• 한국산학기술학회논문지
• /
• 제21권1호
• /
• pp.90-96
• /
• 2020

현 시대에 있어 정보력은 국방 분야에 있어 굉장히 주요한 요인으로 손꼽히고 있다. 따라서 감시 및 정찰을 위한 무기체계 기술 확보가 불가피해졌다. 이에 따라 군이 직접 수행하기에는 너무 위험하거나(Dangerous), 지저분하거나(Dirty), 지루한(Dull) 환경과 같이 유인항공기의 비행운용이 제한되는 경우에 무인항공기(UAV)가 개발되어 전 세계적으로 활발히 운용 중에 있다. 국내에서 연구 개발된 한 무인항공기 체계에는 구성품 중 비행체 점검 장비가 포함되어 있다. 비행체 점검 장비는 무인항공기와 연결되어 그것의 상태를 확인하는 장비로, 무인항공기에 동작 명령을 인가하고 명령 값을 추종하는 지 확인함으로써 운용자로 하여금 비행 가능 여부를 점검할 수 있도록 하는 장비이다. 본 연구는 이러한 운용 중 엔진 소음에 의하여 비행체 점검 장비가 정지한 현상에 대한 고장탐구를 실시하고 소프트웨어, 하드웨어 그리고 외부 환경의 측면에서 원인을 분석한다. 분석된 원인에 따라 개선방안을 제시하고 제안된 방안이 고장을 방지할 수 있음을 검증한 결과를 다룬다.

• 대한건축학회논문집:계획계
• /
• 제36권2호
• /
• pp.79-86
• /
• 2020

In order to accommodate the increase in urban population due to government-led national planning and economic growth, many buildings such as houses and business building were supplied. Although the building law was revised and managed to manage the supplied buildings, for the sake of economic benefit, there have been buildings that are enlarged or reconstructed without declaring building permits. In order to manage these buildings, on-site surveys were conducted. but it has many personnel consumption. To solve this problem, a method of using a satellite image and a manned aircraft is utilized, but it is diseconomical and a renewal cycle is long. In addition, it is not utilized to the height, and although it is judged by the shading of the building, it has limitations that it must be calculated individually. In this study, height of the building was calculated by using the unmanned aerial vehicle with low personnel consumption, and the accuracy was verified by comparison with the building register and measured value. In this study, spatial information was constructed using a fast unmanned aerial vehicle with low manpower consumption and the building height was calculated based on this. The accuracy by comparing the calculated building height with the building register and the actual measurement.

• 문화기술의 융합
• /
• 제9권2호
• /
• pp.295-299
• /
• 2023

우리나라는 21세기 들어 출생자 수가 급격히 감소하고 있다. 이것은 현행 병역제도와 인사제도를 유지한 상태로는 감축한 36.5만 명의 육군도 유지하기 어렵게 한다. 그럼에도 불구하고 육군은 국가방위 최후의 보루로서 외부의 침략으로부터 국토를 지켜야 할 사명이 있다. 이러한 사명을 다하기 위해서는 병역제도와 인사제도를 개선하는 방법도 있지만, 개인의 전투력을 극대화시켜 일당백의 용사를 만들고 적보다 우세한 기동력을 통해 부족한 병력 수를 극복하는 방안도 있다. 본 연구는 후자의 개념을 적용하여 개인전투력과 기동력을 극대화 할 수 있는 유·무인 복합전투체계를 통해 병력 부족의 해결은 물론, 전투력을 강화하는 방안을 연구하였으며 더 나아가 미래 전장환경을 분석하고 육군의 유·무인 복합전투체계의 발전적인 방향을 제시하여 작전수행 체계에 대한 시사점을 제공하는 것이다.

• 한국항해항만학회:학술대회논문집
• /
• 한국항해항만학회 2000년도 추계학술대회논문집
• /
• pp.121-129
• /
• 2000

In this paper, we discuss how to operate a buffer yard in an automated container terminal, which will be used for resolving the difficulties to which the interaction between external manned trucks and internal unmanned equipment led. The determination of fleet size of material handling equipment is an important issue in designing of buffer yard in automated container terminals. This research also addresses the issue of determining buffer capacities through simulation. By using response surface methodology (RSM) for efficient experimentation, the optimal combination of design parameters under applicable operational strategies is obtained.

