Method for calculating load of wing integral fuel tank

An integral fuel tank, load calculation technology, applied in the direction of calculation, special data processing applications, instruments, etc., can solve the problems of complex inertial load and no load calculation, etc.

Active Publication Date: 2015-12-30
JIANGXI HONGDU AVIATION IND GRP
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Problems solved by technology

[0002] The aircraft is maneuvering in the air, and the inertial load of the fuel in the wing fuel tank to the fuel tank is very complicated. For the integral fuel tank of the wing with pressure, the national mil

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  • Method for calculating load of wing integral fuel tank
  • Method for calculating load of wing integral fuel tank
  • Method for calculating load of wing integral fuel tank

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Embodiment Construction

[0021] The present invention will be further described below in conjunction with the accompanying drawings and specific embodiments. The following examples are only used to illustrate the present invention, and are not intended to limit the protection scope of the present invention.

[0022] A kind of wing integral fuel tank load calculation method of the present invention, it comprises the following steps:

[0023] According to the flight parameters of each load condition when the overall fuel tank of the aircraft wing is full of fuel, the more serious conditions are selected in combination with the stress of the aircraft wing, and then the fuel tank load is calculated. When calculating the fuel tank load, the comprehensive effect of fuel inertial loads in all directions (the center of gravity overload, the inertial force generated by angular acceleration and the centrifugal force generated by angular velocity) is considered, that is, the inertial loads in each direction are ...

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Abstract

The invention discloses a method for calculating a load of a wing integral fuel tank. The method comprises the steps of first calculating loads which fuel is subjected to in the X-direction, Y-direction and Z-direction by utilizing the principle that the loads can be overlaid linearly in the structure on-line elastic range; respectively calculating pressure distribution of each end face of the inner wall of the fuel tank under unidirectional overloads; finally overlaying pressure generated by each unidirectional overload, and obtaining pressure distribution of the wing fuel tank; establishing a wing fuel tank local detail finite element model in a full-aircraft overall finite element model, adding the pressure load of each end face of the fuel tank to the finite element model, applying corresponding working condition aerodynamic loads, and performing finite element stress analysis to obtain finite element stress result under each working condition. Under the conditions that the aircraft wing integral fuel tank is not pressurized and an inertial load of the fuel to the fuel tank exists, the method for calculating the load of the fuel tank is used for intensity assessment, and the load which the fuel tank is subjected to can be reflected genuinely.

Description

technical field [0001] The invention relates to a method for calculating the load of an integral fuel tank of a wing. Background technique [0002] The aircraft maneuvers in the air, and the inertial load of the fuel in the wing fuel tank on the fuel tank is very complicated. For the integral fuel tank of the wing with pressure, the national military standard has regulations on the load calculation. For the integral fuel tank of the wing without pressure, There is only the inertial load of fuel to the fuel tank, and there is no provision for load calculation at present. [0003] Therefore, it is necessary to provide a new technical solution to solve the above problems. Contents of the invention [0004] The present invention needs to provide a load calculation method for the integral fuel tank of the wing under the condition that the integral fuel tank of the aircraft wing is not pressurized and only has the inertial load of the fuel on the fuel tank, which is used for st...

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Application Information

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IPC IPC(8): G06F17/50
Inventor 王震李朝光杜龙王红飞杜兴刚姜亚娟徐丹王学强吕万韬朱翔黄亚超胡博海余凌晶秦利军唐姗
Owner JIANGXI HONGDU AVIATION IND GRP
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