International Journal of Aeronautical and Space Sciences

The Korean Society for Aeronautical and Space Sciences (한국항공우주학회)
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Variable stability system control law development for in-flight simulation of pitch/roll/yaw rate and normal load

  • Ko, Joon Soo (School of Aerospace and Mechanical Engineering, Korea Aerospace University) ;
  • Park, Sungsu (Department of Aerospace Engineering, Sejong University)
  • Received : 2014.10.13
  • Accepted : 2014.12.17
  • Published : 2014.12.30
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Abstract

This paper describes the development of variable stability system (VSS) control laws for the KFA-i to simulate the dynamics of KFA-m aircraft. The KFA-i is a single engine, Class IV aircraft and was selected as an in-flight simulator (IFS) aircraft, whereas the KFA-m is a simulated aircraft that is based on the F-16 aircraft. A 6-DoF math model of KFA-i aircraft was developed, linearized, and separated into longitudinal and lateral motion for VSS control law synthesis. The KFA-i aircraft has five primary control surfaces: two flaperons, two all movable horizontal tails, and one rudder. Flaperons are used for load control, the horizontal tails are used for pitch and roll rate control, and the rudder is used for yaw rate control. The developed VSS control law can simulate four parameters of the KFA-m aircraft simultaneously, such as pitch, roll, yaw rates, and load. The simulation results show that KFA-i follows the responses of KFA-m with high accuracy.

Keywords

Acknowledgement

Grant : Helicopter Fly by Wire Flight Control System Development, according to ADS-33

Supported by : Ministry of Knowledge Economy(MKE)

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