• 한국항공운항학회:학술대회논문집
• /
• 한국항공운항학회 2016년도 춘계학술대회
• /
• pp.228-232
• /
• 2016

유/무인기가 통합되어 운용되는 환경을 고려한 시뮬레이션 시스템 설계 방안을 제시하였다. 기존의 관제 공역 내의 유인기를 대상으로 하는 항공 교통 시뮬레이션 시스템의 기능과 무인기 시스템의 기본적인 기능을 고려하였으며, 이를 기반으로 유/무인기 복합 운용의 새로운 개념을 적용하여 모의할 수 있는 시뮬레이션 환경을 구성하였다. 모의 환경의 확장성을 고려하여, 무인기는 관제 공역에 진입하여 유인기와 복합 운용되는 무인항공기 시스템과 비관제 영역에서 운용되는 소형 무인비행장치로 구분하여 구성하였다. 시뮬레이션 시스템을 구현하기 위한 운용 개념에 대해 서술하였으며, 이를 기반으로 필요로 하는 주요 기능 요소들을 구성하고 각 요소에서 고려되어야 하는 주요 요구 사항을 제시하였다.

• 항공우주시스템공학회지
• /
• 제6권3호
• /
• pp.24-28
• /
• 2012

An actuator should be added to a existing control linkage to make manned aircraft to unmanned. But it is quiet difficult to synchronize actuator with control surface because non-linear error necessarily occurs when four-bar linkage acts in three dimensional motion. In addition, in point of controller design view, while a real-time model needs the control surface deflection as its input, controller needs the actuator command as its output. Hence, the relation between both should be investigated. In this paper, the mathematical relation between actuator and control surface deflection investigated by kinematic analysis of a plant aircraft. The performance margin of the selected actuator also was verified.

• 한국시뮬레이션학회:학술대회논문집
• /
• 한국시뮬레이션학회 2004년도 춘계학술대회 논문집
• /
• pp.142-147
• /
• 2004

It is very difficult to acquire high-fidelity flight test data for small airplanes such as typical unmanned aerial vehicles because MEMS-type small sensors used in the tests do not present reliable data in general. Besides, it is not practical to conduct expensive flight tests for low-cost small airplanes in order to simulate their flight characteristics. A practical approach to obtain acceptable flight data, including stability and control derivatives and data of weight and balance, is proposed in this study. Aircraft design software such as Darcorp's AAA is used to generate aerodynamic data for small airplanes, and moments of inertia are calculated using CATIA, structural design software. These flight data from simulation software are evaluated subjectively and tailored using simulation flight by experienced pilots, based on the certified procedures in FAA AC 120-45A and 40B, which are used for manned airplane simulators.

• 동력기계공학회지
• /
• 제19권3호
• /
• pp.36-41
• /
• 2015

The true north-finding equipment utilizing gyro sensor is used for INS(Inertial Navigation System) and has an increasing preference for gyro compass system due to compact size, lightening, low power and price. The purpose of this experiment is to research gyro compass system providing high performance in the field of manned or unmanned gyro compass system which proposes the accuracy of 1% utilizing experimented equipment at true north of the earth. Unlike the conventional system, the proposed gyro sensor system indicates to be applied in the various and specific equipment using multiple technique and method.

• 제어로봇시스템학회논문지
• /
• 제14권5호
• /
• pp.502-510
• /
• 2008

UAVs(Unmanned Aerial Vehicles) have many applications in military and commercial areas. The flight control system of UAVs is more important than manned aircraft's because the mission of UAVs must be operated without a human pilot. But very heavy and expensive navigation system makes it difficult to develop UAV flight control system. In this research, GPS/IMU integrated navigation filter was developed for light weight/low cost flight control system of small UAVs. With this navigation filter, full flight control system which has real time operating capability has been developed. The performance of the flight control system is basically checked by HILSIM (Hardware In the Loop SIMulation). Finally, the flight control system is verified by showing performance test result under real flight environment.

• 한국항공운항학회지
• /
• 제21권3호
• /
• pp.1-8
• /
• 2013

An application of adaptive flight controller is required for the non-linear and high uncertain system that configuration of tiltrotor aircraft is dramatically changed from rotary wing mode to fixed wing mode. In this paper, the applicable adaptive controller for the tiltrotor aircraft was designed using Neural Networks and DMI (Dynamic Model Inversion). The performance of the SCAS (Stability and Control Augmentation System) was simulated against manned military specification, using the fullscale model of 'Smart UAV(Unmanned Aerial Vehicle)' developed by Korea Aerospace Research Institute. And Neural Networks based adaptive controller was verified through its whole operating envelope using the established HQ (Handling Quality) criteria.