• International Journal of Aeronautical and Space Sciences
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• 제11권2호
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• pp.110-117
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• 2010

We propose guidance laws based on a pursuit-evasion game. The game solutions are obtained from a pursuit-evasion game solver developed by the authors. We introduce a direct method to solve planar pursuit-evasion games with control variable constraints in which the game solution is sought by iteration of the update and correction steps. The initial value of the game solution is used for guidance of the evader and the pursuer, and then the pursuit-evasion game is solved again at the next time step. In this respect, the proposed guidance laws are similar to the approach of model predictive control. The proposed guidance method is compared to proportional navigation guidance for a pursuit-evasion scenario in which the evader always tries to maximize the capture time. The capture sets of the two guidance methods are demonstrated.

• 한국우주과학회:학술대회논문집(한국우주과학회보)
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• 한국우주과학회 2003년도 한국우주과학회보 제12권2호
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• pp.51-51
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• 2003

인공위성의 개발 단계는 Prototype Model(PM), Engineering Model(EM), Qualification Model(QM) 그리고 Flight Model(FM)로 구분된다. 이때, Prototype 개발을 제외한 EM, QM, FM 개발단계는 반드시 종합조립시험(AIT)을 통하여 System Integration Test를 수행한다. 이 중에서 위성발사 전 최종 종합조립시험단계인 FM AIT는 위성의 최종시험단계이므로 Scenario Test를 포함한 지상에서 수행하여야 할 모든 시험을 수행한다. 이때, EM, QM 단계와는 다르게 FM AIT는 전기적 및 기계적 시험을 수행하나, 본 논문에서는 전기적 시험 과정과, Control Center 구성도 등을 포함하고 있는 Hardware 부분과, 관련 시험을 수행하게 될 Simulator를 포함한 Software 부분으로 나누어 소개하며, 기타 FM AIT 수행에 필요한 Electrical Ground Support System (EGSE) 전체 구성을 소개한다.

• 유체기계공업학회:학술대회논문집
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• 유체기계공업학회 2006년 제4회 한국유체공학학술대회 논문집
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• pp.415-421
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• 2006

The unsteady flow calculation around the proprotor of Smart UAV was conducted. Using the flight scenario of SUAV which composed of hover, transition, and airplane mode, the aerodynamic analysis of proprotor were performed for the variation of collective pitch, rpm, forward speed, and tilt angle. The unsteady compressible Navier-Stokes equations were used for the calculation and the dynamic overset grid technique was applied for the rotating proprotor. The aerodynamic performance of proprotor calculated in this way were validated by comparing with the performance data obtained from the blade element momentum method.

• International Journal of Aeronautical and Space Sciences
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• 제6권2호
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• pp.97-109
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• 2005

In this paper, the critical requirement for obstacle awareness and avoidance is assessed with the compliance of the equivalent level of safety regulation, and then the collision avoidance sensor system is presented with the key design parameters for the requirement of the smart unmanned aerial vehicle in low-altitude flight. Based on the assessment of various sensors, small-sized radar sensor is selected for the suitable candidate due to the real-time range and range-rate acquisition capability of the stationary and moving aircraft even under all-weather environments. Through the performance analysis for the system requirement, the conceptual design result of radar sensor model is proposed with the range detection probability and collision avoidance mode is established based on the time-to-collision, which is analyzed by collision scenario.

• 한국전자파학회논문지
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• 제28권3호
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• pp.225-236
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• 2017

본 논문은 항공기용 다기능 레이다의 성능 평가를 위한 레이다/환경 통합 시뮬레이터 구축 및 검증에 대해 설명한다. 항공기 운용 시나리오 구현을 위해 6자유도 동역학 모델을 적용하였다. 항공기 6자유도 강체 동역학 모델에서 항공기의 자세 기동을 고려한 궤적 생성을 위해 정상 상태 비행 평형점 탐색, 오토파일럿 설계, 항공기 유도 명령 생성을 진행하였다. 레이다 시뮬레이터 구축을 위해 레이다의 표적 탐지 및 측정 모델, 추적 필터를 포함하는 레이다 운용 모델이 고려되었다. 이를 통해 항공기의 자세 기동을 고려한 다기능 레이다/환경 통합 시뮬레이터를 구현하였고, 특정 공대공 시나리오를 생성하여 레이다/환경 통합 시뮬레이터를 시험 및 검증하였다.

• 산업경영시스템학회지
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• 제46권2호
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• pp.160-167
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• 2023

This study focuses on the development of a Last-Mile delivery service using unmanned vehicles to deliver goods directly to the end consumer utilizing drones to perform autonomous delivery missions and an image-based precision landing algorithm for handoff to a robot in an intermediate facility. As the logistics market continues to grow rapidly, parcel volumes increase exponentially each year. However, due to low delivery fees, the workload of delivery personnel is increasing, resulting in a decrease in the quality of delivery services. To address this issue, the research team conducted a study on a Last-Mile delivery service using unmanned vehicles and conducted research on the necessary technologies for drone-based goods transportation in this paper. The flight scenario begins with the drone carrying the goods from a pickup location to the rooftop of a building where the final delivery destination is located. There is a handoff facility on the rooftop of the building, and a marker on the roof must be accurately landed upon. The mission is complete once the goods are delivered and the drone returns to its original location. The research team developed a mission planning algorithm to perform the above scenario automatically and constructed an algorithm to recognize the marker through a camera sensor and achieve a precision landing. The performance of the developed system has been verified through multiple trial operations within ETRI.

