• 정보과학회 논문지
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• 제44권7호
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• pp.649-657
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• 2017

드론의 종류와 목적이 다양해지고 부가기능이 많아지면서 소프트웨어의 역할이 증가되고 있다. ARINC 653은 파티셔닝을 통해 항공전자 시스템의 소프트웨어 재사용 및 통합을 안정적으로 제공하고 SWaP(Size, Weight and Power) 문제를 효율적으로 해결할 수 있다. ARINC 653은 대형 항공기 외에 소형 무인비행체인 드론에도 효과적으로 적용될 수 있다. 본 논문에서는 드론의 비행제어 프로그램에 ARINC 653을 적용하기 위하여 계층적 ARINC 653을 확장하여 파티션 내 통신을 구현하고 실제 드론 시스템에 적용한 사례를 보인다. 실험 결과, 파티션 내 통신의 오버헤드가 낮으며, ARINC 653의 파티셔닝 기능에 의해서 드론의 비행제어 프로그램에 할당된 자원이 보장됨을 확인할 수 있다.

• E2M - 전기 전자와 첨단 소재
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• 제10권8호
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• pp.836-842
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• 1997

• 대한전자공학회:학술대회논문집
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• 대한전자공학회 2004년도 학술대회지
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• pp.463-467
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• 2004

A FTS (Flight Termination System) is a system that resides in a flying object such as a rocket, unmanned airplane, helicopter, missile, etc., receives commands from ground stations or detects coordinates automatically, and accomplishes a destruction command in case the object does not follow the presumed orbit. In this paper, we address the implementation of a communication modem for the FTS modem. We present general theory, simulation results using Matlab, and several results on the implementation using VHDL.

• IEIE Transactions on Smart Processing and Computing
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• 제6권3호
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• pp.175-182
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• 2017

In this paper, we present a multi-depth generation method using a time-of-flight (ToF) fusion camera system. Multi-view color cameras in the parallel type and ToF depth sensors are used for 3D scene capturing. Although each ToF depth sensor can measure the depth information of the scene in real-time, it has several problems to overcome. Therefore, after we capture low-resolution depth images by ToF depth sensors, we perform a post-processing to solve the problems. Then, the depth information of the depth sensor is warped to color image positions and used as initial disparity values. In addition, the warped depth data is used to generate a depth-discontinuity map for efficient stereo matching. By applying the stereo matching using belief propagation with the depth-discontinuity map and the initial disparity information, we have obtained more accurate and stable multi-view disparity maps in reduced time.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2001년도 춘계학술대회논문집D
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• pp.1008-1013
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• 2001

KSR-III propulsion system designed in KARI has a gas-pressurization system for propellant feeding system. This system uses a regulator for the control of the ullage pressure of propellant tank and a venturi for passive control of propellant flowrate. This system seems to be very reliable, but the flowrate of propellant varies according to the change of acceleration with the rocket flight. In this paper, dynamic characteristic of KSR-III propulsion feeding system was analyzed in flight condition. The purpose of this research is to find the variation of off ratio and propellant flowrate change for certification condition of engine reliability test.

• Journal of Mechanical Science and Technology
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• 제18권11호
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• pp.2021-2031
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• 2004

A new nondimensional method for predicting the windmilling performance of centrifugal -flow turbojet engines in flight has been developed. The method incorporates loss correlations to estimate the performance of major engine components. Given basic engine geometry, flight Mach number, and ambient conditions, this method predicts transient and steady-state windmilling performance. Thus, this method can be used during the preliminary design stage when detailed hardware geometry and component performance data are not yet available. A nondimensional time parameter is newly defined, and using this parameter, the transient performance of different types of turbojets (e.g. centrifugal vs. axial) is compared. In addition, the predictions' sensitivity to loss correlations, slip factors, and inlet ambient temperatures are analyzed.

• 대한전기학회:학술대회논문집
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• 대한전기학회 2005년도 제36회 하계학술대회 논문집 D
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• pp.2546-2548
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• 2005

본 논문에서는 무인항공기의 비행제어시스템 개발 및 성능분석을 위한 HILS(Hardware-in-the-Loop-Simulation) 시스템의 구축을 제안한다. 제안한 HILS 시스템은 실시간 시뮬레이션 컴퓨터(dSPACE DS1005), 3축 모션테이블, 자세 센서, 지상통제장치(GCS; Ground Control Station), 비행제어컴퓨터(FCC; Flight Control Computer)로 구성된다. 실제 신호와 유사한 신호를 발생시키기 위한 실시간 시뮬레이션 컴퓨터는 dSPACE가 담당하며, 이 신호는 비행운동을 재현을 위한 3축 모션테이블을 동작시키게 된다. 모션테이블 상에 위치하는 자세센서 값과 GCS의 명령은 FCC의 입력으로 사용된다. 구현된 HILS 시스템을 이용하여 UAV의 제어알고리즘 및 자세센서 성능 검증을 수행하였다.

• 대한전기학회:학술대회논문집
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• 대한전기학회 2005년도 심포지엄 논문집 정보 및 제어부문
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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 Aeronautical and Space Sciences
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• 제10권2호
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• pp.148-160
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• 2009

By the development of recent technology, a new variant of rotorcrafts having four rotors start drawing attention from aerial-robotics engineers more than before. Its potential spans from just being control device test bed to performing difficult task such as carrying surveillance device to unreachable places. In this regards, modeling a quad-rotor is significant in analyzing its dynamic behavior and in synthesizing control system for such a vehicle. This paper summarizes the modeling of a mini quad-rotor aerial vehicle. A first principle approach is considered for deriving the model based on Euler-Newton equations of motion. The result of the modeling is a simulation platform that is expected to acceptably predict the dynamic behavior of the quad-rotor in various flight conditions. Linear models associated with different flight condition can be extracted for the purpose of control synthesis.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2002년도 학술대회지
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• pp.87-90
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• 2002

Computational study has been undertaken to investigate the aerodynamic influence of side jet on a supersonic missile and to find a similarity condition between the flight condition and the wind tunnel testing. Tasks were performed to validate the existing Raytheon test body with side jet, to simulate the flow inside the supersonic wind tunnel, and to compare the flow fields between the missile in free flight and that in the wind tunnel. Then sub-scale model of body-tail configuration was analyzed to estimate the influence of the side jet on the missile components. It Is found that the influence of side Jet is not as significant on the tail region as on the body surface and a simple algebraic formula for aerodynamic coefficients accounting for the side jet as a point force may be cautiously utilized in setting up control logic.