• Journal of Aerospace System Engineering
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• v.14 no.5
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• pp.91-99
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• 2020

A liquid rocket engine goes through many tests to prove its performance before liftoff. It means the tests for setting ignition and start-up conditions or a test on design condition, which verifies the design performance. However, the development process requires verification of performance under off-design conditions through tests involving different operating conditions, which affects the duration of engine development. The off-design performance test is performed by altering the conditions of the propellant supplied to the engine in conjunction with the engine performance test that varies the opening of the control valves in the engine. This paper is based on the results of the engine tests performed at the KSLV-II engine test facilities in the Naro Space Center and describes the operations of the test facility for off-design condition test that changes the inlet conditions of the turbo-pump due to changes in the pressure and temperature of the propellant supplied to the test engines.

• Journal of Aerospace System Engineering
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• v.2 no.3
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• pp.29-32
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• 2008

The overview of KUH design and development process is presented according to Buede's systems and development "vee" model. The system decomposition and integration activities exemplify KUH specification tree, design maturity and analysis according to design stage(conceptual, preliminary, and detail design), scheduled work breakdown structure, qualification test, ground test, and flight test. This process can be applied to the development of a new aircraft.

• 연구논문집
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• s.25
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• pp.77-90
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• 1995

For improving performance of heat pump system, researcher has adapted 2-stage economizer cycle and developed a high-efficiency screw compressor, new working medium(non-azeotropic mixed refrigerant) and counterflow heat exchangers operating with a small temperature difference. Target of this study is development of high performance heat pump system with the 2-stage economizer system using the non-azeotropic mixed refrigerant. For the purpose of excuting target, we constucted computer simulation programs, compared and examed various types of cycle and non-azeotropic mixture. Based on the results from computer simulation we selected optimum mixtures and reflected design and production process of performance test equipment with the 1-stage econmizer system. In order to accomplish the final target, design and production of the 2-stage economizer system, we performed pilot test using the 1-stage economizer performance test system and finally design and production of the 2-stage economizer system.

• Proceedings of the KSR Conference
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• 2008.06a
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• pp.1662-1671
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• 2008

The ERS(Embedded Rail Track system) is constructed in the world due to a slab track system having maintenance free, high structural safety, and deduction of noise and vibration. The ADRI-ERS is developed as Korean type. This paper shows that the design of ADRI-ERS and experiments according to DIN EN 13481-5 and Korea high speed train test guidelines. The ADRI-ERS has high structural safety in pull-out test, longitudinal resistance test, and fatigue test. The design method of ADRI-ERS is proposed by two design constants due to the result of experiments also.

• Journal of the Korea Institute of Military Science and Technology
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• v.14 no.3
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• pp.388-396
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• 2011

Mission Equipment Package(MEP) system is a collection of avionic components that are integrated to perform the mission of the Korean Utility Helicopter(KUH). MEP system development is classified mission-critical embedded system but KUH MEP system developed including flight-critical data implementation. It is important to establish the good development and verification process for the successful system development. This paper describe the development and verification process in each phase for the KUH MEP system. MEP system design is verified through the qualification test, system failure test and compatibility test in System Integration Laboratory(SIL).

• Journal of Aerospace System Engineering
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• v.12 no.1
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• pp.42-46
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• 2018

The subject of this study dealt with the structural safety analysis regarding the measured thrust test equipment as noted on a small engine. In this work, the structural design and analysis of steel and aluminum alloy structure for a small engine test of equipment were performed. Firstly, the structural design requirements of the engine test equipment were identified and investigated. After the structural design was reviewed, next the structural analysis of the engine test equipment was performed by the utilization of the finite element analysis method. The study was performed to determine that the stress and displacement analysis was appropriately managed regarding the applied load condition. As a result, it was determined that through the structural analysis, this study has confirmed that the designed engine test equipment is approved for safety, and meets its design purpose at this time.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2009.04a
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• pp.593-598
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• 2009

In this study we present results for the design of ground test system for 4 degree of freedom(DOF) control test is one of the smart UAV ground test. This system is equipped with real smart UAV and Z direction DOF and 3 direction rotation DOF, Ensuring safe operation of the Smart UAV is a top priority. To this end, it is required to do structure analysis and test verification to confirm the design margin and safety. Based on the analysis, the ground test system has been redesigned to meet the structural conditions.

• The Transactions of the Korean Institute of Electrical Engineers
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• v.37 no.10
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• pp.683-693
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• 1988

For the economical and reasonable operation of electric power system according to continual increase of electric power demand and decrease of load factor, the potential application of superconducting magnertic energy storage [SMES] with high efficiency and fast response in the electric utility is receiving attractive attension. In the light of this background, to confirm the basic principle of SMES, theoretical study, design technique and fabrication procedure for superconducting coil, current lead, cryostat, measuring and protection system of SMES are described in detail. Especially, a new design technique for superconducting coil and current lead is porposed and it was proved experimentally by the performance test of SMES which is developed for the first time in our country. At the peak operating current 200A, the maximum magnetic field amd stored energy of the coil are 3.52T and 2500J, espectively. The thermal and mechanical stability of 2500J SMES is also confirmed experimetally by its characteristics test, AC loss, protection system, charge and discharge test. The experimetal results show good characteristics of energy storage system.

• Transactions of the Korean Society of Automotive Engineers
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• v.9 no.1
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• pp.131-138
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• 2001

The performance analysis of an electronic equipment test is very complicate due to the variety o vehicles. In this study, automatic design system for the electronic equipment test has been carried out using the standard load patterns. For the test, standard signal patterns for each item are modeled. The test items can be decided by the user by means of these patterns. Also, engineering software modules are developed and proved to be very efficient for analyzing the test results statistically. Experiments are performed for the test system in the vehicle assembly line. By analyzing the test results, it is found that bad samples can be detected without failure. Also, the engineering software modules provide an analytical tool for the automation of the test process.

• Current Optics and Photonics
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• v.5 no.2
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• pp.164-172
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• 2021

In this paper a catadioptric laser-irradiation-precision test system is designed, to achieve a high-precision laser-irradiation-accuracy test. In this system, we adopt the method of imaging the entire target surface at a certain distance to realize the measurement of laser-irradiation precision. The method possesses the advantages of convenient operation, high sensitivity, and good stability. To meet the test accuracy requirement of 100 mm/km (0.01%), the coma, field curvature, and distortion over the entire field of view should be eliminated from the optical system's design. Taking into account the whole length of the tube and the influence of stray light on the structure type, a catadioptric system with a hood added near the primary imaging surface is designed. After optimization using the ZEMAX software, the modulation transfer function (MTF) of the designed optical system is 0.6 at 30 lp/mm, the full-field-of-view distortion is better than 0.18%, and the energy concentration in the 10-㎛-radius surrounding circle reaches about 90%. The illumination-accuracy test results show that the measurement accuracy of the radiation hit rate is better than 50 mm when the test distance is 1 km, which is better than the requirement of 100 mm/km for the laser-irradiation-accuracy test.