• Journal of Advanced Navigation Technology
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• v.27 no.3
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• pp.293-299
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• 2023

UPRT(Upset Prevention And Recovery Training) is an accident prevention training program developed over a three-year period after the main cause of aircraft accidents in commercial aviation between 2001 and 2011 was analyzed as LOC-I(Loss Of Control Flight). In 2014, ICAO presented UPRT for fixed-wing aircraft through Doc.10011(Manual On Aeroplane Upset Prevention And Recovery Training) and recommended mandatory implementation to Contracting States from March 2019. Since naval P-3C is a major mission of maritime patrol and anti-submarine warfare, it takes a lot of time to fly at low altitude (70-600 m), and the majority of P-3C pilots have experienced spatial disorientation, so Upset prevention and recovery training is essential for naval P-3C pilots. To this end, this study intends to present measures for UPRT from limited conditions using the P-3C simulator owned by the Navy.

• Journal of Advanced Marine Engineering and Technology
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• v.36 no.4
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• pp.512-519
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• 2012

This paper proposes a 3-D pose (positions and orientations) estimation system based on the recognition of circular ring patterns. To deal with monocular vision-based pose estimation problem, we specially design a circular ring pattern that has a simplicity merit in view of object recognition. A pose estimation procedure is described in detail, which utilizes the geometric transformation of a circular ring pattern in 2-D perspective projection space. The proposed method is evaluated through the analysis of accuracy and precision with respect to 3-D pose estimation of a quadrotor-type vehicle in 3-D space.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.12
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• pp.1217-1224
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• 2009

A simple and effective guidance and control scheme that enables autonomous three-dimensional path-following for a fixed wing aircraft is presented. The method utilizes the nonlinear path-following guidance law for the outer loop that creates steering acceleration command based on the desired flight path and the current position and velocity of the vehicle. The scheme considers the gravity in the guidance level, where it is subtracted from the acceleration command to form the specific force acceleration command which the aircraft is better suited to follow than the total acceleration command in the inner-loop. A roll attitude control scheme is also presented that enables inverted flight or sideslip maneuvers such as slow roll and knife-edge. A series of aerobatic maneuvers are demonstrated through simulations to show the potential of the proposed scheme.

• Journal of Advanced Navigation Technology
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• v.8 no.1
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• pp.19-26
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• 2004

This paper deals with the automatic flight control system for an unmanned target drone which is operated by an army as an anti-air gun shooting training. By automation of unmanned target drone that is manually operated by external pilot, pilot can reduce workload and an army can reduce the budget. Most UAVs which are developed until today use high-cost sensors as AHRS and IMU to measure the attitude, but those are contradictory for the reduction of budget. This paper says the development of low-cost automatic flight control system which makes possible of automatic flight with low-cost sensors. We have developed the integrated automatic flight control system by integrating electricity module, switching module, monitoring module and RC receiver as an one module. We also prove the performance of automatic flight control system by flight test.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.45 no.9
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• pp.711-723
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• 2017

This paper proposes a flight control system for an organic flight array(OFA) which has a new configuration to consist of multi modularized ducted-fan unmanned aerial vehicles (UAVs). The OFA is able to apply to various missions such as indoor reconnaissance, communication relay, and radar jamming by using capability of hover flight. The OFA has a distinguished advantage due to reconfigurable structure to assemble or separate with respect to its missions or operational conditions. A dynamic modelling of the OFA is derived based on equations of motion of the single ducted-fan modules. In order to apply nonlinear control method, an affine system of attitude dynamics is derived. Moreover, the control system is composed of a back-stepping controller for attitude control and a PID controller for position control. Then the performance of the proposed controller is verified via a numerical simulation under wind disturbance.

