• International Journal of Aeronautical and Space Sciences
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• 제5권1호
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• pp.57-63
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• 2004

UAV(Unmanned Aerial Vehicle) has become one of the most popularmilitary/commercial aerial robots in the new millennium. In spite of all theadvantages that UAVs inherently have, it is not an easv job to develop a UAVbecause it requires very systematic and complete approaches in full developmentenvelop. The ground test and evaluation phase has the utmost importance in thesense that a well-developed system can be best verified on the ground. In addition,many of the aircraft crashes in the flight tests were resulted from the incompletedevelopment procedure. In this research, a verification procedure of the wholeairbome integrated system was conducted including the flight management system.An airbome flight control computer(FCC) senses the extemal environment from thepehpheral devices and sends the control signal to the actuating system using theassigned control logic and flight test strategy. A ground test station controls themission during the test while the downlink data are transferred from the flightmanagement computer using the serial communication interface. The pilot controlbox also applies additional manual actuating commands. The whole system wastested/verified on the wind-tunnel system, which gave a good pitch controlperformance with a preUspecified flight test procedure. The ground test systemguarantees the performance of fundamental functions of airbome electronic systemfor the future flight tests.

• 한국항공운항학회지
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• 제22권2호
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• pp.16-26
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• 2014

After the GBAS ground system installing at the airport, a GBAS ground and flight testing must be conducted to verify functionality and performance of the system. Since Korea has no experience of the GBAS ground system installation, GBAS test and evaluation methods have never been studied so far. Therefore this paper analyzes the test items and methods for the GBAS ground and flight testing based on ICAO documents, FAA flight inspection manual and testing reports of other countries. As a result of the analysis, this paper proposes the GBAS ground and flight testing items in korea, also describes the flight procedures for the GBAS flight testing.

• Journal of Positioning, Navigation, and Timing
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• 제2권1호
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• pp.41-48
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• 2013

When the ground subsystem of Ground Based Augmentation System(GBAS) is installed at the airport, the functions and performance of subsystem should be evaluated through ground and flight testing at the pre-commissioning phase. In the case of GBAS flight testing, it can be conducted by the existing flight check aircraft, but the GBAS ground testing requires the development of specially customized equipment to perform the ground testing. Therefore, this paper describes the preliminary design of GBAS onboard test equipment which can be independently used for the GBAS ground testing and flight testing on a car and an aircraft.

• 한국항공우주학회지
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• 제40권9호
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• pp.800-806
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• 2012

본 논문은 지상지원과 지상관제의 기능을 결합한 무인항공기의 비행시험을 위한 통합형 지상지원시스템(Ground support system)에 대한 설계 및 개발에 관해 기술한다. 통합비행시험은 비행체의 성능을 검증하기 위한 필수적인 절차이다. 개발한 통합형 지상지원시스템은 비행시험에 필요한 인적 물적 자원과 시간을 절감하고 비행시험의 체계적인 준비와 진행을 하기 위한 인프라로써 비행시험의 제반 사항을 갖추어 지상관제, 통신, 발전, 장비의 수송, 수리와 유지 등이 가능하며 소규모 연구소에서 2~3명의 인원으로 운용하기에 적합한 수준이다.

• 한국항공우주학회지
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• 제35권5호
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• pp.452-459
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• 2007

본 논문에서는 PC104를 메인프로세서로 사용하여 GPS와 IMU를 이용한 비행제어시스템을 구축하였다. 안전을 위해 PIC16을 이용한 자동/수동 변환 모듈을 제작하였으며, 계속 목표 지점을 향해 비행하기 위해 호밍 방식의 유도 알고리즘을 구성하였다. 지상 실험을 통해 각각의 시스템이 원활하게 작동하는지 확인하였으며 상용 비행제어시스템과 유사한 출력을 나타냄을 확인함으로써 본 시스템이 무인항공기 제어시스템으로 사용될 수 있음을 보였다

• 제어로봇시스템학회논문지
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• 제14권8호
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• pp.824-836
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• 2008

Relaxed static stability(RSS) concept has been applied to improve aerodynamic performance of modern version supersonic jet fighter aircraft. Therefore, flight control systems are necessary to stabilize an unstable aircraft, and provides adequate handling qualities and achieve performance enhancements. Standard FCSDVP (Flight Control System Design and Verification Process) is provided to reduce development period of the flight control system. In addition, if this process is employed in developing flight control system, it reduces the trial and error for development and verification of flight control system. This paper addresses the flight control system design and verification process for the RSS aircraft utilizing design goal based on military specifications, linear and nonlinear system design and verification based on universal software, handling quality test based on HILS(Hardware In-the-Loop Simulator) environment, and ground and flight test results to verify aircraft dynamic flight responses.

