Journal of Aerospace System Engineering (항공우주시스템공학회지)

The Society for Aerospace System Engineering (항공우주시스템공학회)
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Optimization and Evaluation of Flight Control Laws to Satisfy Longitudinal Handling Quality and Stability Margin Requirements

종축 비행성 요구도 및 안정성 여유 만족을 위한 비행제어법칙 최적화 및 평가

  • Kim, Seong Hyeon (School of Mechanical and Aerospace Engineering, Gyeoungsang National University) ;
  • Ko, Deuk Won (School of Mechanical and Aerospace Engineering, Gyeoungsang National University) ;
  • Lee, Tae Hyun (School of Mechanical and Aerospace Engineering, Gyeoungsang National University) ;
  • Kim, Dong Hwan (Flight Control Law Team, Korea Aerospace Industries) ;
  • Kim, Byoung Soo (School of Mechanical and Aerospace Engineering, Gyeoungsang National University)
  • 김성현 (경상대학교 기계항공공학부) ;
  • 고득원 (경상대학교 기계항공공학부) ;
  • 이태현 (경상대학교 기계항공공학부) ;
  • 김동환 (한국항공우주산업 비행제어법칙팀) ;
  • 김병수 (경상대학교 기계항공공학부)
  • Received : 2020.12.23
  • Accepted : 2021.05.05
  • Published : 2021.10.31
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Abstract

This paper describes a design method using an optimization technique to satisfy the longitudinal handling quality of high maneuverable jet aircraft. The dynamic inversion technique was applied to the target aircraft, and the control gain optimization satisfied the longitudinal short-period handling quality, however, the stability margin was not considered. If the stability margin is not satisfied, it is necessary to directly readjust the gains through trial and error methods for improvement. To improve this, an additional compensator and an optimization constraint were added to the control gain optimization procedure. In addition, the degree of handling quality satisfaction with the optimization result was reevaluated, and additional control evaluation criteria for the convergence of the time response and the steady state error that the flight performance requirement set as the optimization constraint cannot be reflected, and the results are described.

본 논문은 고기동 제트항공기의 종축 비행성 요구도를 만족하기 위해 최적화 기법을 이용한 설계 방법에 관해 기술한다. 대상 항공기는 모델 역변환 기법이 적용되었으며, 제어이득 최적화로 종축 단주기 비행성 요구도를 만족하지만, 안정성 여유 항목이 고려되지 않았다. 안정성 여유를 만족하지 못하는 경우 개선을 위해 시행 착오법 등을 통한 이득의 직접 재조정이 필요하며, 이를 개선하기 위해 추가적인 보상기와 최적화 구속조건을 추가한 제어이득 최적화 방안을 제시하였다. 또한, 최적화 결과에 대한 비행성 만족도를 재평가하였으며, 최적화 구속조건으로 설정된 비행성 요구도가 반영하지 못하는 시간 반응의 수렴성과 정상상태 오차에 대한 추가적인 제어법칙 평가 기준 설정 및 그 결과에 관해 기술한다.

Keywords

Acknowledgement

이 연구는 2020년도 경상대학교 연구년제연구교수 연구지원비에 의하여 수행되었음

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