• 해양환경안전학회지
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• 제21권4호
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• pp.409-420
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• 2015

본 연구에서는 미국 일본 등 해양선진국에서 운영하고 있는 민간해양구조세력의 사례와 국내 의용소방대의 현황을 조사, 비교분석하였다. 이를 통해 한국해양구조협회와 민간해양구조대로 이원화되어 있는 해양구조세력을 일원화하여 통합구조체제를 갖추고, 법제화를 통해 안정적인 육성 지원책을 마련할 필요가 있었다. 효율적인 구조활동을 위해 미국 캐나다처럼 정부기관에서 지휘 통솔권을 갖추도록 법령을 정비하고 교육 훈련을 체계화하며 전문교육기관 위탁교육 등을 통하여 구조역량을 높여야 할 것으로 판단되었다. 민간구조세력의 안정적인 지위를 유지하기 위해 정부지원금 등 재정지원책을 마련하며, 해양구조 업무를 담당하는 일원으로 사명감과 자긍심 고취를 위해 국내 외 연수 등 사기진작책 마련 등 법적, 제도적 개선사항을 도출하여 제시하였다.

• 한국우주과학회:학술대회논문집(한국우주과학회보)
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• 한국우주과학회 2011년도 한국우주과학회보 제20권1호
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• pp.24.4-24.4
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• 2011

Frozen orbit concept is very useful in designing particular mission orbits including the Sun-synchronous and minimum altitude variation orbits. In this work, variety of frozen and Sun-synchronous orbit conditions around the Moon is investigated and analyzed. The first two zonal harmonics of the Moon, J2 and J3, are considered to determine mean orbital elements to be a frozen orbit. To check the long-term behavior of a frozen orbit, formerly developed YonSei Precise Lunar Orbit Propagator (YSPLOP) is used. First, frozen orbit solutions without conditions to be the Sun-synchronous orbit is investigated. Various mean semi-major axes having between ranges from 1,788 km to 1,938 km with inclinations from 30 deg to 150 deg are considered. It is found that a polar orbit (90 deg of inclination) having 100 km of altitude requires the orbital eccentricity of about 0.01975 for a frozen orbit. Also, mean apolune and perilune altitudes for this case is about 136.301 km and 63.694 km, respectively. Second, frozen orbit solutions with additional condition to be the Sun-synchronous orbit is investigated. It is discovered that orbital inclinations are increased from 138.223 deg to 171.553 deg when mean altitude ranged from 50 km to 200 km. For the most usual mission altitude at the Moon (100 km), the Sun-synchronous orbit condition is satisfied with the eccentricity of 0.01124 and 145.235 deg of inclination. For this case, mean apolune and perilune altitudes are found to be about 120.677 km and 79.323 km, respectively. The results analyzed in this work could be useful to design a preliminary mapping orbit as well as to estimate basic on-board payloads' system requirements, for a future Korea's lunar orbiter mission. Other detailed perturbative effects should be considered in the further study, to analyze more accurate frozen orbit conditions at the Moon.

• 산업경영시스템학회지
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• 제43권4호
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• pp.116-122
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• 2020

Human and material resource planning is one representative example of Operations Research. Resource planning is important not only in civilian settings but also in military ones. In the Air Force, flight scheduling is one of the primary issues that must be addressed by the personnel who are connected to flight missions. However, although the topic is of great importance, relatively few studies have attempted to resolve the problem on a scientific basis. Each flight squadron has its own scheduling officers who manually draw up the flight schedules each day. While mistakes may not occur while drafting schedules, officers may experience difficulties in systematically adjusting to them. To increase efficiency in this context, this study proposes a mathematical model based on a binary variable. This model automatically drafts flight schedules considering pilot's mission efficiency. Furthermore, it also recommends that schedules be drawn up monthly and updated weekly, rather than being drafted from scratch each day. This will enable easier control when taking the various relevant factors into account. The model incorporates several parameters, such as matching of the main pilots and co-pilots, turn around time, availability of pilots and aircraft, monthly requirements of each flight mission, and maximum/minimum number of sorties that would be flown per week. The optimal solution to this model demonstrated an average improvement of nearly 47% compared with other feasible solutions.

• 한국해양공학회지
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• 제32권5호
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• pp.402-409
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• 2018

This paper describes the plan and procedure of a development test and evaluation that will be performed to verify the performance and technology of multi-mission unmanned surface vehicles (MMUSVs). In order to verify the design requirement of MMUSVs, we designed and manufactured the common platform of MMUSVs, which have an overall length of8.4 m, a displacement of 3,100 kg, and a speed of more than35 kts. The platform is equipped with several sub-systems, including radar and an EOTS/IRS. The EOTS/IRS, along with the search radar, is used for effective detection, identification, and targeting. The core technologies of MMUSV for DT&E will be investigated. The common platform design technologies, remote operating and control system technologies, autonomous navigation technologies, and unmanned operational technology of sensors and equipment will be studied for the development of the MMUSV's core technologies. The system will be able to make precise observations and track targets both manually and automatically during day and night conditions. Currently, the verification tests for each of the technologies and for the integrated system are in the pipeline for DT&E, which will be performed next year. Also, software reliability and life tests will be performed.

