• Title, Summary, Keyword: flight control

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Development of a Reconfigurable Flight Controller Using Neural Networks and PCH (신경회로망과 PCH을 이용한 재형상 비행제어기)

  • Kim, Nak-Wan;Kim, Eung-Tai;Lee, Jang-Ho
    • Journal of Institute of Control, Robotics and Systems
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    • v.13 no.5
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    • pp.422-428
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    • 2007
  • This paper presents a neural network based adaptive control approach to a reconfigurable flight control law that keeps handling qualities in the presence of faults or failures to the control surfaces of an aircraft. This approach removes the need for system identification for control reallocation after a failure and the need for an accurate aerodynamic database for flight control design, thereby reducing the cost and time required to develope a reconfigurable flight controller. Neural networks address the problem caused by uncertainties in modeling an aircraft and pseudo control hedging deals with the nonlinearity in actuators and the reconfiguration of a flight controller. The effect of the reconfigurable flight control law is illustrated in results of a nonlinear simulation of an unmanned aerial vehicle Durumi-II.

Flight Control Test of Quadrotor-Plane with Hybrid Flight Mode of VTOL and Fast Maneuverability (Hybrid 비행 모드를 갖는 Quadrotor-Plane의 비행제어실험)

  • Kim, Dong-Gyun;Lee, Byoungjin;Lee, Young Jae;Sung, Sangkyung
    • Journal of Institute of Control, Robotics and Systems
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    • v.22 no.9
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    • pp.759-765
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    • 2016
  • This paper presents the principle, dynamics modeling and control, hardware implementation, and flight test result of a hybrid-type unmanned aerial vehicle (UAV). The proposed UAV was designed to provide both hovering and fixed-wing type aerodynamic flight modes. The UAV's flight mode transition was achieved through the attitude transformation in pitch axis, which avoids a complex rotor tilt mechanism from a structural and control viewpoint. To achieve this, a different navigation coordinate was introduced that avoids the gimbal lock in pitch singularity point. Attitude and guidance control algorithms were developed for the flight control system. For flight test purposes, a quadrotor attached with a tailless fixed-wing structure was manufactured. An onboard flight control computer was designed to realize the navigation and control algorithms and the UAV's performance was verified through the outdoor flight tests.

A Study on the Design and Validation of Switching Mechanism in Hot Bench System-Switch Mechanism Computer Environment (HBS-SWMC 환경에서의 전환장치 설계 및 검증에 관한 연구)

  • Kim, Chong-Sup;Cho, In-Je;Ahn, Jong-Min;Lee, Dong-Kyu;Park, Sang-Seon;Park, Sung-Han
    • Journal of Institute of Control, Robotics and Systems
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    • v.14 no.7
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    • pp.711-719
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    • 2008
  • Although non-real time simulation and pilot based evaluations are available for the development of flight control computer prior to real flight tests, there are still many risky factors. The control law designed for prototype aircraft often leads to degraded performance from the initial design objectives, therefore, the proper evaluation methods should be applied such that flight control law designed can be verified in real flight environment. The one proposed in this paper is IFS(In-Flight Simulator). Currently, this system has been implemented into the F-18 HARV(High Angle of Attack Research Vehicle), SU-27 and F-16 VISTA(Variable stability. In flight Simulation Test Aircraft) programs. This paper addresses the concept of switching mechanism for FLCC(Flight Control Computer)-SWMC(Switching Mechanism Computer) using 1553B communication based on flight control law of advanced supersonic trainer. And, the fader logic of TFS(Transient Free Switch) and stand-by mode of reset '0' type are designed to reduce abrupt transient and minimize the integrator effect in pitch axis control law. It hans been turned out from the pilot evaluation in real time that the aircraft is controllable during the inter-conversion process through the flight control computer, and level 1 handling qualities are guaranteed. In addition, flight safety is maintained with an acceptable transient response during aggressive maneuver performed in severe flight conditions.

A Study on Qualification Procedures of Flight Control Software on Military Aircraft (군용항공기 비행제어 소프트웨어 품질인증 절차에 관한 연구)

  • Heo, Jin-Goo
    • Journal of the Korean Society for Quality Management
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    • v.41 no.3
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    • pp.433-441
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    • 2013
  • Purpose: This study investigates software qualification procedures based on the FA-50 flight control software to satisfy high reliability and flight safety. Methods: We studied software qualification categories, standard/specification and developed country case. We proposed procedure to satisfy not only flight safety but also international standard. Results: The proposed software qualification procedure satisfied flight safety and airworthiness based on the testing result of the FA-50 flight control software. Conclusion: This paper showed an appropriate qualification procedures of the flight control software in domestic circumstance through the FA-50 flight control software qualification.

A Model of a Mechanical Flight-Control System for Simulating Control Authority Switching of a Helicopter Technical Demonstrator (헬리콥터 기술시범기의 비행제어 조종권 전환 모의를 위한 기계식 조종장치 모델 설계 연구)

  • Yang, Chang Deok
    • Journal of Aerospace System Engineering
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    • v.11 no.2
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    • pp.23-29
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    • 2017
  • Since the flight-control system is critical for the safety of an aircraft, a fail-safe system is needed in a flight demonstrator used to test a new flight-control system. A backup control system is also needed to ensure safety in using a mechanical flight-control system. This paper presents a development of an MFCS (Mechanical Flight Control System) model for simulating control authority switching of a helicopter technical demonstrator, as well as the results of evaluating the developed MFCS model.

