• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1996.05a
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• pp.265-272
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• 1996

액츄에이터에 사용되는 터어보 펌프의 터어빈을 구동시키기 위한 가스발생기용 고체연료 추진기관의 뒷마개부에 대하여 열/구조 해석을 수행하였다. 가스발생기는 장시간 연소모타로써 뒷마개에는 단열이 되어 있지 않은 배출튜브가 나사로 체결되어 고온, 고압의 연소가스에 의해 뒷마개 구조물에 작용하는 열 하중이 상당히 클 것으로 판단되므로, 최적설계를 위하여 뒷마개부의 열 및 구조해석을 수행하여 열하중의 영향을 예측하고 경량화를 위한 설계자료를 얻고자 하였다. 본 논문에서는 해석결과만을 언급하였으며 차후에 수행될 지상시험시에 해석치와 실험치를 비교한 후 좀 더 정확히 모델링을 하여 열/구조 해석 결과를 뒷마개부의 최적설계에 활용하고자 한다. 해석 결과 열하중이 연소관과의 조립부에는 거의 영향을 주지 않았으나, 열과 압력하중이 동시에 작용할 경우에 뒷마개 배출튜브의 조립부 근접한 곳에서 항복응력을 넘는 응력이 발생하여 정확한 구조 해석을 위해서는 탄소성해석을 수행하여야 할 것으로 판단된다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.703-704
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• 2010

The environmental tests simulating the flight condition have been performed to manufacture the high reliable safety and arming device(SAD). A motor assay in preliminary design was reinforced with the structure to resist severe vibration and shock environment, and the design change had been verified by conducting the principal environmental test again.

• Journal of Aerospace System Engineering
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• v.12 no.3
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• pp.1-8
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• 2018

The fuel pump, which is used for an aircraft, was first developed in Korea through the Civil-Military Dual Components Development Program. The BLDC motor type, which is superior to the DC brush motor when considering efficiency, endurance, and explosive environmental characteristics, was applied to the fuel pump given its capacity and operating condition. The magnetic flux of the permanent magnet was analyzed based on the magnet flux density equation, using the Maxwell equation and the environmental condition. The motor performance, according to the load, was analyzed using the finite element method in order to design validation. The motor assembly was developed by designing the motor drive and the EMI filters. The performance test results of the motor assembly for the fuel boost pump were consistent with the analysis.

• The Bulletin of The Korean Astronomical Society
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• v.37 no.2
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• pp.153.1-153.1
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• 2012

조립 후 발사대로 이송된 추진기관(또는 발사체)는 지상시험 및 비행시험을 위한 충전을 하게 되는데, 추진제 및 고압가스 등 추진기관 구성품의 운용절차는 하드웨어의 설계 단계에서 그 개념이 수립되어야 한다. 다시 말해, 발사체 및 추진기관 설계 단계에서 연료와 산화제의 충전/배출, 시험 취소시의 운용절차 개념이 수립되어 있어야 추진기관 구성품들의 설계, 지상인터페이스 구성품의 설계에 그 내용이 반영될 수 있다. 따라서, 본 논문에서는 발사체 및 추진기관 운용와 관련된 일반적인 충전/배출 절차와 지연 또는 취소시의 작업절차의 주요개념을 다루었고, 추진기관 운용에 필요한 각종 지상설비에 요구되는 주요 기능을 검토하였다. 또한, 추진제 충전 이후 발사 대기시까지의 업무와 발사 전에 수행되어야 하는 추진기관 운용 업무(Pre-Launch Operation)도 다루었다. 특히 다단 발사체의 경우에는 운용과 관련된 준비 업무량이 단수에 비례하여 늘어나므로, 효율적으로 모든 시험 준비 업무를 마치기 위해, 지상에서의 추진기관 운용절차는 각 단별로 유기적으로 진행되어야 한다. 즉, 각 단별 하드웨어에 대한 사전 검사, 충전, 대기 등의 운용시간 설계 및 그 절차가 중요하다. 한국형 발사체 및 추진기관의 운용 개념설계를 수행하는데에는 기 확보된 운용기술을 활용하였다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.44 no.9
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• pp.814-824
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• 2016

The mission objective of STEP Cube Lab. (Cube Laboratory for Space Technology Experimental Project) classified as a pico-class satellite is to find space core technologies researched at domestic industry or university and to verify these technologies on mission orbit. To implement this objective, system level electrical integration and function test (EIT) by using developed flight software were performed in compliance with system requirements. And the effectiveness of the flight model (FM) was verified through launch and thermal vacuum test at acceptance level. This paper will introduce a series of process of electrical function tests for FM EIT, launch and thermal vacuum tests.

• 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.3 no.1
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• pp.232-241
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• 2004

KARI(Korea Aerospace Research Institute) is achieving the KSLV program according to National Space Technology Development Program. In this paper, the authors are intend to introduce the Integrated Power Plant(IPP) test facility which will be constructed for the variety of tests on KSLV program. IPP test facility refers to comprehensive testing equipment for liquid rocket launch vehicle. Using this facility, KARI can verify the adaptedness of parts and subsystems for launch vehicle and finally can qualify the system characteristics of launch vehicle doing kinds of test including hot firing test. IPP test facility will make it possible to simulate the vehicle launching circumstances and to predict the performance of launch vehicle during its flight test.

• Proceedings of the KSME Conference
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• 2004.11a
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• pp.383-387
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• 2004

The Fuel Test Loop (FTL) consists of In-Pile Test Section (IPS) and Out-of-Pile System (OPS). The test condition in IPS such as pressure, temperature and quality of the main cooling water, can be controlled by the OPS. The FTL has been developed to be able to irradiate three pins to the core irradiation hole (IR1 hole) by considering for its utility and user's irradiation requirement. The IPS vessel assembly (IVA) consists of IPS head, outer pressure vessel, inner pressure vessel, inner assembly and test fuel carrier. The IVA is approximately 5.6 m long and fits within a 74 mm in diameter envelope over the full height of the chimney. Above the top of the chimney, the head of the IPS is enlarged to allow the closure flanges and pipe work connections. IVA was designed to test the CANDU and PWR nuclear fuel pin together. Specially, wished to minimize interference by nuclear fuel change in design and synthesize these items and shape design for IVA.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.19 no.8
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• pp.239-245
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• 2018

The importance of reliability in the development of weapons systems and reliability tests has been emphasized recently. Therefore, this study evaluated a reliability test design method of a bladder type accumulator and proposed a process for reliability test design. To design the reliability test of the accumulator, the main failure modes and failure mechanisms were investigated, and the main stress factors were analyzed to select the appropriate acceleration model. A steady - state reliability test was designed according to the number of samples, and the reliability level and accelerated life test time were calculated according to the acceleration factor computed using the selected acceleration model.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.36 no.8
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• pp.740-746
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• 2008

In this paper, robust structural design of the PEMFC stack gasket is pursued with Taguchi method by considering the noise factor in stack assembly. The study of noise problem in stacking is required to secure the safety and performance improvement of PEMFC stack. The design parameters in the Taguchi method are selected so that the structural responses are insensitive to the noise factors. In the gasket analysis, a Mooney-Rivlin strain energy function is used to consider hyperelasticity between load and displacement. By uni-axial and equi-biaxial tension tests of the gasket, the material properties are determined for the use in robust design of PEMFC gasket. The robust design of the PEMFC stack may provide structural reliability.