• Bulletin of the Korean Space Science Society
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• 2003.10a
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• pp.58-58
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• 2003

과학위성 1호의 컴퓨터 시스템은 지상국 명령 및 데이터 처리, 위성 자세 제어, 위성체 운용, 상태 감시, 탑재체 운용, 배터리의 충방전 제어 등을 담당하며, 우리별 3호 위성을 통하여 검증된 컴퓨터 시스템을 기반으로 개발되었다 과학위성 1호의 컴퓨터 시스템은 탑재 컴퓨터(On-board Computer)와 비행 소프트웨어(Flight Software)로 구성된다. 과학위성 1호의 탑재 컴퓨터는 우리별 3호의 탑재 컴퓨터에 비하여 FPGA를 사용함으로써 크기 및 무게의 소형화를 추구하였고, 네트워크 제어기를 내장함으로써 통신 성능의 개선을 이루었다. 그리고 EEPROM을 장착하여 위성 운용 기간 도중에 발생할 수 있는 소프트웨어의 변경에도 대응하였다 과학위성 1호의 비행 소프트웨어는 우리별 3호의 비행 소프트웨어를 기반으로 하여 과학위성 1호의 명령 및 데이터 처리 시스템과 임무에 적합하도록 개발되었다.

• The Proceeding of the Korean Institute of Electromagnetic Engineering and Science
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• v.2 no.4
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• pp.26-32
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• 1991

Korea Aerospace Research Institute(KARI) performs research on developing the scientific sounding rocket(KSR-420S) for measuring ozone profile and atmosphere layer over korean peninsula. Informations about performances of flighting scientific rocket, that is temperature, strain, acceleration, pressure, rocket attitude and ranging data, and measuring data of ozone, ionosphere and X-ray are transmitted ground system by rocket onboard transmitting system. In this paper, the telemetry ground system which is compatible with the KSR-420S is designed for tracking the trajectory and receiving the incoming signals.

• Proceedings of the KIEE Conference
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• 2004.07d
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• pp.2218-2220
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• 2004

조종사 없이 사전에 입력된 프로그램 또는 인공지능에 의해 기체 스스로 판단하여 자율비행하는 비행체를 무인 항공기라 한다.[6] 이러한 비행을 위해서는 기체의 위치, 자세, 속도 등의 정보가 필요하다. 본 논문에서는 3축 가속도센서 1개 및 1축 자이로센서 3개를 서로 수직으로 구성하는 관성항법 시스템에 자기콤파스, 고도센서, GPS등의 비관성센서를 추가로 구성하여 시스템을 설계하였으며 칼만필터를 이용하여 시스템의 오차를 추정하고 이를 되먹임 시킴으로써 오차를 정정한다.

• 제어로봇시스템학회:학술대회논문집
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• 1986.10a
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• pp.619-622
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• 1986

컴퓨터 기술의 발달에 따라 디지탈 전산기는 연산처리 능력이 더욱 빨라지고, 더욱 큰 기억용량을 갖게 되었다. 따라서 산업공정, 화학프랜트, 원자력발전 및 항공분야 등의 복잡한 연속 동특성계에 대한 실시간 시뮬레이션이 가능하게 되었다. 특히 복잡한 연속 동특성계의 시뮬레이션 목적으로 Multiprocessor 형태의 전산기가 개발되었다. 이 Multiprocessor형태의 전산기는 D/A 변환기와 A/D 변환기를 갖추므로써 실시간 실물 모의시험(A real time hardware-in-the-loop simulation) 시의 컴퓨터와 외부장비와의 데이타 전달이 용이하여 졌다. 본 연구에서는 비행체의 비행자세를 제어하기 위한 조종장치의 설계해석 및 성능시험을 위하여 Multiprocessor를 이용하여 실시간 실물 모의실험이 가능함을 보였다. 본 시뮬레이션에 사용된 전산기는 AD10 전산기이다.

• The Science & Technology
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• v.34 no.2 s.381
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• pp.30-31
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• 2001

UFO는 '미확인물체'라는 뜻이므로 그런 물체는 우주 도처에 얼마든지 있을 수 있다. 그러나 오늘날의 과학이 갖고 있는 한계로는 외계인이 타고 온 비행체일 가능성은 거의 없다. 우주실험실, 우주정거장, 우주공장 등 연구영역을 우주로 확대해 나가고 있는 이 시점에서 우주를 향한 우리 과학자들의 자세를 한번 점검해 보아야 할 것이다.