A Study on Standardization on the Flight Controller Mode in Remotely Piloted Aircraft Drone : Focused on Drone Controller Mode Preference (원격조종항공기 드론 조종기모드 표준화 연구 : 드론 조종기모드 선호도를 중심으로)

  • Park, Wontae
    • Journal of the Society of Korea Industrial and Systems Engineering
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    • v.42 no.4
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    • pp.69-75
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    • 2019
  • Remotely Piloted Aircraft (RPA) controls as a type of unmanned aerial vehicle (drone) is growing rapidly and its flight controller stick disposition is required standardization. We should standardize RPA drone flight control disposition because the flight pilot of RPA is hard to be trained so the flight controller stick differences impairs safety and wastes time and effort of flight controller industry. So this study researches the on-going standardization of RPA drone flight control disposition in Korea and foreign countries. Also this paper analyzes and researches of expert about RPA drone flight controller function and application of flight control mode. I accomplished expert research about standardization plan of unmanned flight control mode and confirm the necessity. Nowadays mode1 and 2 are mostly used in Korea so I carried out preference investigation for two modes. There were 4 preferences choices of RPA drone control mode necessity (importance) and recommendation of standardization modes. They answered that necessity of standardization is important considering pilot training, flight safety and positive development of drone industry. The result of standardization mode preference is that they prefer mode 2 (drone maker 86%, training facilities and research facilities 58%, government bureau 60%). Overall preference result shows that mode 1 24%, mode 1&2 16%, mode 2 60%. So they preferred mode 2 by 60%. The differences between two modes are the direction of throttle and pitch. Direction of throttle and pitch operate opposite way. They prefer mode 2 because mode 2 has similarities of manned flight control mode. Significance of this study is that it showed the necessity of standardization and flight control preference in a quantitative way. It will help drone standardization in related industries and development direction near future.

A Study on the Control Law Design and Analysis Process (비행제어법칙 설계 및 해석 절차에 관한 연구)

  • Hwang Byung-moon;Cho In-jae;Kim Chong-sup
    • Journal of Institute of Control, Robotics and Systems
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    • v.11 no.11
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    • pp.913-919
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    • 2005
  • An advanced method of Relaxed Static Stability (RSS) is utilized for improving the aerodynamic performance of modem version supersonic jet fighter aircraft. The flight control system utilizes RSS criteria in both longitudinal and lateral-directional axes to achieve performance enhancements and improve stability. Standard CLDA (Control Law Design and Analysis) process is provided that reduce the development period of the flight control system. In addition, if this process is employed in developing flight control laws, it reduces the trial and error development and verification of control laws. This paper details the design process of developing a flight control law for the RSS aircraft, utilizing military specifications, linear and nonlinea, analysis using XMATH and ATLAS(Aircraft, Tim Linear and Simulation), handling quality tests using the HQS (Handling Quality Simulator), and real flight test results to verify aircraft dynamic flight responses.

A study on the design of ALFLEX flight control system

  • Imado, Fumiaki;Yuasa, Eiji
    • 제어로봇시스템학회:학술대회논문집
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    • pp.219-222
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    • 1996
  • Authors ahve developed ALFLEX simulation program which can implement the flight simulation ad control system design of ALFLEX efficiently by using aerodynamic data provided by NAL/NASDA. Then we have designed and example of flight path and altitude control system of ALFLEX. The philosophy of the design method is explained in detail, and a flight simulation result is shown, which verifies the fine performance of the system.

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Development of a UAV Flight Control System Using a Low Cost GPS/IMU (저가형 GPS/IMU를 이용한 UAV 비행 제어 시스템 개발)

  • Koo, Won-Mo;Chun, Se-Bum;Won, Dae-Hee;Kang, Tae-Sam;Lee, Young-Jae;Sung, Sang-Kyung
    • Journal of Institute of Control, Robotics and Systems
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    • v.14 no.5
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    • pp.502-510
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    • 2008
  • UAVs(Unmanned Aerial Vehicles) have many applications in military and commercial areas. The flight control system of UAVs is more important than manned aircraft's because the mission of UAVs must be operated without a human pilot. But very heavy and expensive navigation system makes it difficult to develop UAV flight control system. In this research, GPS/IMU integrated navigation filter was developed for light weight/low cost flight control system of small UAVs. With this navigation filter, full flight control system which has real time operating capability has been developed. The performance of the flight control system is basically checked by HILSIM (Hardware In the Loop SIMulation). Finally, the flight control system is verified by showing performance test result under real flight environment.

A Study on the Parameter Estimation of DURUMI-II for the Fixed Right Elevator Using Flight Test Data

  • Park Wook-Je;Kim Eung-Tai;Seong Kie-Jeong;Kim Yeong-Cheol
    • Journal of Mechanical Science and Technology
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    • v.20 no.8
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    • pp.1224-1231
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    • 2006
  • The stability and control derivatives of DURUMI-lI UAV using the flight test are obtained. The flight test data is gathered from the normal flight condition (normal mode) and the flight condition assumed as the right elevator fixed (fault mode). Using real-time parameter estimation techniques, applied to Fourier transform regression method, simulates the aircraft motion. From the result, the fault of control surface is to be detected. In this paper, the results of the real- time parameter estimation techniques are compared with the results of the Advanced Aircraft Analysis (AAA). Using the aerodynamic derivatives, it provides the base line of normal/failure for the control surface by using the on-line parameter estimation of Fourier transform regression. In flight, this approach maybe helpful to detect and isolate the fault of primary control surface. It is explained how to perform the flight condition assumed as the right elevator fixed in the flight test. Also, it is mentioned how to switch between the normal flight condition and the assumed fault flight condition.