Journal of Aerospace System Engineering (항공우주시스템공학회지)

The Society for Aerospace System Engineering (항공우주시스템공학회)
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Implementation of Fuel Quantity Measurement System for Aircraft Using Capacitive Fuel Sensor

정전용량형 연료센서를 이용한 항공기 연료량측정시스템 구현

  • Yang, Junmo (Korea Aerospace University Affiliated Aviation System Test and Certification Research Center) ;
  • Yang, Sungwook (Graduate School of Aerospace and Mechanical Engineering, Korea Aerospace University) ;
  • Lee, Sangchul (Department of Aerospace and Mechanical Engineering, Korea Aerospace University) ;
  • Yi, Yongsik (Korea Aerospace Industries, Ltd.)
  • 양준모 (한국항공대학교 부속 항공체계시험인증연구센터) ;
  • 양성욱 (한국항공대학교 대학원 항공우주 및 기계공학과) ;
  • 이상철 (한국항공대학교 항공우주 및 기계공학부) ;
  • 이용식 (한국항공우주산업(주))
  • Received : 2018.08.09
  • Accepted : 2018.11.17
  • Published : 2018.12.31
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Abstract

The amount of fuel, which affects aircraft endurance, needs to be measured accurately. This paper deals with the implementation of a fuel quantity measurement system that consists of capacitive fuel sensor, DAQ board, and Labview software. The main circuit of the implemented system for measuring fuel quantity is simulated with Pspice to identify parameters, which are related to the change of fuel quantity. After simulation, we established that Vrms changes with the variation of fuel amount. The Vrms, which is the output of fuel sensor, is transmitted to the Labview software via the DAQ board of the implemented fuel quantity measurement system. The fuel quantity is also calculated using this software. The present simulation results indicated that the accuracy of the implemented fuel quantity measurement system improved with the filter application.

항공기 항속시간에 영향을 미치는 요소인 연료량은 정확한 측정이 필요하다. 본 논문에서는 정전용량형 연료센서, DAQ 보드, Labview 소프트웨어로 구현된 연료량측정시스템을 다루었다. 연료량에 따라 변화하는 파라미터를 확인하기 위해 Pspice를 이용하여 구현된 시스템의 주회로가 시뮬레이션 되었다. 시뮬레이션을 통해 연료량에 따라 변화하는 파라미터인 Vrms를 찾아내었다. 연료 센서의 출력인 Vrms는 구현된 연료량측정시스템의 DAQ 보드를 통해 Labview 소프트웨어로 전송되고, 이 소프트웨어를 사용하여 연료량이 계산된다. 그 결과, 필터가 적용되지 않은 연료량측정시스템보다 정확도가 향상되었다.

Keywords

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Fig. 1 Concept of Capacitive Fuel Sensor

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Fig. 2 US4289028 PRIOR ART

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Fig. 3 High Accuracy Fuel Sensor

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Fig. 4 Pspice Simulation Model

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Fig. 5 Capacitor(C3) 102 pF Result

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Fig. 6 Capacitor(C3) 112 pF Result

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Fig. 7 Capacitor(C3) 120 pF Result

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Fig. 8 Implementation of Fuel Quantity Measurement System

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Fig. 9 Block Diagram of Fuel Quantity Measurement System

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Fig. 10 Fuel Quantity Measurement System GUI

Table 1 Configuration and Signal of P-300C

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Table 2 Input Signal Electrical Requirement

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Table 3 Output Signal Electrical Characteristics

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Table 4 Component of Fuel Quantity Measurement System

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Table 5 Test Result in Case of 4 L

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Table 6 Test Result in Case of 7 L

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References

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