• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.656-657
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• 2010

The ground oxidizer supply system in the launch site of NARO space center had operated 9 times from the start of tests with ILV on May, 2009 to the 2nd flight test of the NARO vehicle. This system operated successfully for twice launches of the NARO vehicle. To judge the successful operation of the ground facility, it should have reproducibility and reliability. In this report, we have analyzed the liquid oxygen consumption of the system to judge of its reproducibility and it can be a reference for using this system for the next generation of KSLV system.

• Aerospace Engineering and Technology
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• v.9 no.1
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• pp.151-157
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• 2010

The tracking radars in NARO space center are precious, long-range tracking systems for tracking the launch vehicle (KSLV-1) and transmitting TSPI (Time, Space and Position Information) data to MCC (Mission Control Center). Because TSPI data from tracking radars to MCC are important information for the launch mission and flight safety control, TSPI data are required to be more accurate. In this paper, we analyzed theoretically the required specification of the random noise error in tracking radar and verified the real random noise error. In this analysis, we evaluated the TSPI data of several flight tests performed in NARO space center.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.14 no.3
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• pp.1-6
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• 2006

The altitude engine test is a sort of engine performance tests carried out to measure the performance of a engine at the simulated altitude and flight speed environments prior to that at the flight test. During the performance test of a engine, various values such as pressures and temperatures at different positions, air flow rate, fuel flow rate, and the load by thrust are measured. These measured values are used to derive the representative performance values such as the net thrust and the specific fuel consumption through a momentum equation. Hence each of the measured values has certain effects on the total uncertainty of the performance values. In this paper, the combined standard uncertainties of the performance variables at the engine test were estimated by the uncertainty analysis of the measurement values and the repeatability and reproducibility of the altitude test measurement were assessed by the analysis of variation on the repeated test data with different operator groups.

• Journal of Korean Society for Quality Management
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• v.47 no.3
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• pp.467-478
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• 2019

Purpose: The purpose of this paper is to improve quality for water infiltration to FCISA during military aircraft operation. Methods: A series of troubleshooting studies were conducted to identify the root cause of the water infiltration and reproduce the defects through various simulation tests. And design improvement measures were derived, and countermeasures were taken to prevent recurrence of moisture inflow defects. Conclusion: FCISA operates a very important role in the operation of military aircraft, and defects due to water infiltration are very fatal to flight safety. In this study, the root cause was identified and the design improvement to prevent recurrence was carried out through the failure investigation performed in this study, and the FCISA was improved so that the flight safety was not affected. The results of this study will be valuable back data that can be reflected in the design process through Lessons-Learned in the design phase of the aircraft that will be developed in the future.

• Journal of the Korean Society of Propulsion Engineers
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• v.22 no.4
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• pp.91-98
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• 2018

A numerical investigation of stage separation behavior of a two-body vehicle focusing on its flow characteristics is carried out. For this simulation, the separation of a booster from a vehicle is modeled using a chimera grid system and calculated with commercial code, $CFD-FASTRAN^{TM}$. Consideration of spring force, gravity and relative acceleration of a booster is the essential factor of a realistic simulation. In this study, it is validated that the booster separation time decreases with an increase in flight Mach number and angle of attack. In view of results thus far achieved, it is expected that the dynamics modeling and boundary condition set-up applied in this study will be useful for estimating safe stage separation and event sequencing of flight tests.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.47 no.7
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• pp.499-507
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• 2019

Despite the well-known mathematical model of fixed-wing aircraft, there are various studies to meet desired performances by considering the modeling errors in the extended flight envelope. This paper proposes a new adaptation mechanism of model-reference adaptive control, which applies the Levenberg-Marquardt algorithm to the pitch attitude control of fixed-wing UAV. In addition, reference model in the adaptation law is set by referring to the dynamic properties of the plant model. The performance of the proposed adaptive control law is verified through simulations and flight tests.

• The Journal of Asian Finance, Economics and Business
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• v.8 no.4
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• pp.433-440
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• 2021

This study aims at testing word-of-mouth (WOM) by mediating positive and negative perceptions of purchase intention on low-cost carriers (LCC) flights in Indonesia. One of the communications mixes that airlines can carry out is WOM. WOM is a form of communication between passengers after using a flight. The formation of a positive perception of WOM is expected by airlines. If a positive perception of WOM has formed, a purchase intention will arise. The study population included LCC flight passengers in Indonesia, involving 387 respondents. For indicators and variables, validity and reliability tests were conducted using CFA, CR, and AVE tools. Sampling locations were Soekarno-Hatta and Kualanamu airports. Sample collection was obtained through purposive sampling, and the analytical tool used was structural equation modeling (SEM) with Lisrel. The results showed that WOM influenced purchase intention through positive and negative perceptions of WOM. It can be seen that a positive perception of WOM has a direct effect, while a negative perception of WOM has the opposite effect. In conclusion, the mediation of perceptions influences purchase intention, whether it in the same direction or the opposite ones. To conclude, WOM is an antecedent for it influences purchase intention.

• International Journal of Computer Science & Network Security
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• v.22 no.2
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• pp.357-361
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• 2022

Employing the available technologies and utilizing the advanced means to improve the level of health care provided to citizens in their various locations. Citizens have the right to get a proper health care services despite the location of their residency or the distance from the health care delivery centers, a goal that can be achieved by utilizing air ambulance systems. In such systems, aircrafts and their life spans are the essential component, the flight duration of the aircraft during its life span is determined by the maintenance schedule. This research, enhances the air ambulance systems by presenting a proposal that maximizes the aircraft flight duration during its life span. The enhancement will be reached by developing a set of algorithms that handles the aircraft maintenance problem. The objective of these algorithms is to minimize the maximum completion time of all maintenance tasks, thus increasing the aircraft operation time. Practical experiments performed to these algorithms showed the ability of these algorithms to achieve the desired goal. The developed algorithms will manage the maintenance scheduling problem to maximize the uptime of the air ambulance which can be achieved by maximizing the minimum life of spare parts. The developed algorithms showed good performance measures during experimental tests. The 3LSL algorithm showed a higher performance compared to other algorithms during all performed experiments.

• Journal of the Korean Society of Manufacturing Process Engineers
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• v.21 no.8
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• pp.53-59
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• 2022

In this study, an experimental device was fabricated to evaluate the hovering flight performance of a single rotor on a hexacopter used for river surveillance, and a thrust performance test was conducted. In addition, the 3D profile of the propeller was extracted by 3D scanning and CFD analysis was performed using ANSYS CFD 14.5 based on the extracted 3D model of the propeller. The aerodynamic characteristics were compared with the results of the performance tests and CFD analysis, and the vortex structure corresponding to each motor rotational speed in revolutions per minute (rpm) was identified. In the future, we plan to provide valuable data for multicopter propeller design and performance verification.

• Journal of Aerospace System Engineering
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• v.17 no.1
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• pp.97-105
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• 2023

For aviation sensor pod, structural integrity should be verified through static structural tests for flight loads induced in various maneuvering conditions of the aircraft. For this, it is necessary to develop a test system for full-scale static load test of sensor pod. Based on test requirements, this paper introduced a test system configuration of the static test and the development of test structure frame, restraints equipment, loading equipment, control, and measurement equipment. In addition, methods and procedures for verifying the developed test system were explained. In conclusion, the static load test and data acquisition were successfully performed. Reliability of the test equipment was also verified in the process.