• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.43 no.9
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• pp.765-772
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• 2015

Aerodynamic force measurements and phase-locked PIV study were carried out to check the bio-mimetic MAV applicability of a swift flight. Two-rotational DOF robotic wing model and blowing-type wind tunnel were employed. The amplitude of twist angle were ${\pm}0$, ${\pm}5$, ${\pm}10$, and ${\pm}20$ deg. and stroke angles were manipulated by simple harmonic function with out-of-phase in regards to the stroke motion. It is acknowledged that the time-varying lift coefficients in accordance with the change of the twist angle did not result in any noticeable differences, just the small decrease and delay. However, the drag exhibited that the small change of the twist angle can produce large thrust. These findings imply why a swift uses small twist angle during flight. The PIV results displayed that the delay of aerodynamic forces is highly associated with the vortical structures around the wing. It is therefore indicated that a process of designing a swift-based Micro Air Vehicle should take the twist angle into consideration, as the essential parameter.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.50 no.3
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• pp.181-192
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• 2022

Active vibration control system(AVCS) for helicopter enables to control the vibration generated from the main rotor and has the superb vibration reduction performance with low weight compared passive vibration reduction device. In this paper, FxLMS algorithm-based vibration control software of the light civil helicopter tansmits the control command calculated using the signals of the tachometer and accelerometers to the circular force generator(CFG) is developed and verified. According to the RTCA DO-178C/DO-331, the vibration control software is developed through the model based design technique, and real-time operation performance is evaluated in PILS(processor in-the loop simulation) and HILS(hardware in-the loop simulation) environments. In particular, the reliability of the software is improved through the LDRA-based verification coverage in the PIL environments. In order to AVCS to light civil helicopter(LCH), the dynamic response characteristic model is obtained through the ground/flight tests. AVCS configuration which exhibits the optimal performance is determined using system optimization analysis and flight test and obtain STC certification.

• Journal of the Society of Naval Architects of Korea
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• v.61 no.5
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• pp.312-323
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• 2024

This study aims to evaluate the safe operating envelope (SOE) for light aircraft carriers using a computational fluid dynamics (CFD) modeling database of flight deck air-wake. Assessing the SOE is crucial for ensuring the safe operation of carrier-based aircraft, particularly during take-off and landing maneuvers. Traditional methods that only consider relative wind envelopes (RWE) provide basic information but fail to account for the complex airflow patterns over the flight deck. To address this limitation, this research utilizes CFD to analyze the air-wake and integrate these findings into the SOE assessment. Various studies on CFD modeling of airflow around naval ships and aircraft carriers were reviewed, confirming the importance of accurate airflow databases for operational safety. This study employs the KRISO-CVX1 model, a light aircraft carrier designed by the Korea Research Institute of Ships & Ocean Engineering (KRISO), to demonstrate the application of CFD data in SOE evaluations. The methodology involves a detailed analysis of turbulent flow and thermal fields around the carrier deck under different wind speed, direction, and ship speed conditions. The results indicate significant variations in air-wake characteristics depending on the relative wind speed and direction, impacting the operational safety of carrier-based aircraft. This study emphasizes the need for incorporating CFD-based airflow data into SOE assessments to enhance the accuracy and reliability of operational safety evaluations for aircraft carriers. In conclusion, the integration of CFD air-wake modeling databases provides a more comprehensive approach to assessing the SOE, offering improved safety margins for carrier-based aircraft operations. This research is expected to contribute to the development of more robust and precise operational guidelines for naval aviation.

• Journal of the Korean Society of Marine Environment & Safety
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• v.19 no.6
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• pp.666-673
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• 2013

