• Journal of Advanced Navigation Technology
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• v.27 no.1
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• pp.1-7
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• 2023

Mission autonomy system should be embedded on UAV (Unmanned Aerial Vehicle) for mosaic warfare where UAVs autonomously assign tasks to themselves. UxAS (Unmanned x-systems Autonomy Service) proposed by Air Force Research Laboratory is mission autonomy system for unmanned platforms. UxAS has extensible structure composed of numerous module services. However, UxAS can conduct mission autonomy process only when an operator sends an autonomy request. In this paper, We analyze the process of mission autonomy in UxAS, and propose an improved structure of UxAS where mission autonomy process is autonomously triggered by situation awareness service without the request of the operator. The proposed process was validated by simulation.

• Journal of Astronomy and Space Sciences
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• v.21 no.2
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• pp.153-166
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• 2004

Interplanetary trajectories using the gravity assists are studied for future Korean interplanetary missions. Verifications of the developed softwares and results were performed by comparing data from ESA's Mars Express mission and previous results. Among the Jupiter exploration mission scenarios, multi-planet gravity assist mission to Jupiter (Earth-Mars-Earth-Jupiter Gravity Assist, EMEJGA trajectory) requires minimum launch energy ($C_3$) of 29.231 $Km^2$/$S^2$ with 4.6 years flight times. Others, such as direct mission and single-planet(Mars) gravity assist mission, requires launch energy ($C_3$) of 75.656 $Km^2$/$S^2$ with 2.98 years flight times and 63.590 $Km^2$/$S^2$ with 2.33 years flight times, respectively. These results show that the planetary gravity assists can reduce launch energy, while EMEJGA trajectory requires the longer flight time than the other missions.

• Korean Journal of Social Welfare
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• v.63 no.1
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• pp.159-185
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• 2011

This study aims to find out the determinants of male police officers' investigative behavior(active investigation vs. secondary victimization) of sexual violence. For this purpose, a hypothetical model which explains the relationships among the 5 variables (knowledge of law about the investigative role, perception of the protective & connective role, prejudice against the sexual violence, active investigation, and secondary victimization) was developed. Using the data collected from 354 male police officers of 3 cities in Gyeongnam area, the hypothetical model was tested. For data analysis, a structural equation modeling was used, and the final model was found(CFI=0.947, IFI=0.948, RMSEA=0.048). As a result of analyzing the model, the followings were found: (1) Active investigation was increased by knowledge of law about the investigative role, and perception of the protective & connective role, while decreased by prejudice against the sexual violence. (2) Secondary vicimization was decreased by knowledge of law about the investigative role. (3) Prejudice against the sexual violence mediate the effects of knowledge of law about the investigative role, and perception of the protective & connective role on active investigation. (4) Prejudice against the sexual violence was found to have no significant effect on secondary victimization. Based on the findings, multi-educational programs, protocols on investigation of sexual violence, professionalization of the police, and changes in investigation environment as well as a system of collaboration and cooperation between police officer and social worker were suggested as a way to increase active investigation and to decrease secondary victimization.

• Journal of Advanced Navigation Technology
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• v.26 no.5
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• pp.304-311
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• 2022

Although the SEAD(suppression to enemy air defenses) mission is a strategically important task in modern warfare, the high risk of direct exposure to enemy air defense assets forces to use of unmanned aerial vehicles. this paper proposes a path planning algorithm for SEAD mission for an unmanned aerial vehicle and a method for calculating the mission effectiveness on the planned path. Based on the RRT-based path planning algorithm, a low-altitude ingress/egress flight path that can consider the enemy's short-range air defense threat was generated. The Dubins path-based Intercept path planning technique was used to generate a path that is the shortest path while avoiding the enemy's short-range anti-aircraft threat as much as possible. The ingress/intercept/egress paths were connected in order. In addition, mission effectiveness consisting of fuel consumption, the survival probability, the time required to perform the mission, and the target destruction probability was calculated based on the generated path. The proposed techniques were verified through a scenario.

