages. TVC is the method which generates the side force and roll moment by controlling exhausted gas directly in a rocket nozzle. TVC is classified by mechanical and fluid dynamic methods. Mechanical methods can change the flow direction by several objects installed in a rocket nozzle exhaust such as tapered ramp tabs and jet vane. Fluid dynamic methods control the flight direction with the injection of secondary gaseous flows into the rocket nozzle. The tapered ramp tabs of mechanical methods are used in this paper. They installed at the rear in the rocket nozzle could be freely moved along axial and radial direction on the mounting ring to provide the mass flow rate which is injected from the rocket nozzle. In this paper, the conceptual design and the study on the tapered ramp tabs of the thurst vector control has been carried out using the supersonic cold flow system and schlieren system. This paper provides the thrust spoilage, three directional forces and moments and distribution of surface pressure on the region enclosed by the tapered ramp tabs.