• Journal of Welding and Joining
• /
• 제21권5호
• /
• pp.518-524
• /
• 2003

The block assembly of ship consists of a series of heat processes such as cutting, bending, welding, residual stress relaxation and fairing. With the fast development of computers, the thermal elasto-plastic analysis method has become a versatile tool for practical applications in the ship production. If numerical analysis is proved to be an advantageous tool to predict the residual deformation due to various heat processes, the optimum methods which can remove the welding distortion can be presented at each assembly stage, which will result in great progress in improving the accuracy of block assembly. In order to minimize the weld-induced angular distortion in thick weldments, this paper proposes the optimum groove design for various plate thickness as the distortion control method. The validity of this method has been substantiated by a number of numerical simulations and experiments.

• 한국해양공학회지
• /
• 제22권6호
• /
• pp.100-105
• /
• 2008

The block assembly of ship consists of a series of heat processes such as cutting, bending, welding residual stress relaxation and fairing With the fast development of computers, the thermal elasto-plastic analysis method has become a versatile tool for practical applications in the ship production. If numerical analysis is proved to be an advantageous tool to predict the residual deformation due to various heat processes, the optimum methods which can remove the welding distortion can be presented at each assembly stage, which will result in great progress in improving the accuracy of block assembly. In order to minimize the weld-induced angular distortion in thick weldments, this paper proposes the optimum groove design for various plate thickness as the distortion control method. The validity of this method has been substantiated by a number of numerical simulations and experiments.

• 대한기계학회:학술대회논문집
• /
• 대한기계학회 2003년도 추계학술대회
• /
• pp.163-168
• /
• 2003

Analytical approach is applied to predict temperature of satellite box under worst hot condition from fairing jettison to separation. The box is tried to solve analytically which is exposed to known environmental heating condition and has internal heating and irradiation to space. For a single thermal mass, governing equation for temperature is simplified to 1st order ordinary differential equation(ODE) by several assumptions. Two cases are considered. The one is for constant mass box and the other is for mass-varying box. Each case has three different analytical solution by sign of constant term in ODE. One analytical solution for constant mass is applied to physical launch stage condition. It is concluded that the present analytical method can be used to quick predict the temperature of a satellite box and check whether a satellite is safe against space environment during launch stage.

• 한국소음진동공학회:학술대회논문집
• /
• 한국소음진동공학회 2011년도 추계학술대회 논문집
• /
• pp.64-71
• /
• 2011

In this study, steady and unsteady aerodynamic analyses of a huge rocket configuration have been conducted in a transonic flow region. The launch vehicle structural response are coupled with the transonic flow state transitions at the nose of the payload fairing. The developed fluid-structure coupled analysis system is applied for aeroelastic computations combining computational structural dynamics(CSD), finite element method(FEM) and computational fluid dynamics(CFD) in the time domain. It can give very accurate and useful engineering data on the structural dynamic design of advanced flight vehicles. For the nonlinear unsteady aerodynamics in high transonic flow region, Navier-Stokes equations using the structured grid system have been applied to the rocket configurations. Also, it is typically shown that the current computation approach can yield realistic and practical results for rocket design and test engineers.

• 수산해양기술연구
• /
• 제39권4호
• /
• pp.298-304
• /
• 2003

In this paper a free-form hull design program and performance prediction program for planing boat is introduced. This program enables the designer to do complex geometric hull shape design on a personal computer and accurately to predict power requirements for a given loading and velocity. For a free form design, Bezier curve model is adopted as a basic representation tool of curves and surfaces, and this program has versatile functions to do fairing jobs with a convenient graphical user interface. After creating a hull form the geometric data is provided in a manner compatible with a variety of analysis tools including 'Motion Analysis(by Zarnick)' for prediction of motion characteristics in regular waves, 'Running Attitude (by Savitsky)' for prediction of the running attitude and required power.

• 대한조선학회논문집
• /
• 제35권4호
• /
• pp.118-125
• /
• 1998

본 연구는 B-spline 근사법과 유전자 알고리즘을 이용하여 기하학적 경계 조건-양끝점의 위치 벡터 및 접선 벡터-을 만족하는 혼합 곡선 근사법에 의한 선형 표현을 내용으로 한다. B-spline 근사법을 이용하여 선형을 표현하고, 이들 곡선을 제어하는 조정점들이 기하학적 경계조건을 만족하도록 유전자 알고리즘으로 조정한다. 이 방법은 선형 생성시 순정 작업을 동시에 수행하므로 효율적인 선형 설계를 가능하게 한다.

