• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 1997년도 한국자동제어학술회의논문집; 한국전력공사 서울연수원; 17-18 Oct. 1997
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• pp.1663-1666
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• 1997

The purpose of this paper is to find how to determine the controllability and stability derivatives form flight test and to display the stability of the Twinbee aircraft. There are various methods developed to find the derivatives : wind tunnel testing, predicted result from empirical data, flight test and so on. Among those methods, the estimation form flight test of real aricraft is the most reliable. We performed the flight test of Twinbee and recorded the states of aorcraft. Using those states and parameter setimation algorithem based on the Maximum Likdlihood(MMLE) criterion, we can estimate the controllability and stability derivatives. In this paper, wel will show the process form designing the proper flight test input to estimation of derivatives.

• 한국항공운항학회지
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• 제16권3호
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• pp.1-6
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• 2008

The stalling speed flight test of light airplane, ChangGong-91, was performed to acquire the certification. With power-off engine condition, the wings level stall flight tests were conducted at the aircraft configuration of various flap angle - clean, 20degree, and full flap, respectively. They were performed considering with the combination of the maximum and minimum test weight, and forward and afterward center of gravity. The stalling speeds and the minimum speeds of light airplane were determined from the results of flight test. Also, the appropriateness of stall warning speeds are evaluated through the flight test measures. The airplane is recoverable only with pitch control and engine throttle from stall state without exceptional operation.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 1996년도 한국자동제어학술회의논문집(국내학술편); 포항공과대학교, 포항; 24-26 Oct. 1996
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• pp.199-202
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• 1996

In this paper, we used the maximum likelihood method for 2-point aerodynamic model to determine the parameters of the ChangGong-91. Since the estimation from the flight test of real aircraft is the most reliable, we performed the flight test of ChangGong-91 to get the parameters such as velocity, height, 3 axis acceleration, 3 axis angular rate, pitch angle, angle of attack, temperature and so on. We recorded the flight test data in S-VHS tapes and stored them to personal computer using A/D(analog to digital) converter. Flight test was done in stall motion, and the acquired data was be processed with parameter identification method.

• 한국항공우주학회지
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• 제45권2호
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• pp.133-139
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• 2017

틸트로터 무인기의 비행제어컴퓨터는 신뢰도 향상을 위하여 주 채널과 보조 채널을 갖는 이중화 시스템으로 설계되었다. 이중화 기능은 채널 전환과 데이터 복원으로 구성된다. 채널 전환 기능은 교차채널 데이터링크를 이용한 소프트웨어 방식과 워치독 타이머를 이용한 하드웨어 방식으로 구성되었다. 데이터 복원 기능은 운용 중 비행제어컴퓨터가 비정상적으로 재시작 되었을 때 비행 상태를 유지하기 위한 기능이다. 이중화 기능은 비행제어컴퓨터 벤치 시험, 체계 통합 시험 그리고 HILS 시험을 통해 검증되었다. 본 논문에서는 틸트로터 무인기 비행제어컴퓨터에 구현된 이중화 기능과 시험-검증 방법에 대해서 기술하였다.

• 한국추진공학회지
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• 제12권3호
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• pp.41-48
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• 2008

고체추진기관의 지상연소시험시 점화통제시스템은 추진기관의 점화를 위해 착화기에 점화전류를 공급하여 추진기관을 연소시키는 것이 기존의 주요기능이었다. 본 논문에서는 다양한 방식의 점화 이벤트와 비행 시퀀스를 제어하고 검증할 수 있는 지상연소시험용 점화통제시스템에 대한 설계 및 구현에 대해 기술하였다.

• International Journal of Aeronautical and Space Sciences
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• 제17권1호
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• pp.120-131
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• 2016

The full results of troubleshooting process related to the flight control system of a tilt-rotor type UAV in the flight tests are described. Flight tests were conducted in helicopter, conversion, and airplane modes. The vehicle was flown using automatic functions, which include speed-hold, altitude-hold, heading-hold, guidance modes, as well as automatic take-off and landing. Many unexpected problems occurred during the envelope expansion tests which were mostly under those automatic functions. The anomalies in helicopter mode include vortex ring state (VRS), long delay in the automatic take-off, and the initial overshoot in the automatic landing. In contrast, the anomalies in conversion mode are untrimmed AOS oscillation and the calibration errors of the air data sensors. The problems of low damping in rotor speed and roll rate responses are found in airplane mode. Once all of the known problems had been solved, the vehicle in airplane mode gradually reached the maximum design speed of 440km/h at the operation altitude of 3km. This paper also presents a comprehensive detailing of the control systems of the tilt-rotor unmanned air vehicle (UAV).

