• Defense and Technology
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• no.7 s.293
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• pp.50-57
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• 2003

이라크 전쟁에서 네트워크 체계는 우주의 인공위성에 의한 정찰과 고고도, 중고도 및 저고도의 용도별 정찰 항공기들로부터 수집한 정보의 분석 및 융합을 거의 실시간으로 처리하여 그 정보를 요구하는 부대에 신속히 전파할 수 있는 네트워크 체계로서 우주선을 활용하여 전파할 수 있으므로 필요한 부대에서 정확한 정보를 이용한 정밀 공격이 가능하였던 것으로 판단된다. 이러한 네트워크 전쟁의 양상으로 판단할 때, 우리 군도 미래 네트워크 전쟁에 대비한 군사력 건설을 강화하여 앞서 언급한 기술들을 기반으로 하는 네트워크 체계 중심의 우주 및 공중 정찰로부터 필수적으로 요구되는 정보를 수집할 수 있는 정보 수집 및 분석/융합 네트워크 체계와 우주 및 공중으로부터 정밀 유도할 수 있는 정밀 유도 네트워크 체계를 건설하여야 할 것이다.

• Journal of Aerospace System Engineering
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• v.11 no.6
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• pp.68-75
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• 2017

In this study, the bolt torque calculation method for space industry was compared and verified experimentally. Currently, NASA, European Aerospace Agency, and US National Defense Standards are proposing standards for bolt torque estimation. However, these standards vary slightly and require a high level of comprehension. To address these challenges, we selected typical equations among the widely-used bolt torque calculation methodologies, and the predicted values were verified via clamping force test. In addition, we examined the changes in clamping force associated with handling and refastening.

• Journal of the Korea Institute of Military Science and Technology
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• v.25 no.1
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• pp.9-22
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• 2022

A fighter performing a reconnaissance mission is equipped with a pod that drives optical/infrared sensors for acquiring and identifying target information on the lower part of the fuselage. Due to the nature of the reconnaissance mission, the fighter performs high speed evasive maneuvers, and the resulting load should be considered importantly for the development of the pod. This paper concerns a numerical investigation into the inertial and aerodynamic loads of the airborne pod of high performance aircrafts. For the aerodynamic load analysis, the pylon and pod shapes are added to the fighter 3D model, and the commercial software was used for static and dynamic analysis. Considering the practical mission conditions, the common/extreme conditions were established respectively in the static and dynamic situations of pods and the driving torque could be tripled under dynamic conditions. In the analysis of inertia load, a 3-DOF model considering roll and turning maneuvers was derived by the Lagrangian method, and then the numerical integration method was applied to the analysis. As a results, it was conformed that the inertia load was generally induced at a low level compared to the aerodynamic load, but depending on the unbalance mass condition of the pod, the inertia load cannot be negligible.

• Journal of Aerospace System Engineering
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• v.17 no.4
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• pp.118-125
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• 2023

The wind tunnel test is one of the essential processes in the development of guided missile systems, and various wind tunnel facilities exist depending on the test requirements, various conditions, and their purposes. The Ludwieg tube is very useful in the development of guided missile systems, and we have necessitated the upgrade of the Ludwieg tube in ADD to acquire various test requirements, such as high angle of attack, repeatability, and stability. In this paper, upgrading the nozzle, vacuum tank, and model support is suggested to improve the Ludwieg tube performance, and we demonstrate a result of the solution through pressure measurement.

• Journal of Aerospace System Engineering
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• v.13 no.5
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• pp.79-86
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• 2019

An anti-collision light of a rotary-wing aircraft is used for the purpose of preventing collision during the operation of an aircraft and is a key component to ensure flight safety. The anti-collision lights of the Korean Utility Helicopter (KUH) consist of upper and lower lights, and the power supply of anti-collision lights mounted on the aircraft. The anti-collision light is designed as a dual structure capable of brightness control and selective lighting. During the operation after delivery of the aircraft, abnormal lighting of anti-collision light occurred. In this paper, a comprehensive review of the aircraft system and component level was conducted to solve these phenomena at first. Then, the causes of anti-collision light anomalies were analyzed and the design changes are presented. The validity of design changes has been verified through the component and aircraft system ground/flight test.

• Journal of Aerospace System Engineering
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• v.16 no.3
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• pp.84-92
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• 2022

The electro-hydrostatic actuator (EHA) recently has been used in flight control fields for aircraft because of its benefits of minimizing oil leakage and weight, improving safety, and etc. while independently operating the hydraulic power source and eliminating complex hydraulic piping. The aircraft of which EHA is installed inside, has the thermal management issue of EHA, because of its limited cooling source as compared with the aircraft which installs the traditional central hydraulic system. So, the thermal analysis model which predicts the thermal characteristics of EHA, is required to resolve this thermal management issue. In this study, an oil circulation circuit inside the hydraulic power module comprised of hydraulic pump and electrical motor for EHA was applied. This is for the purpose of developing the internal rotary group of hydraulic power module, which operates under the conditions of high rotation speed and hydraulic pressure. After formulating an appropriate thermal analysis model, the thermal analysis results with oil cooled or no oil cooled hydraulic control module were compared and reviewed, for the purpose of predicting the thermal characteristics of EHA.

• Journal of Aerospace System Engineering
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• v.18 no.2
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• pp.95-103
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• 2024

The propulsion technology used in unmanned Aerial Vehicles (UAVs)—which represent one of the most important development directions in aviation—is significantly related to their flight performance. This review paper discusses the different types of propulsion technologies used in unmanned aerial vehicles, namely the internal combustion engine (reciprocating, rotary, and gas turbine engines), the hybrid system, and the pure electric system. In particular, this paper presents and discusses the classification, working principles, characteristics, and critical technologies of these types of propulsion systems. These findings are expected to be helpful in establishing a development framework, comprehensive views, and multiple comparisons of future UAV propulsion systems.

• Journal of Aerospace System Engineering
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• v.13 no.1
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• pp.62-68
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• 2019

The software installed on an aircraft is directly related to its safety. Therefore, it shall comply with the standards of the airworthiness certification to ensure safety of flight. Airborne software should be developed in accordance with the DO-178 (Software Consideration in Airborne Systems and Equipment Certification) to comply with the airworthiness certification criterion. However, the military airborne software has been developed in accordance with the DAPA weapons system software development and management manual. In this paper, we completed a questionnaire survey of software experts. We also suggest a military airborne software development/certification process based on DO-178.

• Journal of Aerospace System Engineering
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• v.16 no.6
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• pp.18-23
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• 2022

This paper examines the electromagnetic shielding structure of ultra-high frequency (UHF) RF modules used in aircraft. Advances in electrical and electronic technologies have increased the need for electronic equipment in aircraft. High-frequency wireless devices have become integrated circuits in the form of UHF integrated circuits to support a wide range of frequencies and miniaturisation. To ensure the functionality and performance of these integrated devices in aviation, shielding is necessary to prevent unexpected electromagnetic interference, which could be detrimental to aircraft safety. A shield structure was designed to protect the RF chipset from malfunctioning, and the shielding effectiveness was improved through the application of various geometric shapes.

• 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.