• Journal of the Korean Society for Precision Engineering
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• v.33 no.10
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• pp.781-787
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• 2016

We introduce FEST (Flight Environment Simulation Test) procedures for precise guided missiles to reliably improve systems. Flight vibration specification was established based on power spectral density curves calculated from flight test data of a high speed precise guided missile. A FEST pre-profile was developed according to flight vibration specification and delivered to a precise guided missile assembly. Vibration responses were measured by installing accelerometers on electronic components vulnerable to dynamic forces. The FEST profile was adjusted by comparing the vibration responses and the flight vibration specification. Subsequently, the FEST profile was repeatedly modified through trial and error, because the responses were similar to the flight environment. The modified FEST profile enabled performance testing of assembled precise guided missiles under simulated flight conditions on the ground, where unexpected errors could be corrected before the flight tests, leading to cost and risk reduction in the development of the precise guided missile system.

• Proceedings of the Korean Institute Of Construction Engineering and Management
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• autumn
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• pp.491-494
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• 2003

Curtain wall (for the outside wall) must be designed and constructed to resist weather condition of nature like rain. wind and surrounding environment. So, Now days, Mock-up test of curtain wall's total capability is generally used for skycraft building. But, Mock-up test specification in korea is so weak that there are lots of disputation. Also, lacking of clearness in specification causes many trouble in adaptation. Therefore, I would like to consider the problem of Mock-up test specification by inspecting and comparing with other country's works. and I will mention the way of approvement in our specification.

• Journal of Food Hygiene and Safety
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• v.22 no.1
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• pp.52-56
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• 2007

In order to offer monitoring data about standard and specification of metallic kitchenware, we carried out the material test and migration test of lead and antimony in 71 kinds of kitchenwares. As a result of this study, Pb was detected less than 0.06% at the material test and Sb was not defected in 71 kinds of kitchenwares. Pb was also detected less than 0.41 mg/L at the migration test. Currently according to the Food Code of Korea, Pb and Sb in metal product shall not exceed 10% and 5%, respectively and Pb migrated from metal product shall not exceed 1.0 mg/L. Therefore, our all data are not exceeding the standard and specification of metal product and show that all the kitchenwares in domestic circulation may be safe.

• Transactions of the Korean Society of Automotive Engineers
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• v.7 no.5
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• pp.213-220
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• 1999

The life data analysis of the system and component are useful to describe the result of reliability test in product life to satisfy customer's growing need and to change test specifications or design criteria by life data analysis. And vehicle durability tesr occurred market environment. In this study, a statistical analysis for the wear life of brake pad linings helped perform correlation procedure between vehicle durability test and market. B-life values of the brake pad wear life data from both vehicle durability test and marker usage were compared to determine acceleration of the test by the Weibull, normal and log-normal distribution. The acceleration coefficient of the vehicle durability test can access to evaluate design criteria of product and test specification.

• Aerospace Engineering and Technology
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• v.7 no.1
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• pp.142-150
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• 2008

In order to ensure the individual and mutual performances among the telemetry system, tracking system, flight termination system, GPS, and inertial navigation & guidance system which are installed in the KSLV-I 2nd stage and ground equipment of the Naro space center, flight test using a light airplane is required. Since the high degree of test efficiency is fulfilled through the minute plan and analysis about selection of the equipment which are applicable to the test, harness, operation strategy, and antenna installation. KSLV-I communication environment and flight profile should be precisely taken into account during the flight test. In this document, overall aspect of the KSLV-I 2nd stage equipment specification, a rack for the installation, harness, the airplane specification, and flight route which are required for the effective flight test are presented.

• Journal of Aerospace System Engineering
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• v.1 no.4
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• pp.22-27
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• 2007

The 150 gal Ion EFT(External Fuel Tank) used to enlarge the aircraft operation range was adopted an import equipment in T-50 FSD phase. But in Production phase the EFT was planed to develop for the stable ILS(Integrated Logistics Support) and technical ability improvement by using the composite materials. The design for configuration and fuel system is intended to maintain compatibility with aircraft systems and the development test is performed on component, assembly and aircraft. This study is conducted to provide the technology of design and test for the 150 gallon composite EFT in LRU level. The test results show that the composite EFT is satisfied with structural, functional and environment requirements which are described in specification.

• Proceedings of the Korean Institute of Navigation and Port Research Conference
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• v.2
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• pp.273-278
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• 2006

In order to use a GPS antenna for launch vehicles, it should be installed on the skin of the vehicle and be able to normally receive the live GPS signals during the vehicle's full flight mission. The GPS antenna on the surface of the launch vehicle is, however, exposed to higher temperature than inner equipments of the vehicle due to aerodynamic heating generated during the flight. Test specification of the GPS antenna for qualification of hot-temperature is determined to $+95^{\circ}C$ that is higher than inner components by $25^{\circ}C$. Test results in this paper show that the GPS antenna normally operates under the above environment.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.41 no.11
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• pp.915-920
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• 2013

Units developed for a real satellite should pass space environmental tests and launch environment tests. Thermal Vacuum Test, one of the space environmental test, simulates extreme thermal environment encountered in on-orbit operation of satellite. Many payloads which adapt non-traditional, brand-new technology are developed by developers who is not familiar to space engineering field. There might be some possibility of mistakes which result in serious problem due to lack of experience, especially from planning to performing thermal vacuum test. In this paper, brief overview of thermal environmental test related to a satellite development is summarized in order to prepare and perform the thermal test.

• Journal of Environmental Impact Assessment
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• v.4 no.2
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• pp.123-130
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• 1995

The equipment composed of many complicated electronic stuffs undergoes diverse stresses caused by mechanical vibrations during its service. Thus, to ensure its proper operation in the field a simulated vibration test has to be carried out in the laboratory with the Vibration Qualification Level, the test specification, which can include the real environment. In this paper we intent to deal with method and procedure for determining the Vibration Qualification Level so as to estimate the vibration-endurance for the equipment precisely.

• Journal of the Korea Institute of Military Science and Technology
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• v.24 no.3
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• pp.302-308
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• 2021

Developers generally use test standards suggested by military standards such as MIL-STD-810G when performing vibration tests in the materiel development. However, according to MIL-STD-810G, it is recommended to test by tailoring the test standard suitable for the developed materiel, and it is specified to apply the suggested test standard only when there is difficulty in tailoring. In addition, the test standards presented by MIL-STD-810G are standards created under operating conditions different from the actual operating environment of each developed materiel, so the test according to this standard may be excessive or understated. Therefore, the developer must create an appropriate vibration test standard for the developed materiel as similar to the operating conditions as possible. In this paper, the procedure for creating the functional test standard and durability test standard suitable for the operating environment of the equipment to be mounted on the propeller aircraft under development is described, and the created standard is introduced.