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Volume 41 Issue 11
Nov.  2015
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Journal of Beijing University of Aeronautics and Astronautics  > 2015  >  41(11): 2036-2043.
YUAN Mei, HE Yiqiang, DONG Shaopeng, et al. Aircraft fuel measurement sensor optimal layout technology[J]. Journal of Beijing University of Aeronautics and Astronautics, 2015, 41(11): 2036-2043. doi: 10.13700/j.bh.1001-5965.2014.0745(in Chinese)
Citation: YUAN Mei, HE Yiqiang, DONG Shaopeng, et al. Aircraft fuel measurement sensor optimal layout technology[J]. Journal of Beijing University of Aeronautics and Astronautics, 2015, 41(11): 2036-2043. doi: 10.13700/j.bh.1001-5965.2014.0745(in Chinese)
shu

Aircraft fuel measurement sensor optimal layout technology

doi: 10.13700/j.bh.1001-5965.2014.0745
  • 1.

    School of Automation Science and Electrical Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

  • 2. Collaborative Innovation Center for Advanced Aero-Engine, Beijing 100191, China

  • 3. Aviation Science and Technology National Laboratory, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

  • Received Date: 01 Dec 2014
  • Rev Recd Date: 26 Dec 2014
  • Publish Date: 20 Nov 2015
    Abstract
  • It is very important for aircraft flight safety to accurately measure the remaining fuel in each fuel tank in real time. An aircraft fuel measurement sensor optimal layout method based on particle swarm optimization (PSO) was designed to improve aircraft fuel measurement accuracy. Firstly, the concept of the fuel entity was proposed, and two models were built including the complex wing fuel tank CAD model which had multi-chamber with inner clapboards and the fuel entity model in fuel tank. Secondly, the total fuel volumes of complex and irregular multi-chamber tanks were calculated at different aircraft attitudes based on the second development of Unigraphics NX (UG). Thirdly, the concept of the largest measurement range (LMR) of the aircraft fuel tanks was put forward, which was used as the goal to optimize the sensor layout. Finally, the boundary distance factor (BDF) was introduced to avoid settling the sensor too close to the fuel tank wall. The results show that the method can optimize the layout of several fuel sensors without being limited by the shape and size of the fuel tank, which can effectively avoid interference in the internal area of the tank, ensure fuel measurement continuity at different aircraft attitudes, and make the aircraft fuel measurable range reach a higher level.

     

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