• Journal of Applied Reliability
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• v.9 no.2
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• pp.81-91
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• 2009

This paper presents the comparison of climatic environmental tests of IEC Pub. 60068 and MIL-STD-810. Cold, dry heat, change of temperature, and heat-humidity cyclic tests are compared in terms of the types of tests and test severities. This study shows the difference between the standards, which will provide the useful information to the industries and be helpful in applying the standards.

• Journal of Applied Reliability
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• v.18 no.2
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• pp.95-103
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• 2018

Purpose: Environment test aim to validate the guarantee of required capability of materiel against various environment conditions which exposed during materiel life-cycle. In this paper, environment test design procedure and tailoring guideline for Korean peninsula and periphery climate are proposed. Methods: To design tailoring guideline, climate data which are regarding Korean peninsula and periphery regions provided from Korea Meteorological Administration (KMA) and National Climatic Data Center (NCDC) are used. Conclusion: For effective environment test, it is important that environment test have to design in considering environment conditions during materiel life-cycle. It is concluded that the high temperature test level can be softer than the test criteria in MIL-HDBK-310, however, the low temperature test level will be expected to be $2{\sim}6^{\circ}C$ harsher than MIL-HDBK-310.

• Journal of Applied Reliability
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• v.6 no.2
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• pp.105-113
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• 2006

• Journal of Applied Reliability
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• v.6 no.1
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• pp.1-11
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• 2006

• Journal of the Korea Institute of Military Science and Technology
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• v.24 no.6
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• pp.569-576
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• 2021

Radar is a ground defense system that detects enemy aircraft and receives power from a mobile power supply in an emergency. Serious problems may occur if the equipment is damaged by impact during transportation for use. The US military standard MIL-STD-810H contains information on environmental tests such as shock and vibration applied to munitions. Therefore, in this study, the transient analysis of ANSYS 19.2 was performed using the impact data specified in MIL-STD-810H as an input value. Through this, the maximum stress generated in the impact environment of the mobile power supply container was derived, and the safety margin was calculated to confirm the reliability of the container.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.50 no.10
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• pp.739-745
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• 2022

In various environmental requirements of a fighter aircraft, the explosive atmosphere is a test to verify whether or not military products are ignited for the safety of the aircraft system and crew. For the test, the explosive atmosphere test chamber owned by the Korea Institute of Industrial Technology (KITECH) was applied, and n-hexane, which has more sensitive ignition characteristics than general fuel, was used to conduct the test conservatively. Based on Procedure I, Method 511.6, MIL-STD-810G w/Change 1, the US military environmental test specification, the scope of application, tailoring guide, and detailed test procedures are checked, and the necessity of this test for each subsystem of the fighter aircraft is considered. In this study, we present the correct tailoring method by analyzing the explosive atmosphere test results for the components installed in the fighter aircraft and sharing the derived essential points.

• Journal of the Korean Society of Systems Engineering
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• v.16 no.2
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• pp.78-86
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• 2020

The environmental tests are one of the key branches of the reliability tests. The purpose of the high/low environmental test of KT-1 Export Version Trainer is not only based on meeting the compliance of the reliability, customer satisfaction, but also for the expansion of its export. Amongst many existing environmental tests, the high and low temperature tests are considered as the two most important tests. The tests are considered and tailored to the high and low temperature methods of MIL-STD-810H. This paper proposes the tailoring processes and the results of High/Low temperature conditions, test procedures, and test profiles for the aircraft. Additionally, this paper is described by considering the view of MIL-STD-810H.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.11a
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• pp.403-406
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• 2009

This research is based on the altitude temperature, pressure and humidity, as defined by MIL-HDBK-310 standard and modifies this conditions to conform to the new standard MIL-STD-810F and test procedure given in AIAA-2466 from this fundamental guideline optimal design and sizing of test section, inlet, exhauster duct, temperature and humidity control was performed.

• Journal of Aerospace System Engineering
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• v.13 no.3
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• pp.87-94
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• 2019

In this paper, we test procedures to demonstrate operating environmental conditions that can be exposed to UAV during its life-cycle are proposed. They are set up to be used in a large-sized climate chamber, one of the facilities of the Agency for Defense Development corresponding with the system requirements. The test steps and profile details were more specifically suggested for rainfall, humidity, and temperature (low-temperature storage and operation, high-temperature operation and solar radiation), and MIL-STD-810G w/Change-1-based.

• 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.