• ICROS
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• v.3 no.2
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• pp.14-19
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• 1997

현존하는 비행체는 항공기에서 유도탄에 이르기까지 실로 그 종류가 다양하지만 대부분 비행체 운동 제어라는 공통된 기능과 특성을 갖는 자동비행조종 장치가 장착되어 있다. 본 고에서는 이러한 자동비행조종장치의 기술동향을 주로 Software 관점에서 살펴보고자 한다.

• Journal of the Institute of Electronics Engineers of Korea TE
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• v.39 no.4
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• pp.350-354
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• 2002

In this paper, we designed an autopilot of the unmanned piloted vehicle to guide to the specific position, and analyzed robustness of the designed autopilot. We divide an aircraft velocity into the three case which are low, cruising and high speed, and designed autopilot gains are gain scheduled. We generated the turbulence for the operational altitudes and proved robustness of the designed autopilot for the turbulence using simulation.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.36 no.11
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• pp.1104-1111
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• 2008

The supersonic advanced trainer based on digital flight-by-wire flight control system uses aircraft flight information such as altitude, calibrated airspeed and angle of attack to calculate flight control law, and this information is measured by IMFP(Integrated Multi-Function Probe) equipment. The information has triplex structure using three IMFP sensors. Final value of informations is selected by mid-value selection logic to have more flight data reliability. As the result of supersonic flight test, pitch oscillation is occurred due to IMFP noise when altitude hold autopilot mode is engaged. This tendency may affect stability and handling quality of an aircraft during autopilot mode. This paper addresses autopilot control law design to remove pitch oscillation and these control laws are verified by non-real time simulation and flight test. Also, pitch response characteristics of pitch attitude hold autopilot mode is improved by upgrading the control law structure and feedback gain tuning during bank turn.

• Aerospace Engineering and Technology
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• v.2 no.1
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• pp.11-21
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• 2003

This paper deals with preliminary design results of autopilot for station keeping mode of airship. Linear equations of motion for the airship are derived. Basic architecture of the control laws for cruising and station keeping modes are proposed. Performance analysis results show that autopilot design for station keeping mode of airship is feasible.

• 제어로봇시스템학회:학술대회논문집
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• 1987.10b
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• pp.537-540
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• 1987

항공기가 평형상태로 비행하는 도중 돌풍과 같은 외부교란을 만난 교란상태운동은 선형화된 미분방정식으로 표현되며 비교적 짧은 비행시간동안의 비행은 선형시 불변계가 된다. 돌풍은 Gauss-Markov확률과정으로 모델링 되며, 항공기가 돌풍을 만난 교란상태운동은 시스템론적으로 보면 백색잡음이 성형필터를 거쳐 계에 입력되는 것과 같다. 초기의 설계방법은 고전적인 주파수영역에서의 해석방법을 사용하였으나 1960년대에 최적제어이론이 도입되면서 평가함수를 사용하여 원하는 비행특성을 얻는 방법을 사용하게 되었다. 그 후 계에 입력되는 외란과 측정시의 잡음으로 인한 불확실한 측정량으로부터 최적상태변수의 추정을 위해 필터링이론을 도입한 확률제어이론을 적용하여 자동조종장치를 설계하게 되었다. 이때까지는 연속제어계로 설계되었으며 그 후 측정신호를 샘플링하여 연속제어계와 등가의 이산제어계를 사용한 자동조종장치가 등장하였으며 이 경우 설계기법으로는 연속제어계를 사용하고 실현시킬 때는 디지털컴퓨터를 사용하였다. 이는 제어하는 동안 계의 계수와 제어법칙을 바꾸어 줄 수 있는 이산제어계의 장점을 이용하지 못하므로 처음부터 계를 등가의 이산계로 보고 제어계를 설계하는 방법이 도입되었다. 이 때 샘플링간격의 결정과 Quantization 영향이 설계시 고려되어야 한다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.30 no.7
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• pp.130-136
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• 2002

In this paper, a flight test method is described for the system identification of the unmanned aerial vehicle equipped with an automatic flight control system. Multistep inputs are applied for both longitudinal mode and lateral/directional excitation. Optimal time step for excitation is sought to provide the broad input bandwidth. A programmed mode flight test method provides high-quality flight data for system identification using the flight control computer with the longitudinal and lateral/directional autopilot which enables the separation of each motion during the flight test. In addition, exact actuating input that is almost equivalent to the designed one guarantees the highest input frequency attainable. Several repetitive flight tests were implemented in the calm air in order to extract the consistent system model for the air vehicle. The enhanced airborne data acquisition system endowed the high-quality flight data for the system identification. The flight data were effectively used to the system identification of the unmanned aerial vehicle.

• 전기의세계
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• v.50 no.12
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• pp.4-11
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• 2001

• ICROS
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• v.3 no.5
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• pp.51-57
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• 1997

항공우주분야의 제어는 크게 항공기, 헬리콥터, 발사체, 미사일, 인공위성 등으로 비행체의 특성에 따라 크게 구분된다. 이러한 항공우주 시스템 설계시에는 다른 시스템 설계시와 동일하게 성능 요구조건을 설정한 후에 자동조정 장치를 설계하게 된다. 항공기의 경우에는 비행성과 조종성으롤 크게 구분하여 요구조건이 주어진다. 본 고에서는 항공기 비행제어에 적응제어가 어떻게 사용되었는가에 대하여 소개하였다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.44 no.12
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• pp.1035-1042
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• 2016

By using commercial flight simulation game engine, X-Plane, we have studied QTG(Qualification Test Guide) generation that can satisfy FTD level 5. Flight model is SR-20 of Cirrus. In list of QTG, There are some items to measure control forces. therefore, we have installed CLS(Control Loading System) to flight control devices in order to make it possible to measure control forces. We made Autopilot function externally to make flight model in trim conditions because X-Plane don't provide internal trim routine function. In addition to develop an algorithm, it can automatically perform the test. To avoid the inconvenience to control as it was to be carried out in same conditions. In case of FTD level 5, it is possible to use alternative data sources not only real flight data. By using these alternative data sources, all test results satisfy a scope given by CFR Part 60.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.16 no.3
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• pp.7-14
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• 2008

In modern aircraft, an autopilot system is getting more important. There are not many autopilot systems applied to small aircraft. Also the autopilot system in large or medium aircraft is difficult to apply to small aircraft directly. It is necessary to make a new autopilot system for small aircraft. In this paper, we implement the small aircraft simulator with autopilot system using SIMULINK. The various modes of autopilot - such as altitude select/hold, attitude hold, heading hold, etc. - are implemented to the flight simulator and tested. We also implement the VOR mode for aircraft guidance.