• Title, Summary, Keyword: flight control

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The Effect of an Installation Angle of IMFP sensors on Estimation of Altitude of T-50 Aircraft in the Transonic Region (IMFP 장착각도가 T-50 초음속 고도정보에 미치는 영향)

  • Nam, Yong-seog;Kim, Yeon-hi;Song, Seok-bong;Kim, Seong-jun
    • Journal of Aerospace System Engineering
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    • v.3 no.1
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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.

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무인항공기의 각속도 기반 자동비행제어시스템 개발

  • Lee, Jang-Ho;Ryu, Hyeok;Kim, Jae-Eun;Ahn, Iee-Gi;Kim, Eung-Tai
    • Aerospace Engineering and Technology
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    • v.4 no.2
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    • pp.7-14
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    • 2005
  • This paper describes development of automatic flight control system for an unmanned target drone. Current target drone is operated by pilot control of on-board servo motor via remote control system. Automatic flight control system for the target drone greatly reduces work load of ground pilot and can increase application area of the drone. Most UAVs being operated nowdays use high-priced sensors as AHRS and IMU to measure the attitude, but those are costly. This paper introduces the development of low-cost automatic flight control system with low-cost sensors. The integrated automatic flight control system has been developed. The performance of automatic flight control system is verified by flight test.

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Implementation and Test of the Automatic Flight Dynamics Operations for Geostationary Satellite Mission

  • Park, Sang-Wook;Lee, Young-Ran;Lee, Byoung-Sun;Hwang, Yoo-La;Galilea, Javier Santiago Noguero
    • Journal of Astronomy and Space Sciences
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    • v.26 no.4
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    • pp.635-642
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    • 2009
  • This paper describes the Flight Dynamics Automation (FDA) system for COMS Flight Dynamics System (FDS) and its test result in terms of the performance of the automation jobs. FDA controls the flight dynamics functions such as orbit determination, orbit prediction, event prediction, and fuel accounting. The designed FDA is independent from the specific characteristics which are defined by spacecraft manufacturer or specific satellite missions. Therefore, FDA could easily links its autonomous job control functions to any satellite mission control system with some interface modification. By adding autonomous system along with flight dynamics system, it decreases the operator's tedious and repeated jobs but increase the usability and reliability of the system. Therefore, FDA is used to improve the completeness of whole mission control system's quality. The FDA is applied to the real flight dynamics system of a geostationary satellite, COMS and the experimental test is performed. The experimental result shows the stability and reliability of the mission control operations through the automatic job control.

Development of Low-Cost Automatic Flight Control System for an Unmanned Target Drone (무인표적기용 저가형 자동비행시스템 개발)

  • Lee, Jang-Ho;Ryu, Hyeok;Kim, Jae-Eun;Ahn, Iee-Ki
    • The 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.

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A Study on Longitudinal Phugoid Mode Affected by Application of Nonlinear Control Laws

  • Kim, Chong-Sup;Hur, Gi-Bong;Kim, Seung-Jun
    • International Journal of Aeronautical and Space Sciences
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    • v.8 no.1
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    • pp.21-31
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    • 2007
  • Relaxed Static Stability (RSS) concept has been applied to improve aerodynamic performance of modern version supersonic jet fighter aircraft. The T-50 advanced supersonic trainer employs the RSS concept in order to improve the aerodynamic performance. And the flight control system stabilizes the unstable aircraft and provides adequate handling qualities. The T-50 longitudinal control laws employ a proportional-plus-integral type controller based on a dynamic inversion method. The longitudinal dynamic modes consist of short period with high frequency and phugoid mode with low frequency. The design goal of longitudinal control law is optimization of short period damping ratio and frequency using Lower Order Equivalent System (LOES) complying the requirement of MIL-F-8785C. This paper addresses phugoid mode characteristics such as damping ratio and natural frequency that is affected by the nonlinear control laws such as angle of attack limiter, auto pitch attitude command system and autopilot of pitch attitude hold.

