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논문 기본 정보

자료유형
학술저널
저자정보
Joon Soo Ko (Korea Aerospace University) Sungsu Park (Sejong University)
저널정보
한국항공우주학회 International Journal of Aeronautical and Space Sciences International Journal of Aeronautical and Space Sciences Volume.15 Number.4
발행연도
2014.12
수록면
412 - 418 (7page)

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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.

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Abstract
1. Introduction
2. Design of Model-following Control
3. Simulation Results
4. Conclusions
References

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UCI(KEPA) : I410-ECN-0101-2016-558-000990441