• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.30 no.2
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• pp.115-121
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• 2002

This report summarized the static test of the rudder system for the KTX-1 basic trainer. The test loads are applied up to the limit and ultimate loads in a stepping sequence. Test loads and test results matt the strength and stiffness requirements of the rudder control system.. Using #004 full scale structure test airframe.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.3
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• pp.82-87
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• 2004

The general requirements to achieve the structural integrity of the airframe are described in the military specification, MIL-HDBK-1530. One of these requirements is the durability and damage tolerance of the airframe, which should be shown through the analysis and test based on the related specifications. This paper describes the full scale durability test load simulation to evaluate the structural safety and durability of the advanced trainer, T-50. The test load simulation was performed according to the procedure in the military specification and the KAF contract requirements. The durability test design technique which involve the floating test set-up, the optimal test load simulation method, and the 6-DOF test article balance method to secure the real flight conditions as many as possible. It was confirmed that this method will be available in a similar full-scale airframe structural test in future.

• Aerospace Engineering and Technology
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• v.1 no.2
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• pp.32-44
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• 2002

This paper contains the information that describes the test fixture design and technology for full-scale airframe static test. Obtained technologies consist of determination of design load for test fixture, design technique for loading system, counterbalance system, positioning system of test article, test equipment and overload protection method. Full-scale airframe static test of advanced jet trainer was implemented using test fixture which are applied these technique.

• Aerospace Engineering and Technology
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• v.10 no.2
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• pp.146-153
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• 2011

Some methods of calculation of test load value from design load data were investigated which will be applied at strap installed full-scale airframe of composite aircraft. These methods were applied to left wing of KC-100 composite aircraft and the calculated test load values were compared with each others. Generally since test load values are differently calculated according to each aircraft type and position of straps, all calculation methods mentioned at this study need to be applied and compared to each aircraft. Finally the most appropriate method needs to be selected.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.46 no.6
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• pp.471-478
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• 2018

Static tests of the composite wing structure were performed to verify damage tolerance design. Both 5 cases of DLLT and 3 cases of DULT were completed to meet requirements for static strength. After inducing BVID and open hole damages on the critical areas of the composite wing based on associated regulations, the DULT and fracture test were performed. In major wing parts, the measured strains and displacements agreed well with those of structural analysis. The initial structural fracture occurred at the area having minimum margin of safety as expected by analysis. As a result, it was confirmed that results from analytic model and strength evaluation were similar to behaviors of the composite wing structure.

• KSCE Journal of Civil and Environmental Engineering Research
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• v.28 no.6C
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• pp.379-388
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• 2008

In the bi-directional pile load test (BD PLT) for pile load tests of Mega pile foundations, loading capacity standard is not specified exactly. Therefore there are so many confusions in performing the BD PLT and variations up to maximum 2 times in loading capacity are come out. In this study, standards of bi-directional pile load test (BD PLT) were considered. Based on cases of the bi-directional pile load test performed in domestic areas, maximum equivalent test load, test load increasing ratio, loading capacity increasing ratio and sufficiency ratio of design load were analyzed. It could be known that the loading capacity standard of bi-directional pile load test must be defined as 1-directional loading capacity and also must be established as more than 2 times of design load.

• Proceedings of the Korean Geotechical Society Conference
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• 1999.07a
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• pp.65-91
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• 1999

말뚝기초의 지지력예측방법 중 신뢰도가 가장 높은 것은 말뚝정재하 시험방법이므로 말뚝기초의 경제적이고 신뢰성있는 설계를 위하여 하중전이의 측정이 수반된 말뚝재하시험을 실시하여야 할 것이다. 따라서, 말뚝재하시험 방법들에 대하여 고찰하고, 시험결과의 해석사례를 설명하였다. 또한, 신뢰성있는 말뚝재하시험 수행을 위하여 고려해야 할 점들도 설명하였다. 또한, 하중전이측정실험에 대한 기본개념을 고찰하였으며, 이 결과의 활용방안에 대한 설명도 부가하였다.

• Proceedings of the KAIS Fall Conference
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• 2009.12a
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• pp.885-888
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• 2009

자동차용 Alloy Wheel은 차량의 수직하중이나 가로 방향 하중, 구동, 제동토크 등 주행 시에 발생하는 여러 형태의 응력을 받으면서 사용되므로 이러한 응력을 견딜 수 있는 강성은 물론 차량 부품으로서의 요구 수명도 만족하여야 한다. 알루미늄 휠은 개발 후 규격에 준하는 내구성 평가를 위하여 반경 방향 부하 내구시험과 굽힘모멘트 내구시험과 주행 중 요철이나 벽돌 등에 의한 노면으로부터 갑작스런 하중에 대한 내충격성 평가를 위한 충격시험이 실행되고 있다. 이러한 시험은 많은 시간이 소요되고 있으며, 또한 시험 중 불합격 판정이 날 경우 또다시 처음의 공정을 모두 거쳐 다시 시험을 하게 된다. 3 Piece와 같은 알루미늄 휠은 여러 공정에 의한 생산되어지기 때문에 많은 시간적, 물질적 손실이 일어나고 있다. 따라서 자동차용 알루미늄 휠의 요구조건을 충분히 만족시키며 소비자의 요구에 맞는 품질과 시간을 충족시켜 기업경쟁력 확보는 물론 원가절감에 의한 기업 경쟁력 향상을 위하여 설계 단계서부터 시험조건을 고려한 내구성 해석에 의한 알루미늄 휠의 시험횟수를 단축하고자 한다. 본 논문에서는 3 Piece 알루미늄 휠의 축(shaft)하중에 의한 내구성 평가에 대하여 CAE시스템을 이용하여 보다 빠르고 정확한 결과를 산출함으로서 설계시간의 단축은 물론 다양한 형상의 제품들을 설계단계에서부터 생산에 이르기까지의 해석활용법을 수립하고자 하였다.

• Journal of the Korea Concrete Institute
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• v.20 no.5
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• pp.583-592
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• 2008

Recently, the effects of high temperature on compressive strength, elastic modulus and strain at peak stress of high strength concrete were experimentally investigated. The present study is aimed to study the effect of elevated temperatures ranging from 20 to 700 on the material mechanical properties of high strength concrete of 40, 60, 80 MPa grade. In this study, the types of test were the stressed test and stressed residual test that the specimens are subjected to a 25% of ultimate compressive strength at room temperature and sustained during heating and when target temperature is reached, the specimens are loaded to failure. And another specimens are loaded to failure after 24 hour cooling time. Tests were conducted at various temperatures ($20{\sim}700^{\circ}C$) for concretes made with W/B ratios 46%, 32% and 25%. Test results showed that the relative values of compressive strength and elastic modulus decreased with increasing compressive strength grade of specimen and the axial strain at peak stress were influenced by the load before heating. Thermal strain of concrete at high temperature was affected by the preload level as well as the compressive strength. Finally, model equation for compressive strength and elastic modulus of heated high strength concrete proposed by result of this study.

• Aerospace Engineering and Technology
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• v.3 no.2
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• pp.208-216
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• 2004

Advanced overload protection module for full scale airframe structural test was developed by improving the existing overload protection module. When performing the full scale airframe structural test, overload can be applied to the test article due to unexpected situations such as system shutdown, test article failure, and deficiency of design strength. Therefore, the overload protection module is needed for protecting the test article in unexpected overload situations. In this paper, the function of the existing overload protection module was summarized for each component and the problems encountered when using it in structural test were analyzed in addition, the development of advanced overload protection module was described.