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Operational Control Logic of Series Hybrid Power System for the Unmanned Aerial Vehicle

무인기용 직렬 하이브리드 동력시스템 운용 제어로직

  • Lee, Bohwa (Aeropropulsion Research Division, Korea Aerospace Research Institute) ;
  • Park, Poomin (Aeropropulsion Research Division, Korea Aerospace Research Institute) ;
  • Kim, Keunbae (Aeropropulsion Research Division, Korea Aerospace Research Institute)
  • Received : 2020.07.06
  • Accepted : 2020.11.15
  • Published : 2021.02.28

Abstract

The series hybrid system targeted in this study uses a reciprocating engine, a generator, and a battery as a main power source for the unmanned aerial vehicle. The generator is directly connected to the drive shaft of the reciprocating engine, and the operating characteristics of the reciprocating engine-generator set were confirmed through ground integration tests. In this study, based on the test results, a control logic is proposed an efficient use of the reciprocating engine-generator power and battery power. Also, the power variations of the reciprocating engine-generator and battery according to the logic were verified through simulation. As a result, it was confirmed that the engine-generator power supplied the power required for propulsion along with the battery power by the proposed control logic.

본 연구에서 대상으로 삼은 직렬 하이브리드 시스템은 무인기용으로 왕복엔진, 발전기, 배터리를 주 동력원으로 사용한다. 발전기는 왕복엔진의 구동축에 직결되며, 왕복엔진-발전기 세트의 운용 특성은 지상통합시험을 통해 확인하였다. 본 연구에서는 해당 시험 결과를 바탕으로 왕복엔진-발전기 출력과 배터리 출력을 효율적으로 사용하기 위한 제어로직을 제시하였고, 로직에 따른 왕복엔진-발전기와 배터리의 출력 변동은 시뮬레이션을 통해 확인하였다. 그 결과, 발전기 출력은 제시된 제어로직에 의해 배터리 출력과 함께 추진요구전력을 공급함을 확인하였다.

Keywords

Acknowledgement

본 논문은 한국항공우주연구원 주요사업의 일환으로 수행되는 "다중 전기추진 비행체 형상 및 체계설계연구"과제와 "유인 미래모빌리티 하이브리드 전기추진시스템 기술개발"과제의 지원을 받아 수행되었습니다.

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