This paper proposes the performance evaluation test of attitude heading reference system (AHRS) suitable for small high speed autonomous underwater vehicle(AUV). Although IMU can provides the detail attitude information, it is sometime not suitable for small AUV with short operation time in view of price and the electrical power consumption. One of alternative for tactical grade IMU is the AHRS based micro-machined electro mechanical system(MEMS) which can overcome many problems that have inhibited the adoption of inertial system for small AUV such as cost and power consumption. A cost effective and small size AHRS which incorporates measurements from 3-axis MEMS gyroscopes, accelerometers, and 3-axis magnetometers has been developed to provide a complete attitude solution for AUV and the attitude calculation algorithm is derived based the coordinate transform equation and Kalman filter. The developed AHRS was validated through various performance tests as like the magnetometer calibration, operating experiments using land mobile vehicle and flight motion simulator (FMS). The test of magnetometer calibration shows the developed MEMS AHRS is robust to the external magent field change and the test with land vehicle proves the leveling error of developed MEMS AHRS is below $0.5^{\circ}/hr$. The results of FMS test shows the fact that AHRS provides the measurement with $0.5^{\circ}/hr$ error during 5 minutes operation time. These results of performance evaluation tests showed that the developed AHRS provides attitude information which error of roll and pitch are below $1^{\circ}$ and the error of yaw is below $5^{\circ}$ and satisfies the required specification. It is expected that developed AHRS can provide the precise attitude measurement under sea trial with real AUV.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.18 no.3
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• pp.640-646
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• 2017

A GEN TEST of the auxiliary power unit of a T-50 series aircraft is performed as part of the operational test of its emergency power system on the ground before flight. At this time, the auxiliary power unit should be automatically turned off via the response signal of the ECU when power is not normally supplied to the emergency power system. If the correct operation of the emergency power system cannot be confirmed on the ground, it is not possible to proceed with the flight. This kind of defect is a major factor causing the operation rate of the aircraft to be decreased. The defect code identified by the ECU was confirmed as a defect in the inverter. However, the same defect was found after replacing the inverter. This report presents an improved method of identifying the cause of the defect by analyzing the response characteristics of the ECU and emergency power system and allows the ECU to be recognized as the cause of the defect if the inverter does not generate a voltage within a certain time. Also, the application of the improved method confirmed that it can satisfy the output request time of the emergency power system and effectively prevent the auto-shutdown of the auxiliary power unit.

• Journal of the Korean Data and Information Science Society
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• v.24 no.6
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• pp.1309-1317
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• 2013

There are various parameter estimation methods for the generalized exponential distribution under progressive type I interval censoring. Chen and Lio (2010) studied the parameter estimation method by the maximum likelihood estimation method, mid-point approximation method, expectation maximization algorithm and methods of moments. Among those, mid-point approximation method has the smallest mean square error in the generalized exponential distribution under progressive type I interval censoring. However, this method is difficult to derive closed form of solution for the parameter estimation using by maximum likelihood estimation method. In this paper, we propose two type of approximate maximum likelihood estimate to solve that problem. The simulation results show the obtained estimators have good performance in the sense of the mean square error. And proposed method derive closed form of solution for the parameter estimation from the generalized exponential distribution under progressive type I interval censoring.

• The Journal of the Institute of Internet, Broadcasting and Communication
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• v.21 no.5
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• pp.103-111
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• 2021

The purpose of this study is to study a method for preventing collisions of multiple drones in controlled airspace. As a result of the study, it was proved that it is appropriate as a method to control drone collisions after setting accurate information on the ROI (Region of Interest) area estimated based on the expected drone path and time in the control system as a method to avoid drone collision. As a result of the empirical analysis, the diameter of the flight path of the operating drone should be selected to reduce the risk of collision, and the change in the departure time and operating speed of the operating drone did not act as an influencing factor in the collision. In addition, it has been demonstrated that providing flight priority is one of the appropriate methods as a countermeasure to avoid collisions. For collision avoidance methods, not only drone sensor-based collision avoidance, but also collision avoidance can be doubled by monitoring and predicting collisions in the control system and performing real-time control. This study is meaningful in that it provided an idea for a method for preventing collisions of multiple drones in controlled airspace and conducted practical tests. This helps to solve the problem of collisions that occur when multiple drones of different types are operating based on the control system. This study will contribute to the development of related industries by preventing accidents caused by drone collisions and providing a safe drone operation environment.