Study of Flight Simulation using Real-Time Aerodynamic Model (실시간 공력모델을 이용한 비행 시뮬레이션 연구)

  • Lee, Chang Ho;Park, Young Min;Choi, Hyoung Sik
    • Journal of Aerospace System Engineering
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    • v.9 no.4
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    • pp.49-54
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    • 2015
  • Accurate aerodynamic data is required for the flight simulation or control logic design of aircraft. The aerodynamic look-up table has been used widely to provide aerodynamic forces and moments for given flight conditions. In this paper, we replace the aerodynamic look-up table with real-time aerodynamic model which calculates aerodynamic forces and moments of quasi-steady flow directly for given flight conditions and control surface deflections. Flight simulations are conducted for the low-speed small UAV using real-time aerodynamic model, and responses of the UAV are predicted successfully for inputs of control surfaces.

Robust $\mu$-Controller design for Control Loading System of Flight Simulator (항공기 시뮬레이터 조종력 제어시스템의 견실 $\mu$-제어기 설계)

  • 방경호
    • Proceedings of the IEEK Conference
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    • pp.405-408
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    • 1998
  • Generally, the principle function of simulator control loading system is to provide the pilot or student with the "feel" of the actual aircraft flight control systems during flight, taxing, and in malfunction. Flight control "feel" is the resistance felt by the pilot when moving a control stick or pedal, coupled with the amount of control surface deflection, and hence aircraft response, resulting from the input. Therefore, the control loading servo must be capable of performing to some general list of requirements derived from real aircraft control forces. In this paper, we deal with a $\mu-controller$ design for a control loading system of the flight simulator. For this, we derive a frequency response of the hydraulic system from the identification data and then design a controller using a $\mu-synthesis$ method. Under the same condition of simulation, $\mu-controller$ provides the superior performance than PID controller.than PID controller.

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A Study on the Longitudinal Flight Control Law of T-50 (T-50 세로축 비행제어법칙 설계에 관한 연구)

  • Hwang Byung-moon;Kim Seong-Jun;Kim Chong-sup
    • Journal of Institute of Control, Robotics and Systems
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    • v.11 no.11
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    • pp.963-969
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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. The T-50 advanced trainer employs the RSS concept in order to improve the aerodynamic performance and the flight control law in order to guarantee aircraft stability, The T-50 longitudinal control laws employ the dynamic inversion and proportional-plus-integral control method. This paper details the design process of developing longitudinal control laws for the RSS aircraft, utilizing the requirement of MIL-F-8785C. In addition, This paper addresses the analysis of aircraft characteristics such as damping, natural frequency, gain and phase margin about state variables for longitudinal inner loop feedback design.

A Flight Control System design for an Unmanned Helicopter

  • Park, Soo-Hong;Kim, Jong-Kwon;Jang, Cheol-Soon
    • 제어로봇시스템학회:학술대회논문집
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    • pp.1375-1379
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    • 2004
  • Unmanned Helicopter has several abilities such as vertical Take off, hovering, low speed flight at low altitude. Such vehicles are becoming popular in actual applications such as search and rescue, aerial reconnaissance and surveillance. These vehicles also used under risky environments without threatening the life of a pilot. Since a small aerial vehicle is very sensitive to environmental conditions, it is generally known that the flight control is very difficult problems. In this paper, a flight control system was designed for an unmanned helicopter. This paper was concentrated on describing the mechanical design, electronic equipments and their interconnections for acquiring autonomous flight. The design methodologies and performance of the helicopter were illustrated and verified with a linearized equation of motion. The LQG based estimator and controller was designed and tested for this unmanned helicopter.

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Development of Operation Network System and Processor in the Loop Simulation for Swarm Flight of Small UAVs (소형 무인기들의 군집비행을 위한 운영 네트워크 시스템과 PILS 개발)

  • Kim, Sung-Hwan;Cho, Sang-Ook;Cho, Seong-Beom;Park, Choon-Bae
    • Journal of Institute of Control, Robotics and Systems
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    • v.18 no.5
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    • pp.433-438
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    • 2012
  • In this paper, a operation network system equipped with onboard wireless communication systems and ground-based mission control systems is proposed for swarm flight of small UAVs. This operating system can be divided into two networks, UAV communication network and ground control system. The UAV communication network is intend to exchange the informations of navigation, mission and flight status with minimum time delay. The ground control system consisted of mission control systems and UDP network. Proposed operation network system can make a swarm flight of various UAVs, execute complex missions decentralizing mission to several UAVs and cooperte several missions. Finally, PILS environments are developed based on the total operating system.