• The Korean Journal of Air & Space Law and Policy
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• v.35 no.2
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• pp.75-111
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• 2020

The civilian drone world has evolved in recent years from one dominated by hobbyists to growing involvement by companies seeking to profit from unmanned flight in everything from infrastructure inspections to drone deliveries that are already subject to regulations. Drone flight under the property right relation with the land owner would be deemed legal on the condition that expeditious and innocent passage of drone flight over the land be assured. The United Nations Convention on the Law of the Sea (UNCLOS) enshrines the concept of innocent passage through a coastal state's territorial sea. Passage is innocent so long as it is not prejudicial to the peace, good order or security of the coastal state. A vessel in innocent passage may traverse the coastal state's territorial sea continuously and expeditiously, not stopping or anchoring except in force majeure situations. However, the disturbances caused by drone flight may be removed, which is defined as infringement against the constitutional interest of personal rights. For example, aggressive infringement against privacy and personal freedom may be committed by drone more easily than ever before, and than other means. The cost-benefit analysis, however, has been recognjzed as effective criteria regarding the removal of disturbances or injunction decision. Applying that analysis, the civil action against such infringement may not find suitable basis for making a good case. Because the removal of such infringement through civil actions may result in only the deletion of journal article. The injunction of drone flight before taking the information would not be obtainable through civil action, Therefore, more detailed and meticulous regulation and criteria in public law domain may be preferable than civil action, at present time. It may be suitable for legal stability and drone industry to set up the detailed public regulations restricting the free flight of drone capable of acquiring visual information amounting to the infrigement against the right of personal information security.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.42 no.10
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• pp.851-857
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• 2014

This paper addresses the design of the auto race-track and figure-8 flight mode which can be applied to expand the loitering flight mode and increase the safety of UAV. To implement these flight modes, necessary waypoints and entry points can be calculated automatically from several information of the ground control system. The flight logic is proposed to pass the desired waypoints as well as entry points and transfer to the desired flight path by combining the light-of-sight and loitering guidance controller. The proposed algorithm and logic is verified using the 6-DOF UAV model and nonlinear simulation under the several flight conditions.

• Proceedings of the KIEE Conference
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• 2011.07a
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• pp.1928-1929
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• 2011

무인항공기란(Unmanned Aerial Vehicle : UAV)란 일반적으로 조종사 없이 사전에 입력된 프로그램에 따라 또는 비행체 스스로 주위환경(장애물, 항로)을 인식하고 판단하여 자율 비행(Autonomous Flying)하는 비행체를 말한다. 본 논문에서는 항법센서(Attitude Heading Referance System: AHRS)를 비행제어 시스템과 통합한 시스템에 관하여 다루었다.

• Journal of the Korea Computer Graphics Society
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• v.1 no.2
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• pp.269-272
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• 1995

본 논문에서는 자연지형의 3차원 투사도 제작기술에 비행기의 비행조건을 고려하여 개발한 비행 시뮬레이터에 대하여 설명하고자 한다. 여기서 발표하고자 하는 비행 시뮬레이터란 3차원의 자연지형을 마치 비행기를 타고가며 보는 것과 같은 효과를 낼 수 있게 하는 시스템을 말한다. 본 시스템은 사용자의 편의성을 도모하기 위하여 Sun workstation (SPARC 10)상에서 X11R5와 Motif 그리고 C언어를 이용하여 개발되었으며, 사용자가 비행경로, 비행속도, 비행고도 등의 비행 파라메타들을 마우스를 이용하여 손쉽게 입력할 수 있도록 구성되어 있다.

• Aerospace Engineering and Technology
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• v.6 no.2
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• pp.236-244
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• 2007

The 40% scaled vehicle of Smart UAV has been developed for the investigation of basic flight characteristics and the verification of flight control algorithm. The similar gimbal hub and drive train with the full scale UAV were implemented and a forced air cooling reciprocating engine was installed. The various kind of tests were conducted for the major components of the vehicle. The important performance and mechanical endurance of the fabricated vehicle were identified by ground and hovering test.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.36 no.6
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• pp.653-663
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• 2012

The study considers the high maneuverability flight and path optimization is conducted to investigate the appropriate generation of the lift and thrust considering the angle of the stroke plane. The path optimization problem is defined according to the various purposes of the high maneuverability flight. The flying purposes are to maximize thrust force, lift force and both lift and thrust forces. The flapping motion of the airfoil is made by a combined sinusoidal plunging and pitching motion in each problem. The optimization process is carried out by using well-defined surrogate models. The surrogate model is determined by the results of two-dimensional computational fluid dynamics analysis. The Kriging method is used to make the surrogate model and a genetic algorithm is utilized to optimize the surrogate model. The optimization results show the flapping motions for the high maneuverable flight. The effects on the generation of lift and thrust forces are confirmed by analyzing the vortex.

• 한국사회정책
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• v.24 no.2
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• pp.127-155
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• 2017

The physical and psychological weaknesses of delinquent adolescents increase the possibility of socialization and the possibility of social exclusion. Therefore, this study aims to clarify the characteristics of the social exclusion through the Q methodology and to suggest policy and practical intervention directions. For this purpose, 36 statements about social exclusion were conducted through 15 prejudicial adolescents with the prior cooperation of the institution and the consent of the subjects. As a result of the analysis, four types were derived. Type 1 can be named as social disconnect type 'Type 2 is total type', type 3 is 'poverty type' and type 4 is 'service type'. Based on this, it can be said that the characteristics of social exclusion of juvenile delinquents are complexity, inclusivity, individuality, universality.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.3
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• pp.280-287
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• 2010

The first Korean satellite launch vehicle, KSLV-I(Korea Space Launch Vehicle-I), was launched for its first flight test on Aug. 25, 2009 from Naro Space Center located in south Jolla province. Because launch vehicles usually fly long range with large amount of propellants aboard, preparation of countermeasures against potential malfunctions during flight is essential in launch operation. In this paper, the flight safety operation, prepared to guarantee flight safety during launch operation of KSLV-I, is presented. Prior to flight test, flight safety analysis is performed to estimate associated risk levels quantitatively, and during flight, flight safety systems are operated to cope with any risky situations. Real-time flight monitoring including computation of instantaneous impact point using tracking data is executed normally and the flight test is completed without activation of flight termination system.

• Journal of Advanced Navigation Technology
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• v.15 no.6
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• pp.977-985
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• 2011

Airborne separation assurance is a key requirement for Free Flight Airspace operations, This paper study the feasibility of airborne separation assurance for free flight Airspaces operations by evaluating the efficiency measurement models. Three qualitatively different methods are utilized; one based Ground and Air conflict probability model, other based Dynamic Density model. the other based Direct operating cost model. The evaluation is Direct Operating Cost model and Two metrics are utilized for the efficiency measurements; airborne separation assurance performed quite well in the Free Flight evaluation; (1) 2 scenario of the conflict situations are resolved; (2) The MD-80 flight peformed separation assurance and efficiency, Not only appling for geometric method algorithm is more efficiently than potential method, but also the most efficiently geometric combined method.

• Journal of Aerospace System Engineering
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• v.17 no.5
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• pp.42-57
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• 2023

In this paper, to increase the research capability of flight missions and maintenance in operating military aircraft, we studied the requirements for additional mounting of flight video and data recorders and safety verification methods. The verification process of the recorder equipment itself, structural safety in the aircraft system, power and electrical safety, electromagnetic compatibility, and impact of airworthiness are described in accordance with military standards and operating environment requirements. In addition, through ground/flight tests, the results of functional operation suitable for the influence and demand of interference between the flight video and data recorder and other systems are also presented.