• 시스템엔지니어링학술지
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• 제9권2호
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• pp.83-90
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• 2013

Integrated aircraft synthesis process for rapid analysis and design is described in this paper. Data flow between different analysis fields is described in details. All the data are divided into several groups according to importance and source of the data. Analysis of design requirements and certification regulations is carried out to determine baseline configuration of an aircraft. Overall design process can be divided into initial sizing, conceptual and preliminary design phases. Basic data for conceptual design are obtained from initial sizing, CAD and geometry analysis. Basic data are required input for weight, aerodynamics and propulsion analyses. Results of this analysis are used for stability and control, performance, mission, and load analysis. Feasibility of design is verified based on analysis results of each discipline. Design optimization that involves integrated process for aircraft analysis is performed to determine optimum configuration of an aircraft on a conceptual design stage. The process presented in this paper was verified to be used for light aircraft design.

• 한국항공운항학회지
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• 제19권4호
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• pp.67-73
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• 2011

For loads analysis of airplane, applicable regulation should be determined. Then, loads conditions are prepared from the regulation. Modeling for aerodynamic, mass, and structure are performed. Panel method is usually adopted for aircraft loads analysis to obtain air loads. The ARGON which is a multidisciplinary fixed wing aircraft design software co-developed by the KARI and TsAGI are used for loads analysis. The ARGON can be utilized for flutter and stress analysis as well as for flight and ground loads analysis. In this paper, flight loads analysis for wing structural design of the regional aircraft at the conceptual design phase are performed with the ARGON. FAR 25 is used for the regulation for the load analysis. Shear force, bending moment and torsion diagrams for the wing and shear force and hinge moment for the aileron are presented.

• 한국군사과학기술학회지
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• 제12권2호
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• pp.248-257
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• 2009

The aim of this paper is to propose fighter aircraft's mission severity model which can be used as one of key factors for designing a structure and determining design life of KF-X. The mission severity is a quantitative data of flight loads and expressed by Nz(Vertical Load Factor) exceedances or occurrences. The severities of the flight loads depended on the circumstances of the countries which operate fighter aircraft. In this paper we have studied on Nz occurrences/exceedances of ROKAF fighter aircraft to generate mission severity model for the KF-X. The analyses of flight data were accomplished by using the Matlab.

• 대한기계학회논문집A
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• 제21권2호
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• pp.217-222
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• 1997

A simple finite element approach to predicting deformed shape and load-deflection curve of elastomers is presented in this paper. The method is based on several simplifications in deformation pattern and material behavior. The conventional updated Lagrangian approach is employed together with material data obtained by a simple tension test. The presented approach is verified through comparison of predicted results with experimental ones and applied successfully to shape design of various elastomers for shock, vibration and noise control. The advantage of the presented approach lies in easiness, simplicity and accuracy enough for engineering application.

• 항공우주시스템공학회지
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• 제12권3호
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• pp.38-44
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• 2018

군용항공기는 다양한 임무의 수행을 통한 비행시간 누적과 예상 불가능한 외기 환경에 의한 복합적인 요인으로 구조적으로 취약한 부위에서 피로균열이 발생할 수 있다. 피로 균열은 점차 진전되어 극심한 경우 해당 구조가 파괴될 위험이 있으며 이는 비행 안전성에 큰 영향을 미칠 수 있다. 본 논문에서는 항공기 주익과 동체의 연결부위를 보호하기 위해 장착한 페어링 내부의 지지대에서 주기검사 중 균열 현상을 개선하기 위한 일련의 품질개선에 관한 연구를 수행하였다. 균열의 원인파악을 위해 주익 조립 공정에 따른 예하중 발생 여부에 대해 조사하고 파단면 분석을 수행하였다. 또한, 균열의 재발방지를 위해 지지대의 설계를 개선하는 방안을 제시하였고, 응력 및 피로 수명해석을 통해 구조 건전성을 검증하였다.

• 항공우주시스템공학회지
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• 제13권3호
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• pp.32-39
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• 2019

항공기 외부에 장착되어 전술임무에 사용되는 센서 포드는 운용기간 동안 예상되는 하중 스펙트럼에 대한 피로수명이 확보되어야 한다. 센서 포드와 같은 임무장비는 해석의 효율성을 고려하여 동적 진동 환경조건을 적용한 주파수 영역의 피로수명 예측방법이 선호되어 왔다. 본 논문에서는 실제 비행체 하중 스펙트럼을 고려하여 정적 및 동적 하중에 의한 응력을 합성한 주파수 영역에서의 피로수명 예측방법을 제안하였다. 기존 해석방법과 비교한 결과 제안된 해석방법은 피로수명이 보수적으로 예측되었다. 그리고 제안된 방법으로 해석한 결과 설계된 센서 포드는 피로수명 요구조건을 만족하였다.

• Advances in aircraft and spacecraft science
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• 제5권1호
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• pp.129-139
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• 2018

The composite materials are widely used in aircraft structures. Their relative rigidity/weight gives them an important advantage over the metal structures. The objective of this work is to analyze by the finite element method the mechanical behavior of composite plate type notched with various forms under tensile load. Two basic parameters were taken into consideration. The first, the form of the notch in order to see its effect on the stress and the failure load. The second, we studied the influence of the locale orientation of fiber around the plate's notch. These parameters are studied in order to see their effects on the distribution stress and failure load of the plate. The calculation of the failure load is determined numerically with the numerical code ABAQUS using the XFEM (extended Finite Element Modeling) based on the fracture mechanics. The result shows clearly that it is important to optimize the effect of fiber orientation around the notch.

• 한국기계가공학회지
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• 제11권1호
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• pp.39-45
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• 2012

Currently, the aircraft industry, aircraft parts as well as airframe have been developed in producing, the aircraft parts and fuselages have been produced the product by cutting rather than forging and casting because of the residual stress and stress concentration. In this study, the aircraft is being used in many parts of aluminium alloy 2024 in wire-cut E.D.M. The selected experimental parameters are peak current, no-load voltage, off time and feed rate. It is found that cutting mountain part on surface roughness of the curve 0.3mm than 0.25mm diameter wire electrode is stable in many uniform distribution.

• 항공우주시스템공학회지
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• 제3권1호
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• pp.42-46
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• 2009

The 1st development of "Human Powered Aircraft(HPA)" in Korea has been conducting by KAFA(Korea Air Force Academy) from Aug. 2008 to now. HPA is an aircraft powered by directly human energy. The thrust provided by the human power may be the only source and that is weak. Therefore, light weight and strong structure is first requirement. In this paper, treating a basic conceptual design of HPA and material property and material choice for HPA. Also analysing the structure and checking the safety of HPA.

• 한국군사과학기술학회지
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• 제26권1호
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• pp.1-9
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• 2023

The skin structure of sensor pod mounted on the exterior of aircraft can be exposed to the acoustic dynamic load and static load such as aerodynamic pressure and inertial load during flight. Fatigue life prediction of structural model under acoustic load should be performed and also differential stiffness of model modified by static load should be considered. The acoustic noise test spectrum of MIL-STD-810G was applied to the structural model and the stress response power spectral density (PSD) was calculated. The frequency response analysis was performed with or without prestress induced by inplane static load, and the response spectrum was compared. Time series data was generated using the calculated PSD, and the time and frequency domain fatigue life were predicted and compared. The variation of stress response spectrum due to static load and predicted fatigue life according to the different structural model considering mean stress were examined and decreasing fatigue life was observed in the model with prestress of compressive static load.