• Aerospace Engineering and Technology
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• v.13 no.2
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• pp.142-149
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• 2014

After launch of Low Earth Orbit(LEO) satellite, Initial Activation Checkout(IAC) and Calibration and Validation(Cal & Val) procedure are performed prior to enter normal operation phase. During normal operation phase, most of the time is allocated for mission operation except following up measures to anomaly and orbit maintenance. Since mission operation capability is key indicator for success of LEO satellite program and consistent with promotion purpose of LEO satellite program, reliability should be ensured by conducting through test. In order to ensure reliability by examining the role of LEO satellite and ground station during ground test phase, realistic test scenario that is similar to actual operation conditions should be created, and test that aims to verify full mission cycle should be performed by transmitting created command and receiving image and telemetry data. This paper describes the test design and result. Consideration items for test design are described in detail and result of designed test items are summarized.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.36 no.4
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• pp.357-367
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• 2008

Preparing for future Korean Lunar missions, preliminary Lunar mission design software is developed using a impulsive thrusting method. Developed software is capable of design and analysis every required mission phases to design Lunar mission, including the Earth departure, Lunar transfer, Lunar arrival and mission operation phases. Also, assuming that KSLV-II is selected as a launch vehicle, future Korean Lunar explorer's mass budget is estimated based on driven optimal trajectory characteristics. Tracking analysis is also performed using Deep Space Network including angle geometry analysis between Earth - Moon - Lunar explorer - Sun which are very important for communication, solar panel pointing strategy and eclipse analysis when Lunar missions are under designing phase.

• Journal of the Korea Society for Simulation
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• v.20 no.2
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• pp.59-66
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• 2011

In this paper, a method to allocate a submarine search mission to an ASW(Anti-Submarine Warfare) helicopter is proposed. The aim of the proposed method is to increase the submarine detection capability. For this purpose, we modeled the behaviors that the ASW helicopter conduct during the search mission, and the relations between the behaviors are also modeled. To measure quantitatively the effectiveness of ASW search mission, the measure of effectiveness(MOP) is defined. Scenarios are designed to analyze the effectiveness utilizing the ASW mission model. We conducted simulations applying the designed scenarios and some parameters concerned with the friendly ship and the enemy submarine interacting each other in the ASW missions. We analyzed the result of simulation depending on the dipping interval and the pattern of dipping positions in the situation that the helicopter operates for a long time and should resupply several times on the friendly ship. From the analyzed data, we suggested the practical value of ratio between the detectable range of the sonar and the dipping interval to improve the effectiveness of ASW mission.

• Journal of the Korea Society of Computer and Information
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• v.15 no.1
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• pp.167-175
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• 2010

Like most large organizations, there are business rules such as 'separation of duty' and 'delegation' which should be considered in access control. From a SOD point of view, previous SOD models built on the (Administrative) Role-Based Access Control model cannot present the best solution to security problems such as information integrity by the limited constituent units such as role hierarchy and role inheritance. Thus, we propose a new integrated management model of administration role-based access control model and SOD policy, which is called the OS-SoDAM. The OS-SoDAM defines the authority range in an organizational structure that is separated from role hierarchy and supports a decentralized security officer-level SOD policy in which a local security officer can freely perform SOD policies within a security officer's authority range without the security officer's intervention.

• The Journal of the Convergence on Culture Technology
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• v.10 no.5
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• pp.181-188
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• 2024

This study explores the application of Mission Engineering, a concept and methodology adopted by the U.S. Department of Defense, to the Republic of Korea's defense planning and management system in response to the rapidly changing security environment. Through literature review, analysis of prior research and case studies, and focus group interviews (FGI), key elements of Mission Engineering were derived. Based on these findings, improvements for the ROK military's requirements planning and rapid acquisition system were proposed. As a result, three critical elements for applying Mission Engineering were identified: operational concepts, required capabilities, and acquisition. Suggestions for improvement include transitioning to a mission-oriented requirements planning system, applying Mission Engineering methodology when formulating operational concepts, supporting decision-making to shorten acquisition timelines, allocating budgets for rapid acquisition, and strengthening the capabilities of requirement-setting units. This study confirms the necessity and applicability of Mission Engineering and is expected to serve as a foundation for the future development of the defense planning and management system.

• Aerospace Engineering and Technology
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• v.2 no.2
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• pp.96-104
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• 2003

Geostationary satellite propulsion system provides satellite with the velocity increment for attitude control operations and sationkeeping operations from satellite launch to de-orbit at the end of life. Today, various types of propulsion system and its thrusters are produced by worldwide manufactures. Therefore, geostationary satellite manufacturers give significant modification to the Mission Analysis Software whenever different type of propulsion system type is adopted. Mission Analysis Software is a tool for planning and verification of satellite mission. For the development of the Generalized Mission Analysis Software, many thrusters are carefully investigated and modeled.