• Transactions of the Korean Society for Noise and Vibration Engineering
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• v.18 no.12
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• pp.1278-1285
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• 2008

This paper presents an inertia type of piezostack based active mount fur unmanned aero vehicle (UAV) camera system. After identifying the stiffness and damping properties of the rubber element and piezostack a mechanical model of the active mount system is established. The governing equation of mount is then derived and expressed in a state space form. Subsequently, a sliding mode controller which is robust to uncertain parameters is designed in order to reduce the vibration imposed according to the military specification associated with UAV camera mount system operation. Control performances such as acceleration and transmitted force are evaluated through both computer simulation and experimental implementation.

• Elastomers and Composites
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• v.5 no.1
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• pp.62-68
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• 1970

The physical properties of tire and tube products as a series of experiments have been studied and practical usage has been discussed. 1. The tensile strength and elongation of experimental production of tire and tube revealed better values than those found in requirements of military specification. 2. Adhesion of carcass plies with domestic and foregin cords showed good results in physical properties. 3. Tensile strength of carcass plies, tenacity of domestic cord and breaking energy of tire be exhibited good results.

• Journal of the Computational Structural Engineering Institute of Korea
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• v.24 no.5
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• pp.521-530
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• 2011

Since aircraft fuel tanks have many interfaces connected to the airframe as well as the fuel system, they have been considered as one of the system-dependent critical components. Crashworthy fuel tanks have been widely implemented to rotorcraft and rendered a great contribution for improving the survivability of crews and passengers. Since the embryonic stage of military rotorcraft history began, the US army has developed and practised a detailed military specification documenting the unique crashworthiness requirements for rotorcraft fuel tanks to prevent most, hopefully all, fatality due to post-crash fire. The mandatory crash impact test required by the relevant specification, MIL-DTL-27422D, has been recognized as a non-trivial mission and caused inevitable delay of a number of noticeable rotorcraft development programs such as that of V-22. The crash impact test itself takes a long-term preparation efforts together with costly fuel tank specimens. Thus a series of numerical simulations of the crash impact test with digital mock-ups is necessary even at the early design stage to minimize the possibility of trial-and-error with full-scale fuel tanks. In the present study the crash impact simulation of a few fuel tank configurations is conducted with the commercial package, Autodyn, and the resulting equivalent stresses and internal pressures are evaluated in detail to suggest a design improvement for the fuel tank configuration.

• Journal of Aerospace System Engineering
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• v.16 no.4
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• pp.95-108
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• 2022

Airworthiness certification is critical, in ensuring the flight safety of military aircraft for development tests and production operations. The MIL-HDBK-516C, latest airworthiness certification document, handles the field of flying qualities in Chapter 6 (flight technology), and refers to specific chapters of MIL-STD-1797B, which is the specification document for developing military aircraft. Since the MIL-STD-1797B released in 2006 by the U.S. Department of Defense is not disclosed to other countries, the Chapter 6 (flight technology) of MIL-HDBK-516B Expanded, the former certification standards pursuant to flying qualities, has to be applied to military aircraft being developed in the Republic of Korea. However the requirements of Chapter 6 of MIL-HDBK-516B Expanded comprise unclear sentences, because of contents from various development specifications. Also, clarification is needed in that the same requirements have to be verified in different criteria. In this paper, the results of this study present an effective verification method, for acquiring the airworthiness certification in field of flying qualities based on MIL-HDBK-516B Expanded.

• Journal of the Korea Institute of Military Science and Technology
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• v.20 no.1
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• pp.1-11
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• 2017

In this paper, design requirements of the large radar were investigated, and development was performed through the analysis and design. Large radar should be designed by bearing the 75 knot wind force and $20kg/m^2$ ice mass as operating conditions in order to meet structural stability, and driving torque and bearing load were calculated for securing the driving stability. Thermal dissipation analysis was performed considering TRM and DC-DC Converter's limitation temperature by $50^{\circ}C$ ambient temperature condition in order to attain thermal stability, and PSD and shock analysis were carried out by using MIL-STD-810G vibration and shock specification in order to transport and installation of the large radar. As a result, all components of large radar could secure the structural stability more than 2.8 factor of safety, and driving stability was also secured with adequate bearing fatigue life. Thermal stability was attained by allowable max temperature 88.7 C of the TRM, and structural stability for transportation and installation of the large radar was also secured more than 5 factor of safety. After it was transported and installed to the radar site, operating capability was finally verified by rotating the large radar.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.37 no.11
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• pp.1047-1051
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• 2013