• 한국항공우주학회지
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• 제36권11호
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• pp.1104-1111
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• 2008

고등훈련기급에 탑재되어 있는 전기식 비행제어계통 (digital fly-by-wire flight control system)은 통합 다기능 감지기(IMFP : Integrated Multi-Function Probe)를 이용하여 항공기의 고도/속도/받음각 정보를 획득한다. 고등훈련기에는 3개의 IMFP가 장착되어 있으며, 이는 비행제어법칙에 3중의 공기정보를 제공한다. IMFP로부터 제공된 3개의 공기 정보는 중간 값을 채택하여 보다 신뢰성 있는 정보를 비행제어법칙에 제공한다. 초음속 비행시험 결과, 초음속 영역에서 발생하는 잡음이 포함된 IMFP로 인하여 고도유지모드 자동조종장치를 작동시켰을 때, 세로축으로 진동현상이 발생하였다. 이러한 현상은 자동조종장치를 이용하여 비행을 할 경우, 항공기 안정성 및 조종성을 저해할 수 있다. 본 논문에서는 초음속 영역에서 발생하는 IMFP 잡음정보가 자동조종장치에 영향을 미치지 않도록 비행제어법칙을 설계하였으며, 제어법칙설계 및 귀환이득을 조율하여 선회비행 시에 피치자세각 유지모드를 개선하였다. 설계된 비행제어법칙은 비실시간 시뮬레이션 및 비행시험을 통하여 검증하였다.

• 한국군사과학기술학회지
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• 제8권1호
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• pp.39-48
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• 2005

After the development of the Firefly, flight tests have been performed to verify the performance and get the parameters for the mathematical model of the aircraft. The flight test data is used to get parameters for the mathematical model of the aircraft through the parameter identification process. An arbitrary control input is applied to the test flight which is a part of parameter identification process. A square wave has been used a control input which is called Doublet signal. The aspect of the signal is same length and magnitude in both (+) and (-) directions such as sine wave. The Doublet signal is composed of a dominant frequency and many high frequencies, so that it is appropriate signal to excite the motion of an aircraft. In this paper, the control input of the flight test data has been analyzed to check the efficiency of the control input using DFT(Discrete Fourier Transform). From the result of analysis, an alternative input was extracted.

• 항공우주시스템공학회지
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• 제3권1호
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• pp.1-5
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• 2009

The flight control of the T-50 advanced trainer is conducted by the digital FBW (Flight-by-Wire) control system. The system input data consist of flight conditions such as altitude, airspeed, and angle of attack. And the flight conditions of the aircraft are obtained from IMFP (Integrated Multi-Function Probe). The T-50 aircraft equip three IMFP sensors. To ensure reliability in flight condition data obtained from each IMFP sensor, the mean value of flight conditions is used as the input of the control system. In this study, the effect of an installation angle of IMFP sensors on estimation of flight altitude was investigated by flight test results in the supersonic region.

• 한국항공운항학회지
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• 제28권4호
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• pp.82-88
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• 2020

Currently, flight training is not only a technical instruction that teaches maneuvering operations, but has expertise equal to that of general disciplines. Therefore, flight instructors must have academic knowledge and flight skills. As flight instructors are the first teacher in flight training for students who have never experienced actual flight control, the behavior of flight instructors will affect the students' flight education. Therefore, the influence of flight instructors for students are quite large compared to other educational institutions. In this study, the factors of instructional behavior were determined, and the actual state of instructional behavior of flight instructors were confirmed through students' survey. Improvements were derived to solve the problems identified in the survey results. For the follow-up analysis, improvements were applied to the flight instructors for 8 months, and then re-question was conducted to the same students who responded to the first questionnaire to find out the difference in results before and after through a paired t-test.