• Journal of Computing Science and Engineering
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• v.2 no.4
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• pp.357-374
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• 2008

Over the past few decades, a considerable number of studies have been conducted on the technologies to build an UAV (Unmanned Aerial Vehicle) control system. Today, focus in research has moved from a standalone control system towards a network-centric control system for multiple UAV systems. Enabling the design of such complex systems in easily understandable forms that are amenable to rigorous analysis is a highly desirable goal. In this paper, we discuss our experimental evaluation of the Time-triggered Message-triggered Object (TMO) structuring scheme in the design of the UAV control system. The TMO scheme enables high-level structuring together with design-time guaranteeing of accurate timings of various critical control actions with significantly smaller efforts than those required when using lower-level structuring schemes based on direct programming of threads, UDP invocations, etc. Our system was validated by use of environment simulator developed based on an open source flight simulator named FlightGear. The TMO-structured UAV control software running on a small computing platform was easily connected to a simulator of the surroundings of the control system, i.e., the rest of the UAV and the flight environment. Positive experiences in both the TMO-structured design and the validation are discussed along with potentials for future expansion in this paper.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.17 no.1
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• pp.9-16
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• 2009

The analysis of an aircraft flight dynamics is recently very convenient because of the introduction of state-space method and a well-developed package software. The representation of a dynamic system is described as a simple form of matrix calculation and the unique form of model is available for the linear or nonlinear, time variant or time invariant, mono variable or multi variable system with state-space method. And this analysis can be simplified with the specific functions of a package software and it is very simplified to execute the simulation of the dynamic characteristics for an aircraft model with an interactive graphical treatment. The purpose of this study is to develope an educational flight simulator for the students who need to analyze the dynamic characteristics of an aircraft that is primarily to execute the simulation for the analysis of the transient response and frequency response of an aircraft stability. Furthermore the dynamic characteristics of an aircraft motion is set up as dynamical animation tool for the control response on 3-axis motions of an aircraft.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.41 no.10
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• pp.805-812
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• 2013

The operational flight program(OFP) which has the functions of I/O processing with avionics, flight control logic calculation, fault diagnosis and redundancy mode is embedded in the flight control computer of Smart UAV. The OFP was developed in the environment of PowerPC 755 processor and VxWorks 5.5 real-time operating system. The OFP consists of memory access module, device I/O signal processing module and flight control logic module, and each module was designed to hierarchical structure. Memory access and signal processing modules were verified from bench test, and flight control logic module was verified from hardware-in-the-loop simulation(HILS) test, ground integration test, tethered test and flight test. This paper describes development environment, software structure, verification and management method of the OFP.

• Proceedings of the KIEE Conference
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• 2005.05a
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• pp.155-157
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• 2005

The Electrical Test Bed(ETB) integrates the test environment, required for acceptance tests of system level, prior to FM testing. The ETB will be used for the validation of system-level functions and interface between each subsystem. The FTB supports early functional and limited performance checkout of electrical subsystems. Therefore, it provides the environment for the verification of the Flight Software including AOCS, EPS, and TC&R simulators. These ETB will be composed of engineering version of spacecraft BUS, which are laid on the laboratory table.

• International Journal of Internet, Broadcasting and Communication
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• v.9 no.1
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• pp.29-34
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• 2017

Over the past several decades, embedded system and flight control computer technologies have been evolved to meet the diverse needs of the mobile device market. Current embedded systems are at the heart of technologies that can take advantage of small-sized specialized hardware while still providing high-efficiency performance at low cost. One of these key technologies is multiple memory banks. For example, a dual memory bank can provide two times more memory bandwidth in the same memory space. This benefit take lower cost to provide the same bandwidth. However, there is still few software technologies to support the efficient use of multiple memory banks. In this study, we present a technique to efficiently exploit multiple memory banks by software support. Specifically, our technique use an interference graph to optimally allocate data to different memory banks by an optimizing compiler. As a result, the execution time can be improved upto 7% with the proposed technique.

• Proceedings of the Korean Society of Computer Information Conference
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• 2020.01a
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• pp.3-4
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• 2020

공연을 위한 드론 군집비행의 제어시스템에 관한 기존의 연구 결과들은 실시간으로 반응하지 않으며, 비숙련자가 제어하기 어렵다는 문제점이 있다. 본 논문에서는 첫 번째로 HCI를 기반으로 한 웨어러블 형태의 장갑 컨트롤러를 사용한다. 두 번째로 각각의 음 정보에 실시간으로 반응하도록 FFT를 사용한 주파수 정보를 컴퓨터로 수신 받는다. 세 번째로 각각의 군집비행 움직임 정보를 복수의 드론에게 송신하는 새로운 방법의 드론 실시간 군집비행 제어시스템을 설계하였다.

• Proceedings of the Korea Information Processing Society Conference
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• 2008.11a
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• pp.1240-1241
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• 2008

저궤도 관측위성은 주어진 임무를 수행하기 위해 정해진 궤도에서 다양한 작업들을 수행하게 된다. 위성에 장착되어 있는 각종 센서들을 이용하여 자세를 제어하거나 전지를 충전시키고 지상 명령 및 저장되어 있는 명령에 따라 다양한 동작을 취하게 된다. 또한 각종 module들을 제어하기 위해 해당 module에 대해 주기적으로 pulse를 보내어 이를 제어하는 작업도 수행한다. 이때 수행되는 작업의 내용이나 위성의 상태를 정확히 파악하기 위해서는 지상과 위성에서 사용되는 시간이 동기가 되어야 한다. 본 논문에서는 GPS의 신호를 이용하여 위성의 제어 및 상태를 파악하기 위해 사용되는 기준 시간 동기화 방안에 대해 설명하도록 한다.

• Bulletin of the Korean Space Science Society
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• 2006.10a
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• pp.154-154
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• 2006

• Bulletin of the Korean Space Science Society
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• 2006.10a
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• pp.155-155
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• 2006

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.3
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• pp.88-94
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• 2004

The KSR-III rocket is a liquid propellant sounding rocket and thrust vector control actuators and cold gas thrusters are used to control pitch and yaw, roll attitude respectively during thrusting phase. In this paper, the structure of designed attitude controller and gain scheduling, results of stability analysis for KSR-III rocket are presented. The attitude controller is implemented with flight software in the domestically developed INS and successfully performed its function in the flight test. The flight data are coincident with simulation results.