• 항공우주기술
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• 제9권1호
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• pp.1-8
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• 2010

스마트무인기의 비행시험에 앞서 비행제어시스템을 포함한 전체 무인기 체계의 건전성을 검증하기위한 지상통합시험을 수행하였다. 지상통합시험은 비행체 인터페이스 시험, 비행체 HILS시험, 지상파워시험, 4자유도 치구시험, 안전줄 호버시험 순서로 진행되었으며, 각각의 시험을 통해 전체 무인기 시스템의 안전성을 입증하였다. 본 논문에서는 국내 최초로 개발된 틸트로터인 스마트무인기의 지상시험 절차와 각 시험에서 획득한 데이터 분석결과를 제시하였다. 지상시험 결과 비행제어시스템의 안전성이 충분히 입증되었으며, 비행시험이 수행가능하다고 판단되었다.

• 한국항공운항학회지
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• 제15권4호
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• pp.9-16
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• 2007

Tilt rotor aircraft can take off and land vertically and cruise faster than any other helicopter. A scaled flight demonstration model of a tilt rotor aircraft has been developed by KARI. Because the flight characteristics of tilt rotor are not well known, the developed scaled model would be helpful to evaluate flight control algorithm of a full scale aircraft. The tethered hover test has been performed in order to improve hover flight characteristics of tilt rotor aircraft prior to flight test of the small scaled model. During the tethered hover test, the performance of rotor speed governor, rate SAS (Stability Augmentation System) and control surface mixers have been evaluated. We expect that the results of real flight hover test would be quite same as tethered hover test. Therefore the tethered hover test results will reduce the risk of flight test properly by fixing some of hidden problems which might occur during the flight test. This paper presents the results of tethered hover test in detail and shows how it could be final ground test before flight test. The control mixer gain and rate SAS feedback gains were modified in order to get higher controllability and stability during the tethered hover flight. The rotor governor showed that it could keep rotor RPM constant with very small deviation even during severe pilot collective input change. The tethered hover test results gave pilot and engineers confirmation and experience about the scheduled flight test.

• 항공우주기술
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• 제13권1호
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• pp.1-9
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• 2014

고흥항공센터는 전남 고흥 간척지에 위치하며 길이 700m, 폭 25m의 활주로를 통해 국내에서 개발된 무인기의 비행시험장으로 활용되고 있으며 비행체 조립 및 점검을 위한 시험동을 갖추고 있다. 항공센터에서 이루어지는 개발 항공기들의 항공안전을 위하여 비행시험 지원설비를 구축하고 있으며 현재 지상감시시설로서 1090ES ADS-B를 구축하였다. ADS-B는 차세대 항행감시 장비로서 위성항법과 데이터 통신을 기반으로 항행정보를 실시간으로 공유할 수 있으며 구축된 ADS-B 지상국과 ADS-B 송신기간 지상 및 비행시험을 통하여 ADS-B 지상국의 정상적인 운용과 비행시험 활용 가능성을 확인하였다.

• 한국군사과학기술학회지
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• 제9권2호
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• pp.87-95
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• 2006

The performance of a microwave missile seeker and radar operating in an air-to-air look-down mode is strongly influenced by the presence of ground clutter In order to correctly account for the effects of ground clutter, it is required to develop a model capable of representing clutter characteristics as a function of range and/or frequency. In this paper, a program to estimate the clutter reflectivity for various ground conditions is developed, using the actually measured data and the data available from open literatures. In addition, clutter characteristics measured for various ground conditions such as sea, agricultural area, urban city and industrial area through the captive flight tests are presented.