한국항공우주학회지 (Journal of the Korean Society for Aeronautical & Space Sciences)

  • 제32권5호
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  • Pages.58-64
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  • 2004
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  • 1225-1348(pISSN)
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  • 2287-6871(eISSN)
한국항공우주학회 (The Korean Society for Aeronautical and Space Sciences)
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양시등급 항공기 동력학의 근사 궤환 제어기 설계

Design of Approximate Feedback Controller for Two-Time-Scale Aircraft Dynamics

  • 심규홍 (세종대학교 세종-록히드마틴우주항공연구소) ;
  • 사완 (미국 캔자스 위치타주립대 전기 및 컴퓨터공학과) ;
  • 홍성경 (세종대학교 항공우주공학과)
  • 발행 : 2004.06.01
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⟨ 이전 논문 다음 논문 ⟩

초록

본 논문에서는 양시등급 항공기 동력학에서 빠른 종속시스템의 극점들을 그대로 둔 채 느린 종속시스템의 극점만을 재배치함으로써 페루프의 근사치 해를 획득하는 방법이 제안되었다. 행렬대각화를 통하여 얻어지는 이러한 근사치 해는 수정된 것과 수정되지 않은 것 두 종류로 구분된다. 이들의 차이는 전자의 경우 오차가 $O({\varepsilon})$이며 후자의 경우는 오차가 $O({\varepsilon}^2)$이다. 두 가지 해는 모두 감소해이지만 충분한 견실성을 보여준다. 제안된 기법의 우수성은 항공기 종방향 운동 모델의 시뮬레이션을 통하여 확인되었다.

A new method to obtain approximate solutions by placing the only poles of the slow subsystem for the two-time-scale aircraft dynamic systems. The two kinds of approximate solutions are obtained by a matrix block diagonalization. One is called the uncorrected solution, and the other is called the corrected solution. The former has an error of $O({\varepsilon})$, and the latter has an error of $O({\varepsilon}^2)$. Of course, both solutions are robust enough even though they are reduced solutions. The excellence of the proposed method is illustrated by an numerical example of an aircraft longitudinal dynamics.

키워드

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