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Research on Calculation Method of Fuel Temperature According to Airworthiness Regulations

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Abstract

How to establish a general fuel tank thermodynamic model that meets the requirements of airworthiness certification and how to obtain the equilibrium temperature difference △T and time constant τ in the Monte Carlo evaluation model after obtaining the fuel temperature change law within specific flight envelope are the bottleneck issues need to be solved urgently in the airworthiness certification process of fuel tank flammability. This paper builds the fuel temperature simulation calculation model on the MATLAB/Simulink software platform to obtain the fuel temperature change law and obtains the high-order functional expression of the fuel temperature change law in each stage by means of MATLAB polynomial piecewise fitting function. The exponential attenuation equation stipulated in the Monte Carlo evaluation model is used to characterize the change law of fuel temperature. Among which the total ambient temperature (TAT) is obtained by the method specified in the evaluation model, and the equilibrium temperature difference and time constant are obtained by the improved genetic algorithm. The equilibrium temperature difference and time constant obtained by the inversion are input into Monte Carlo model for calculation, the calculated temperature data and the actual measured flight data are compared to verify the reliability of the method.

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Abbreviations

τ :

Time constant

△ T :

Equilibrium temperature difference

T F :

Temperatures of the front nodes

T B :

Temperatures of the back nodes

T U :

Temperatures of the up nodes

T D :

Temperatures of the down nodes

T L :

Temperatures of the left nodes

T R :

Temperatures of the right nodes

R F :

Corresponding thermal resistances of TF

R B :

Corresponding thermal resistances of TB

R U :

Corresponding thermal resistances of TU

R D :

Corresponding thermal resistances of TD

R L :

Corresponding thermal resistances of TL

R R :

Corresponding thermal resistances of TR

h :

Convection heat transfer coefficient

A :

Heat transfer area

C :

Constant

Gr:

Grashchev number

Pr:

Prandtl number

n :

Exponential

P i :

The probability of each control parameter

f i :

The fitness of individual i

J :

Fitness function

T i, real :

Fuel temperature at each time step in the flight measured data

T i :

The fuel temperature calculated by the exponential attenuation equation

TAT :

Total environmental temperature

T amb :

Atmospheric ambient temperature

T grd :

Temperature of ground atmosphere

Ma :

Flight Mach number

H :

Flight altitude

T crz :

Atmospheric temperature at the cruising altitude

Ma crz :

Mach number of cruise altitude

References

  1. Evosevoch BJ, Jojic I (2018) CA US Patent Application for a “Aircraft fuel tank flammability reduction method and system”, Docket No. P-10–0294, filed 19 Jun 2018s

  2. Michael B, William MC (2001) Inerting of a Vented Air craft Fuel Tank Test Article With Nitrogen-Enriched Air. DOT/FAA/AR-01/6

  3. Langton R, Clark C, Hewitt M (2010) Aircraft fuel system. John Wiley & Sons, New York, pp 225–237

    Google Scholar 

  4. Martinov NP (2002) CA US Patent Application for a Aircraft fuel tank explosion reduction safety method, Docket No. P-343–465, filed 5 Feb. 2002

  5. Jojic I, Snow DR, Grim A (2016) Patent Application for a Aircraft fuel tank flammability reduction methods and systems,” Docket No. P-9–0327, filed 3 May. 2016

  6. FAA (2008) Fuel Tank Flammability Reduction Means, Advisory Circular No.25.981–2A, 2008

  7. Paul MD, Surawski E CA U.S. Patent Application for a “Temperature control system for fuel tank inerting system,” Docket No. P-15–0208, filed 18 Jan

  8. Yang S, Tang WQ (2006) Heat transfer, 4th ed., Education press, 2006, 398–399

  9. Pasion AJ (1979) Inflight fuel tank temperature survey data

  10. Lawson JC (1997) CA, U.S. Patent Application for a “Method for collecting liquid temperature data from a fuel tank,” Docket No. P-5–0613, filed 25 Mar 1997

  11. Kang ZY, Liu ZX, Ren GZ (2014) Simulation and Calculation of Fuel Temperature in Aircraft Fuel Tank Based on MATLAB/Simulink. Journal of Propulsion Technology 1:10

    Google Scholar 

  12. Zhang XJ, Zhang ZQ, Gao F (2010) Fuel temperature analysis of advanced fighter aircraft during supersonic cruise. J Aerosp Power 2

  13. Wang R, Dong SJ, Meng FC (2018) A shortcut method for solving long-term thermal dynamic analysis of aircraft fuel tank by thermal node network analysis and OpenFOAM software. Adv Mech Eng 10(11)

  14. German BJ (2012) Tank heating modeling for aircraft fuel thermal systems with recirculation. J Propul Power 28(1):204–210

    Article  Google Scholar 

  15. Wang R, Dong S, Meng F (2018) A shortcut method for solving long-term thermal dynamic analysis of aircraft fuel tank by thermal node network analysis and OpenFOAM software. Adv Mech Eng 10(11)

  16. Maulik U, Bandyopadhyay S (2000) Genetic algorithm-based clustering technique. Pattern Recogn 33(9):1455–1465

    Article  Google Scholar 

  17. Sivaram M, Batri K, Mohammed AS (2019) Exploiting the local optima in genetic algorithm using Tabu search. Indian J Sci Technol 12(1):9

    Article  Google Scholar 

  18. Armaghani DJ, Hasanipanah M, Mahdiyar A (2018) Airblast prediction through a hybrid genetic algorithm-ANN model. Neural Comput Appl 29(9):619–629

    Article  Google Scholar 

  19. Chatterjee S, Sarkar S, Dey N (2018) Hybrid non-dominated sorting genetic algorithm: II-neural network approach, Advancements in Applied Metaheuristic Computing. IGI Global 264–286s

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Funding

National Natural Science Foundation of China U1933121.

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Authors and Affiliations

  1. Key Laboratory of Aircraft Environmental Control and Life Support, Nanjing University of Aeronautics and Astronautics, Nanjing, 210016, Jiangsu, China

    Ruihua Zhang & Weihua Liu

Authors
  1. Ruihua Zhang
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  2. Weihua Liu
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Correspondence to Ruihua Zhang.

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Zhang, R., Liu, W. Research on Calculation Method of Fuel Temperature According to Airworthiness Regulations. Int. J. Aeronaut. Space Sci. 22, 1504–1511 (2021). https://doi.org/10.1007/s42405-021-00400-z

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  • DOI: https://doi.org/10.1007/s42405-021-00400-z

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