A modern combat vehicle needs to have a separate air-conditioning unit, although new combat systems tend to employ an integrated heating, cooling, and ventilating system. In this study, we investigated an air conditioning unit for an armored combat wheeled vehicle as a special use and military specification and performed a case study of a unique military combat vehicle. By using Fluent software, we tried to determine a suitable air ducting method and its location in the armored combat vehicle. The results show that an air-conditioning unit is one of the best solutions for wheeled vehicles that are not equipped with a cooling unit for their crews, and it can be applied to similar types of armored vehicles.

• Journal of Korean Society for Quality Management
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• v.48 no.1
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• pp.149-169
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• 2020

Purpose: This study analyzes the characteristics of the Quality Management performed by SMEs in the Defense Industry in supply chains and analyzes the effect of the continuous improvement activities based on cooperation. Especially, for Military Supplies, the suitability of products is usually decided by judging their conformity to the specification, and from this structural characteristic, this study would analyze the structural relationship of systematic improvement activities with Supply Chain Quality Management(SCQM) and Business Performance(BP). Methods: Continuous improvement activities(CI) have significance as the driver force for the promotion of Quality Management. Thus, this study analyzed the causal relationships from the perspective of the process among CI, SCQM and BP. For an analysis of the structural characteristics and causal relationships among the constituents, AMOS was used, and 297 companies in the Defense Industry were utilized as samples. Results: It turned out that CI had significant impacts on Management Infra(MGT_Infra), Process Management(PM), Human Resources Management(HRM) and Communication(COMU) and had an indirect impact on the enterprises' financial performance through the parameters of HRM and Communication. Meanwhile, it turned out that between CI and non-financial performance, there was a direct effect, and there was also an indirect effect through the variables of the Management Infra and Communication. Conclusion: It turned out that CI had a positive effect on SCQM as a proactive driver and that they had significant relationships with BP(financial, Non-financial), both financial performance and non-financial performance. However, PM did not have a significant relationship of effect with BP because of the character appearing by the evaluation method of military supplies for the conformity to the specifications.

• Journal of the Korea Institute of Military Science and Technology
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• v.17 no.2
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• pp.223-234
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• 2014

This paper proposes a flexible and highly reusable modeling methodology for a next-generation combat entity which enables joint analysis of performance/engagement effectiveness. According to the scope of the proposed work, the paper is divided into two parts; Part 1 focuses on a conceptual model design, whereas Part 2 proposes detailed model specification and implementation. In Part 1, we, first, classify the combat entity model as combat logic and battlefield function sub-models for joint analysis. Based on the sub-models, we propose two dimensional model partition method, which creates six groups of a single combat entity model by two dimensions: three-activity and two-abstraction. This grouping enables us to reconfigure the combat entity model by sharing the same interface within the group, and the same interface becomes the fundamental basis of the flexible model composition. Furthermore, the proposed method provides a model structure that effectively reflects the real world and maximizes the multi-level reusability of a combat entity model. As a case study, we construct a model design for anti-surface ship warfare. The case study proves enhancement of model reusability in the process of scenario expansion from pattern running to wire guided torpedo operations.

• 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.

• Korean Journal of Materials Research
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• v.14 no.3
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• pp.168-174
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• 2004

The aim of this study is to investigate the effect of process conditions on the microstructual changes and mechanical properties of large 7175 aluminum die forgings. The cast billets of 370 and 720 mm in diameter were homogenized and die forged after direct chill casting. The size and volume fraction of second phase particles in 720 mm billet were larger than those of 370 mm billet. The interdendritic sites containing the second phase particles was considered to be a crack initiation region in the process of cold upsetting. The tensile and yield strength of die forged specimens of 720 mm billet in the direction of Land L T were higher than those of 370 mm billet. However, the tensile strength of these specimens were 5 to 10% lower than that of American military specification. The plane strain fracture toughness of die forged specimens of 370 mm cast billet showed almost the same level of 720 mm billet, which was die forged after free forging.