• 산업경영시스템학회지
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• 제39권3호
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• pp.56-63
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• 2016

For air express service providers offering various express delivery services such as overnight delivery and next-business day delivery services, establishing quickly cargo loading plans is one of important issues owing to the characteristics of air express business, i.e., a short amount of time is available to complete all cargo loading operations before flight departure after receiving air express containers, pallets and bulks. On the other hand, one of major concerns in the air cargo loading planning is to make a plan that insures the stability of an aircraft to avoid take-off, flight, and landing accidents. To this end, this paper considers an air cargo loading planning problem, which is the problem of determining locations in the aircraft cargo space where air containers, pallets and bulks to be loaded while insuring the aircraft stability, motivated from DHL and Air Hong Kong. The objective of the problem is to maximize the total revenue gained from loading air express containers, pallets and bulks. To solve the problem, this paper suggests a simulated annealing algorithm to overcome impracticality of the integer programming model developed by a previous study requiring excessive computation time. The results of computational experiments show that the heuristic algorithm is a viable tool for establishing express cargo loading plans as giving robust and good solutions in a short amount of computation time. Scenario analyses are performed to investigate the effect of the current activities of air express carriers on the revenue change and to draw practical implications for air express service providers.

• 한국항공우주학회지
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• 제35권2호
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• pp.107-114
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• 2007

논문에서는 두루미-II 무인기 모델을 이용하여 다양한 조종력 할당 기법의 성능을 평가하였다. 조종력 할당 기법은 먼저 조종면 고장을 고려하지 않은 상태에서 대상 항공기의 기준 비행제어 시스템을 설계한 후, 조종력 할당 알고리즘을 결합하여 구현할 수 있다. 본 논문에서 대상 항공기 모델인 두루미-II 무인기의 기준 비행제어 시스템을 고전제어 기법에 근거하여 설계하였다. 그리고 Psuedo-inverse CA 기법과 Direct CA 기법 및 Optimization CA 기법을 구현하여 두루미-II 무인기의 기준 비행제어 시스템과 결합한 후, 조종면 고장 시나리오에 따른 비선형 시뮬레이션을 통해 각 조종력 할당 기법의 성능을 평가하고 비교하였다.

• 한국항행학회논문지
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• 제24권4호
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• pp.251-260
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• 2020

무인항공기는 일반항공기와 달리 비행 중에는 원격 점검만 가능한 한계가 있기에 비행 전, 후 점검을 통한 비행체의 고신뢰성을 유지하는 것은 매우 중요하다. 이를 위해, 본 논문에서는 무인항공기 점검을 위한 비행체점검장비의 하드웨어 및 소프트웨어 요구사항을 도출하고 도출된 요구사항을 만족할 수 있도록 설계하였다. 이 설계를 바탕으로 실제 점검 시나리오에 맞춰 비행체점검장비를 구현하였다. 구현한 비행체점검장비는 총 3단계에 걸친 기능검증을 통해 비행 전·후, 시동 전·후와 같은 다양한 상황에서 자동점검 또는 운용자가 필요한 부분만 선택하여 수동점검을 할 수 있어 비행체 점검에 필요한 시간과 비용을 줄일 수 있다는 장점을 가진다. 또한 본 연구의 내용은 다른 무인항공기를 위한 비행체점검장비 설계 및 구현에도 많은 참고와 도움을 줄 수 있을 것으로 기대된다.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2008년 영문 학술대회
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• pp.330-339
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• 2008

Ground-based interceptors(GBI) comprise a major element of the strategic defense against hostile targets like Intercontinental Ballistic Missiles(ICBM) and reentry vehicles(RV) dispersed from them. An optimum design of the subsystems is required to increase the performance and reliability of these GBI. Propulsion subsystem design and optimization is the motivation for this effort. This paper describes an effort in which an entire GBI missile system, including a multi-stage solid rocket booster, is considered simultaneously in a Genetic Algorithm(GA) performance optimization process. Single goal, constrained optimization is performed. For specified payload and miss distance, time of flight, the most important component in the optimization process is the booster, for its takeoff weight, time of flight, or a combination of the two. The GBI is assumed to be a multistage missile that uses target location data provided by two ground based RF radar sensors and two low earth orbit(LEO) IR sensors. 3Dimensional model is developed for a multistage target with a boost phase acceleration profile that depends on total mass, propellant mass and the specific impulse in the gravity field. The monostatic radar cross section (RCS) data of a three stage ICBM is used. For preliminary design, GBI is assumed to have a fixed initial position from the target launch point and zero launch delay. GBI carries the Kill Vehicle(KV) to an optimal position in space to allow it to complete the intercept. The objective is to design and optimize the propulsion system for the GBI that will fulfill mission requirements and objectives. The KV weight and volume requirements are specified in the problem definition before the optimization is computed. We have considered only continuous design variables, while considering discrete variables as input. Though the number of stages should also be one of the design variables, however, in this paper it is fixed as three. The elite solution from GA is passed on to(Sequential Quadratic Programming) SQP as near optimal guess. The SQP then performs local convergence to identify the minimum mass of the GBI. The performance of the three staged GBI is validated using a ballistic missile intercept scenario modeled in Matlab/SIMULINK.