Design method for airplane fuel system

A fuel system and design method technology, applied in the field of aircraft, can solve the problems of inability to simulate the air environment and large influencing factors, and achieve the effect of strong versatility and high precision

Active Publication Date: 2017-02-22
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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Problems solved by technology

[0003] However, the fuel temperature of the aircraft fuel system is greatly affected by factors such as flight profile, environmental conditions, fuel load, fuel tank layout, fuel supply and delivery rules, and radiators. Ground fuel thermal performance tests cannot simulate the air environment. How to accurately a

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  • Design method for airplane fuel system
  • Design method for airplane fuel system
  • Design method for airplane fuel system

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Embodiment Construction

[0052] In order to make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below in conjunction with the drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the invention. The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below ...

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Abstract

The invention discloses a design method for an airplane fuel system. The design method for the airplane fuel system comprises the following steps of 1: building fuel flow models of fuel tanks of an airplane; 2: performing discretized iterative processing on fuel quality of fuel tank compartments and change of temperature along with typical flight profiles of cold and hot extremes of the airplane; 3: calculating change of average temperature of the fuel tank compartments along with the typical flight profiles of the cold and hot extremes of the airplane; 4: determining temperature field distribution of a fuel collection tank; 5: determining fuel mass flow in a fuel supply guide pipe and change of temperature of an environment, in which the fuel supply guide pipe is located, along with the typical flight profiles of the cold and hot extremes of the airplane; 6: calculating change of temperature from the fuel collection tank to an engine inlet along with the flight profiles; and 7: judging whether fuel entering the engine inlet meets a requirement of entering the engine inlet by the fuel or not. According to the design method for the airplane fuel system, the problem of low calculation precision in a conventional method is solved.

Description

technical field [0001] The invention relates to the technical field of aircraft, in particular to an aircraft fuel system design method. Background technique [0002] With the continuous advancement of aircraft design technology, the complexity of aircraft design is getting higher and higher, and the airborne heat load is also increasing. With high requirements, it has become a development trend to use fuel oil as a refrigerant to dissipate heat for other systems. [0003] However, the fuel temperature of the aircraft fuel system is greatly affected by factors such as flight profile, environmental conditions, fuel load, fuel tank layout, fuel supply and delivery rules, and radiators. Ground fuel thermal performance tests cannot simulate the air environment. How to accurately analyze and calculate fuel The thermal performance of the system, whether it can meet the engine inlet temperature requirements under all operating conditions and flight profiles, reduce engineering dev...

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/20
Inventor 李小刚刘苏彦林厚焰任恒英
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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