항공우주시스템공학회지 (Journal of Aerospace System Engineering)

  • 제12권4호
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  • Pages.49-56
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  • 2018
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  • 1976-6300(pISSN)
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  • 2508-7150(eISSN)
항공우주시스템공학회 (The Society for Aerospace System Engineering)
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소형 압전유압펌프 브레이크 시스템의 성능해석 및 실험

Performance Analysis and Test of the Small Piezoelectric-Hydraulic Pump Brake System

  • 황용하 (한국항공대학교 항공우주 및 기계공학과 대학원) ;
  • 황재혁 (한국항공대학교 항공우주 및 기계공학부) ;
  • 응위웬 안 푹 (한국항공대학교 항공우주 및 기계공학과 대학원) ;
  • 배재성 (한국항공대학교 항공우주 및 기계공학부)
  • Hwang, Yong-Ha (Department of Aerospace and Mechanical Engineering, Graduate school at KAU) ;
  • Hwang, Jai-Hyuk (Department of Aerospace and Mechanical Engineering, Korea Aerospace University) ;
  • Nguyen, Anh Phuc (Department of Aerospace and Mechanical Engineering, Graduate school at KAU) ;
  • Bae, Jae-Sung (Department of Aerospace and Mechanical Engineering, Korea Aerospace University)
  • 투고 : 2018.05.16
  • 심사 : 2018.07.14
  • 발행 : 2018.08.31
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초록

본 논문에서는 소형 압전유압펌프 브레이크 시스템의 성능해석 및 실험을 수행하였다. 먼저 브레이크 시스템의 구성을 위해 브레이크 부하 구성품의 3-D 모델링을 수행하였고, 상용 프로그램인 AMESim을 이용한 모델링을 진행하였다. 브레이크 시스템 모델링에는 플로팅 타입의 캘리퍼를 부하로 활용하였다. AMESim 시뮬레이션을 통해, 부하 압력과 체크밸브 변위 및 무부하 상태에서의 유량을 계산하였으며 브레이크 부하의 추가에 따른 성능해석 및 동특성 변화를 확인하였다. 브레이크 시스템의 성능 실험을 위해 부하를 고정시키는 치구를 제작하였고, 무부하 상태에서의 유량 및 부하 압력 형성 실험을 수행하고 시뮬레이션 결과와 비교하였다. 실험 결과, 최대 부하압력은 130Hz에서 약 73bar, 최대 유량 발생은 145Hz에서 약 203cc/min로, 중소형 무인기 브레이크 시스템에 적용가능성을 확인하였다. 또한 시뮬레이션 결과와 실험결과의 오차는 부하 압력과 토출 유량에서 각각 6%, 5% 정도이며, 모델링이 브레이크 성능해석에 효과적으로 활용될 것으로 판단된다.

In this paper, the performance analysis and the experiment of the brake system using the small piezoelectric-hydraulic pump were performed. Initially, the 3-D modeling of the brake load components was performed for the construction of the brake system. Subsequently, modeling using the commercial program AMESim was performed. A floating caliper model was used as a load for modeling the brake system. Through the AMESim simulation, load pressure, check valve displacement and flow rate under no load state were calculated, and performance analysis and changes in dynamic characteristics were confirmed by adding brake load. A jig for use in fixing the brake load during performance test was manufactured. The flow rate was assessed under no load condition and load pressure formation experiments were performed and compared with simulation results. Experimental results revealed the maximum load pressure as about 73bar at 130Hz and the maximum flow rate as about 203cc/min at 145Hz, which satisfied the requirement of small- and medium-sized UAV braking system. In addition, simulation results revealed that the load pressure and discharge flow rate were within 6% and 5%, respectively. Apparently, the modeling is expected to be effective for brake performance analysis.

키워드

참고문헌

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