• 항공우주기술
• /
• 제1권1호
• /
• pp.128-134
• /
• 2002

고속비행 중의 공력가열과 같은 외부 열전달로부터 외피 구조물과 내부 탑재물을 보호하기 위하여, KSR-III의 외피에 단열처리가 필요하였다. 일련의 시험과 분석을 통하여 선정된 단열재인 BMS 10-102는 스프레이 가공 형식의 점착성 물질로서 외피에 도포 후 경화시키며, 낮은 열전달율과 낮은 밀도와 같은 특성을 지녀 우수한 단열효과를 기대할 수 있다. 본 연구에서는 KSR-III 기본형 설계에서 대표적인 다층구조인 노즈 페어링부의 honeycomb 샌드위치 구조에 대한 단열해석을 수행하였다.

• 한국소음진동공학회:학술대회논문집
• /
• 한국소음진동공학회 2005년도 추계학술대회논문집
• /
• pp.172-175
• /
• 2005

Since, similar to other commercial launch vehicles, various kinds of pyrotechnique devices are used in the KSLV-I(Korea Space Launch Vehicle), the electronic equipment on the vehicle equipment bay is exposed to the sever pyroshock environment during Pyrotechnique device detonation. In order to confirm the survivability of electrical instruments from these pyroshock conditions, shock tests are performed by using a pyroshock simulation during development and qualification phase. In this paper, the pyroshock simulator installed in KARI(Korea Aerospace Research Institute) are briefly introduced, and its performance of pyroshock generating is compared with the measured shock response spectrums from small scaled fairing jettisoning tests. The results show that the pyroshock simulator is still proper to generate severe pyroshocks similar to real pyrotechique detonating conditions, but the redesign on the test jigs is necessary to improve its test performance.

• Advances in aircraft and spacecraft science
• /
• 제8권4호
• /
• pp.331-344
• /
• 2021

Airframe internal and external specifications are the product of intensive intellectual efforts and technological breakthroughs distinguishing each aircraft manufacturer. Therefore, geometrical information characterizing aircraft primary aerodynamic surfaces remain classified. When attempting to model real aircraft, many members of the aeronautical community depend on their personal expertise and generic design principles to bypass the confidentiality obstacles and sketch real aircraft airfoils, which therefore vary for the same aircraft due to the different designers' initial assumptions. This paper presents a photogrammetric shape prediction method for deriving geometrical properties of real aircraft airframe by utilizing their publicly accessible static and dynamic visual content. The method is based on extracting the visually distinguishable curves at the fairing regions between aerodynamic surfaces and fuselage. Two case studies on B-29 and B-737 are presented showing how to approximate the sectional coordinates of their wing inboard airfoils and proving the good agreement between the geometrical and aerodynamic properties of the replicated airfoils to their original versions. Therefore, the paper provides a systematic reverse engineering approach that will enhance aircraft conceptual design and flight performance optimization studies.

• 항공우주기술
• /
• 제4권1호
• /
• pp.150-161
• /
• 2005

발사체의 노즈 페어링 벤트 홀 크기 결정 기법의 정확도를 검증하기 위한 시험을 수행하였다. 한국항공우주연구원 우주비행시험그룹이 보유한 열진공 챔버(Bake-Out Chamber)를 이용하여 챔버 내부 압력을 대기압에서 진공으로 떨어뜨렸으며, 그 속에 다양한 벤트홀이 설치된 모델을 넣고 모델 내외부의 압력 및 온도 변화를 측정하였다. 시험 과정에서 나타난 시험 설비 및 측정 장비의 특성을 검토하고 이들이 얻어진 시험 데이터의 정확도 및 신뢰도에 미치는 영향을 분석하였다. 설비 및 측정 장비의 한계 내에서 최대한의 정확도를 얻을 수 있도록 데이터를 처리하였으며, 이렇게 얻어진 시험 결과로부터 벤트 홀 면적 및 배치에 따르는 영향을 분석하였다.