• The Korean Journal of Air & Space Law and Policy
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• v.32 no.2
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• pp.189-217
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• 2017

Declaration of Air Defense and Identification Zones started with the United States in 1950, which was followed by declaration of KADIZ by the Republic of Korea in 1951. Initial ADIZ were solely linked with air defense missions, but their roles have changed as nations around the globe manifested a tendency to expand their influence over maritime resources and rights. In particular, China declared ADIZ over the East China Sea in October 2013 and forced all passing aircraft to submit flight plan to ATC or military authority, saying failure of submission will be followed by armed engagement. China announced it would declare another zone over the South China Sea despite the ongoing conflict in the area, clearly showing ADIZ's direct connection with territorial claim and EEZ and that it serves as a zone within which a nation can execute its rights. The expanded KADIZ, which was expanded in Dec 15, 2013 in response to Chinese actions, overlaps with the Chinese ADIZ over the East China Sea and the Japanese ADIZ. The overlapping zone is an airspace over waters where not only the Republic of Korea but also of China and Japan argue to be covering their continental shelf and EEZ. Military conventions were signed to prevent contingencies among the neighboring nations while conducting identifications in KADIZ, including the overlapping zone. If such military conventions and practice of air defense identification continue to be respected among states, it is under the process of turning into a regional customary law, although ADIZ is not yet recognized by international law or customary law. Moreover, identification within ADIZ is carried out by military authorities of states, and misguided customary procedures may cause serious negative consequences for national security since it may negatively impact neighboring countries in marking the maritime border, which calls for formulation of operation rules that account for other state activities and military talks among regional stake holders. Legal frameworks need to be in place to guarantee freedom of flights over international seas which UN Maritime Law protects, and laws regarding military aircraft operation need to be supplemented to not make it a requirement to submit flight plan if the aircraft does not invade sovereign airspace. Organizational instructions that require approval of Chairman of Joint Chiefs of Staff for entrance and exit of ADIZ for military aircraft need to be amended to change the authority to Minister of National Defense or be promoted to a law to be applicable for commercial aircraft. Moreover, in regards to operation and management of ADIZ, transfer of authority should be prohibited to account for its evolution into a regional customary law in South East Asia. In particular, since ADIZ is set over EEZ, military conventions that yield authority related to national security should never be condoned. Among Korea, China, Japan and Russia, there are military conventions that discuss operation and management of ADIZ in place or under negotiation, meaning that ADIZ is becoming a regional customary law in North East Asia region.

• Korean Security Journal
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• no.62
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• pp.65-86
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• 2020

Drones, which were originally developed for military purpose, have expanded rapidly not only in hobbies, leisure, but also in broadcasting, filming, and public sectors, and search and rescue drones have been used to find four Korean teachers who went to Nepal for volunteer work but went missing in the avalanche. The government is encouraging the use of drones in the public sector as a policy to foster the drone industry, and the market is expected to expand in the future. This study presents improvement measures and specific directions for use of drones by public agencies at a time when the use of drones is expanding in the public sector. To that end, this research reviewed the interviews of relevant experts, analysis of drone operation regulations by public agencies, and the cases of operation of drones for searching missing persons by police. First of all, it will have to secure skilled personnel before the introduction of the drones and then determine the specifications of the drones through sufficient review, and then be put into the mission after careful examination of the drones. Next, it is necessary to draw up a base rule for drone operation and draw up a manual accordingly. Finally, drone flight has the risk of a crash, and it is essential to secure dedicated personnel for drone operation, especially since drones in the public sector are specialized in large scale compared to hobby drones to achieve their purpose. This research only conducted a detailed analysis of the National Police Agency's drones for searching for missing persons, and there are limitations to the number of people interviewed. Subsequent studies will require analysis of various public institutions, and in addition to interviews, surveys will require analysis of various data and statistics.

• Aerospace Engineering and Technology
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• v.4 no.2
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• pp.50-59
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• 2005

This paper described performance test of 1st prototype "Tail-Fan" system. KARI(Korea Aerospace Research Institute) developed "Tail-Fan" system as a kind of helicopter anti-torque system(ATS) and designed ATS performance test-rig for Tail-Fan system performance test. For Tail-Fan system performance tests, firstly, test-rig operation tests were carried out for verification of design specifications. And natural frequencies of fan blade and test-rig were measured respectively. To find the operation rotating speed for performance tests, vibration tests using accelerometers on tail gear box(TGB) were carried out. Through the fanplot and vibration test results, rotational speed for Tail-Fan performance test to avoid a resonance were found and performance tests were carried out in flight conditions. We analyzed test data by non-dimensionalization. Through this results, 1st prototype "Tail-Fan" system was satisfied with design requirements.