• Journal of Aerospace System Engineering
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• v.18 no.3
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• pp.76-85
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• 2024

Recently, from a global perspective, the use of small unmanned aerial vehicles in terrorism and warfare is increasing, and the need for anti-drone shooting training targeting small UAVs is increasing. However, in reality, there are many cases in Korea where anti-drone shooting training is restricted, due to complaints such as noise. In this paper, we describe the development and testing of an electric-powered direct strike type high-speed, low-noise small aerial target drone. To achieve the flight speed and endurance required for shooting training, target drone sizing was performed, and aerodynamic performance analysis was conducted using a CFD program. Based on the performance analysis, the motor propulsion system was selected and a variable pitch propeller system was designed, and performance tests were performed on a ground test rig. Finally, the target flight speed, flight time, and flight noise level were confirmed through flight tests.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.15 no.12
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• pp.7204-7213
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• 2014

This study examined the impact on work life on health recognition and health behavior practices. The data was collected from 314 flight attendants from June to July 2014 in A airline. Questionnaires were used to measure the levels of health recognition, health behavior practice, Stress index, external image, and the impact on the work life. The data was analyzed using descriptive statistics, T-test, ANOVA, Pearson's correlation, structural equating model using the SPSS AMOS 18.0 program. The research showed that health care influences the external image and work life, and the health behavior practice influences the stress management. A survey of the various influencing factors of work life will be needed in terms of human resource management to provide quality service to customers, and health care programs for flight attendants in workplace will be needed.

• Journal of Aerospace System Engineering
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• v.2 no.4
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• pp.13-18
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• 2008

Airworthiness is a term used to dictate whether an aircraft is worthy of safe flight. It is illegal in most countries to fly an aircraft without first obtaining an airworthiness certificate from the responsible government agency. For developing an aircraft, the design modifications and upgrades are considered a high financial risk proposal for most Program Managers(PMs). However Design-to-Certification Integrated System can be a great help in achieving a good design solution in an acceptable amount of time and flight test. In this paper, we present a method to construct database for the Development of Design-to-Certification Integrated System. By using this database, the human designer could manage and find the regulation and requirements related with his concern effectively.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.35 no.10
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• pp.940-947
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• 2007

For the performance upgrade of a supersonic jet fighter, the processor and FLCC(Flight Control Computer) Architecture were upgraded from a baseline FLCC. Prior to the hardware implementation phase, the exact CPU throughput estimation is necessary. For this purpose, an experimental method for new FLCC throughput estimation was introduced in this study.　While baseline FLCC operating, the CPU address bus was collected with logic analyzer, and then decoded to get the exact access times to each memory-memory and the number of program Instruction branches. Based on these data, a throughput test in CPU demo-board of the new FLCC configuration was performed. From test results, the CPU-Memory architecture was design-changed before FLCC hardware implementation phase. To check the flight stability degradation due to power-interrupt problem due to CPU-Memory architecture change, the piloted HILS (Hardware-In-the Loop Simulator) test was conducted.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.46 no.11
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• pp.944-951
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• 2018

Artificial icing test and wind tunnel test can be performed to reduce the development period when a rotorcraft is required operation under icing situations. Artificial icing test of the KUH(Korean Utility Helicopter) was performed in advance to verify anti-icing and de-icing performance before natural icing test. Although high-precision sensor, the CCP(Cloud Combination Probe) is used to measure icing test condition parameters such as LWC(Liquid Water Content) and MVD(Median Volume Diameter), the measured values need to be verified in various methods due to the possibility of uncertainties which are the test atmosphere environment, sensor errors, and etc. The calculated LWC from the ice thickness cumulated on the fuselage of the KUH is compared to the measured value by CCP, and the results show the effective indirect method to check the test conditions.

• Journal of dental hygiene science
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• v.15 no.5
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• pp.636-641
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• 2015

The purpose of this study was to examine the oral health recognition and aesthetic interest of flight attendant. The data was collected 314 flight attendant from June to July 2014 in A Airlines. Questionnaires were used to measure the levels of the health & oral health recognition, experience and requirement of oral esthetic therapy. The data was analyzed using descriptive statistics, T-test, ANOVA, Pearson's correlation, structural equating model by the PASW Statistics 18.0 program. According to the research result, oral health awareness were not healthier than general health. Oral health was an important factor to influence the external image. The flight attendant received aesthetic dental care to improve the external image. However, self-assessment results that oral health condition was significantly lower. Therefore they are required oral care practice with aesthetic dental care.

• 시스템엔지니어링워크숍
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• s.4
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• pp.17-22
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• 2004

This paper present the brief generation process of system requirements or mart UAV from a development obejective. The current Snart UAV requirements deal with the restricted life cycle from development to test and verification exclusive of full life cycle beacuse of the new technology demonstration research program funded by goverments. The Smart UAV system consists of flight vechicle, avionics, communication link, payload, ground control stationand ground supporting system. In thus paper, top-down flown requirememts are intoduced how to allocate to each sub-system.

• International Journal of Aerospace System Engineering
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• v.2 no.2
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• pp.87-91
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• 2015

KT-1P for the Peru Air Force will be used as a utility aircraft with upgraded avionics equipment and arming capability based on KT-1 and KA-1. KT-1P should be shown for compatibility of new store loading configurations loaded with dispenser, bomb, and rocket based on aircraft-store compatibility test and evaluation procedures before KT-1P is operated as a light attack aircraft. The weapon system ground test for installation and flight test for envelope expansion including store separation are described in this paper, which was performed referring 'seek eagle program' under MIL-HDBK-1763 and MIL-HDBK-244A.

• Journal of the Korea Institute of Military Science and Technology
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• v.5 no.2
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• pp.123-131
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• 2002

ASC(Avionics System Computer) was developed to control weapon delivery and navigation sensors, and to perform man-machine interface with pilots for XKO-1 aircraft. The data communications between ASC and UFC(Up Front Controller), DC(Data Concentrator) were implemented by RS422 serial data bus. Also, SCIL(Standard Computer Interface Library) was designed to facilitate control and management of the computer hardware resources and is embedded in the ASC. These structures have a merit of noise immunity and a reduction of wire harness for signal lines, and enable OFP(Operational Flight Program) programmers to use the SCIL easily without knowing hardware details. Manufactured system was on installed on XKO-1, and peformed for BIT(Built In Test) and interface test with UFC and DC. The test results show that it meets the system requirements.

• International Journal of Aeronautical and Space Sciences
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• v.18 no.2
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• pp.365-377
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• 2017

In this paper, we propose a method to identify the parameters of a rotorcraft slung load system using the modal characteristics of a flexible cable. The proposed method estimates the length of the cable and the mass of the payload by means of a frequency analysis. Dynamic equations of the slung load system with the flexible cable are derived using Udwadia-Kalaba equation (UKE) in order to build a simulation program, and the similarity of the simulated slung load movement is verified by comparison with flight test results. Using the computer simulation program, we show that the proposed method works well within various parameter ranges.