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T-50 기체구조의 건전성 평가, 설계수명 평가 등을 위하여 전기체 내구성시험이 국방과학연구소 구조시험실에서 수행되고 있다. 일반적으로 구조시험의 성공 여부는 얼마나 정확하게 시험대상물의 경계조건을 구현하는가에 달려 있다. 특히, 시험대상물이 항공기 전기체일 경우 항공기의 실제 비행상태를 구현하기에 많은 어려움이 있기 때문에 본 논문에서는 고등훈련기 전기체 내구성시험을 위하여 개발된 부유식 시험조립 기법을 소개하고 적용 결과를 검토하였으며, 향후 항공기 전기체 구조시험을 수행하는데 있어서 유용한 시험 조립 기법임을 확인하였다. Full-scale airframe durability test has been performed to evaluate the integrity and the design life of the Advanced Trainer(T-50) Structure at the Structural Test Laboratory in Agency for Defense Development(ADD). Generally, the successful structural test depends on embodying exactly the boundary condition of a test specimen. If the test specimen is a full-scale airframe, it is difficult to embody the real flight condition of a aircraft during the test. In this paper, therefore, the floating test set-up technique for the Advanced Trainer Full-scale airframe durability test is introduced and reviewed. Also, it is confirmed that this method is available in a full-scale airframe structural test in future.
In this paper, the thermal buckling of thick composite angle-ply laminates subject to uniform temperature distribution is studied. For the plates of 4-edges simply supported condition and those of 4-edges clamped condition, the critical buckling temperatue is derived, using tile finite element method based on the shear deformation theory. The effects of lamination angle, layer number, laminate thickness, plate aspect ratio and boundary constraints upon the critical buckling temperature are presented.
In this paper, the design of thick laminated composite plate subjected to thermal buckling load under uniform temperature distribution is presented. In the design procedures of composite laminated plates for maximum thermal buckling load. the finite element method based on shear deformed theory is used for the analysis or laminated plates. One-demensional search method is used to find optimal fiber orientation and, in the next step, optimal thickness is investigated. Design variables such as fiber orientation and ply thicknesses coefficient of plates are adopted. The optimal design for the symmetric or antisymmetric laminated plates consisted of 4 layers with maximum thermal buckling load is performed.
The structure was needed to generate the shock wave with various shapes in the shock test. The structure mounted between the impactor and testbed was called “ Shock programmer”. Various material was used as the material of the shock programmer. In this paper, hyperelastic material was mainly used as the material of the shock programmer. Stress-strain curve of hyperelastic material was different under the velocity of the impactor. To obtain the S-S curve of the hyperelastic material , the small shock test was performed. The shape of the programmer was cylindrical type. The radius and height of the programmer was 150 mm and 100 mm. The velocity of the impactor was 4, 8, 12 m/s. Using the S-S curve of the hyperelastic material in the programmer under various velocities of the impactor, the parameter of the presented constitutive equation was calculated. The comparison on the characteristics of the hyperelastic material under various velocities of the impactor was performed.
본 논문에서는 기체 구조건전성 기준서(MIL-HDBK-1530B) 및 기체 구조건전성 프로그램(ASIP)에 의거하여 고등 훈련기(T-50)의 구조건전성평가와 양산 결정자료 획득을 위한 전기체 내구성시험 기법 개발에 대하여 기술하였다. 전기체 부유식 시험조립 기법, 시험하중 최적화 모사 기법, 시험부가 장치 설계 기법, 시험조립 설계 및 설치 기법, 시험안전장치 설계 및 운용 기법 및 전기체 내구성시험 수행 결과를 수록하였다. 1배 수명 전기체 내구성시험을 성공적으로 수행함으로써 시험기법의 타당성을 입증하였다. This paper describes the test technique for the full-scale airframe durability test according to the military handbook(MIL-HDBK-1530) and ASIP(Aircraft Structure Integrity Program) to evaluate structural integrity and to obtain basic data for IPA(Initial Production Approval) of the Korean advanced trainer(T-50). This paper covers the full-scale airframe floating setup technique, the optimized test load simulation method, test rig design technique, test setup design and installation techniques, test safety device design and operation technique, and durability test results. As 1st life durability test was successfully performed, it was confirmed that this method is available in a full-scale airframe structural test.
Impact Analysis of the structure under the impact load was needed to evaluate the structural safety of the impact resistance in structural design procedure. In this paper, To determine detail dimensions of the testbed under the impact load, the sizing optimization method was applied. The load condition in the optimization was used the impact load in various impact test standards. Design parameters of the testbed were applied as design variables in the optimization, such as round radius and thickness of the upper and lower plate and axial plate. The constraint variable was the total mass of the testbed. The objective variable was to maximize the 1st mode natural frequency and minimize the stress in the testbed.