• 한국군사과학기술학회지
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• 제8권1호
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• pp.49-55
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• 2005

Due to small and light mission payloads, subsystems and propulsion system, small sized UAVs come to be available for reconnaissance that have been performed by aircraft and huge UAVs. The objective of this study is to develop an efficient propulsion system for small reconnaissance UAVs. A glow engine was modified for an efficient and robust 4-stroke gasoline engine with carburetor, new electronic control unit and lubrication system. Engine modification technique and small engine performance test stand are capable of economical method for military UAVs.

• 로봇학회논문지
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• 제18권3호
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• pp.233-240
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• 2023

In this paper, we proposed a hybrid type robot that simultaneously surveillance and reconnaissance on the ground and in the air. It was possible to expand the surveillance and reconnaissance range by expanding the surveillance and reconnaissance area of the ground robot and quickly moving to the hidden area through the drone. First, ground robots go to mission areas through drones and perform surveillance and reconnaissance missions for urban warfare or mountainous areas. Second, drones move ground robots quickly. It transmits surveillance and reconnaissance images of ground robots to the control system and performs reconnaissance missions at the same time. Finally, in order to secure the interoperability of these hybrid robots, basic performance and environmental performance were verified. The evaluation method was tested and verified based on the KS standards.

• 한국항공우주학회지
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• 제32권3호
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• pp.45-50
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• 2004

위성의 성공적인 임무 수행을 위한 자세 안정화와 성능요구조건을 만족하기 위해서 반작용휠 제어로직의 설계가 중요하다. 실제 위성궤도 상에서 발생하는 여러 가지 불확실성으로 인해 지상실험을 통해 획득한 모델 파라미터 값들만으로 제어로직을 설계하는데 한계가 있다. 그러므로 위성이 궤도상에 있을 때의 반작용휠 입력 및 출력 데이터를 이용하여 모델 파라미터를 보정하고 자세제어기에 반영하는 것이 요구된다. 본 논문에서는 다목적실용위성의 Telemetry 데이터를 활용한 시스템인식 (System Identification)을 수행하였고, 이를 통한 반작용휠의 모델 파라미터를 추출한다. 또한, 반작용휠을 모델링 하고 또한 제어기설계에 사용된 모델 파라미터를 추출하여 지상실험 데이터와 비교분석한다.

• 한국항공우주학회지
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• 제40권3호
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• pp.237-242
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• 2012

극저온이 요구되는 우주용 탑재장비의 냉각을 위해 일반적으로 Pulse Tube-type 압축기가 적용되고 있으며, 궤도상에서 압축기의 냉각성능, 임무수명 및 비대칭 온도분포에 의한 미소진동발생 방지를 위해 압축기를 허용온도 범위로 유지하는 열제어가 필요하다. 압축기는 궤도 운용 시 미소진동을 발생하여 관측성능이 요구되는 탑재체의 지향성능을 저하시키는 원인으로 작용한다. 본 논문에서는 압축기의 미소진동 방지를 목적으로 적용된 진동절연기의 성능유지 및 압축기의 허용온도범위 유지를 위한 열제어 성능을 동시에 만족하는 우주용 압축기 조립체의 열설계를 제안하였으며, 설계의 유효성을 해석적으로 입증하였다.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2004년도 ICCAS
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• pp.1392-1395
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• 2004

In order to successfully develop attitude and orbit control subsystem(AOCS), AOCS engineer performs hardware selection, controller design and analysis, control logic and interface verification on electrical test bed, integrated system test, polarity test, and finally verification on orbit after launching. Attitude and orbit control subsystem for KOMPSAT-2 consists of standby mode, sun mode, maneuver mode, science mode, and power safe mode to stabilize and to control the spacecraft for performing the mission. The sun mode is usually divided into sun point submode, earth search submode and safe hold submode. The maneuver mode is divided into attitude hold submode and ${\triangle}$ V submode, while the science mode divided into science coarse submode and science fine submode. Moreover, it is added to back-up mode which uses wheels as an actuator for sun mode and maneuver mode. In this paper, we describe the controller design process and the performance of the design results with respect to the sun mode and the maneuver mode based on thrusters as an actuator using on flexible model.

• 한국전자통신학회논문지
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• 제19권4호
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• pp.647-654
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• 2024

군 무기체계에서는 무장을 제어하기 위한 조종간이 필수적으로 사용된다. 본 논문에서는 RS-422 통신과 임베디드 프로세서를 이용하여 무장 조종간의 설계와 성능을 평가한다. 이 무장 조종간은 한국 조종사의 손 치수와 임무 편의성을 고려하여 인체공학적으로 디자인되었으며, RS-422 통신 기반의 회로와 소프트웨어는 임베디드 프로세서를 이용하여 설계되었다. 무장 조종간의 시제품을 제작하여 기본성능시험 및 고도, 고온, 저온, 온도충격, 습도, 강우, 진동 충격, 가속도 등 다양한 환경시험을 시행하여 기준을 충족하였다.