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Method for load distribution of connection hinge joints of fuselage and empennages based on load of vertical empennage

A distribution method and a technology for connecting hinges, which are applied in computer-aided design, special data processing applications, instruments, etc., to achieve good consistency and avoid omissions

Active Publication Date: 2017-11-10
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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Problems solved by technology

[0003] The purpose of the present invention is to provide a kind of load distribution method based on the vertical tail load at the connecting hinge point of the fuselage and the empennage, to solve or at least alleviate at least one problem in the background technology

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  • Method for load distribution of connection hinge joints of fuselage and empennages based on load of vertical empennage
  • Method for load distribution of connection hinge joints of fuselage and empennages based on load of vertical empennage
  • Method for load distribution of connection hinge joints of fuselage and empennages based on load of vertical empennage

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[0026] 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 method for load distribution of connection hinge joints of a fuselage and empennages based on load of a vertical empennage and relates to the technical field of aircraft structural strength design. The method for the load distribution of the connection hinge joints of the fuselage and the empennages based on the load of the vertical empennage comprises the following steps of step 1.creating a mathematical calculation model based on the load of the vertical empennage of the empennages according to the force transfer characteristics of a connection area of the back fuselage and the tail empennage of an aircraft; and step 2.computing a theory resolution of the load distribution of the connection hinge joints of the connection area of the tail empennage according to the model established in the step 1 and determining the relationship among a lateral distance between the connection joints and a symmetry plane of the aircraft, overall stiffness of the connection hinge joints and a vertical load value of the connection points. The method has the advantages that through application of a mathematical modeling method and creation of the mathematic model and an equation, the key factors for affecting the load distribution of the connection hinge joints of the connection area are explored, the algebraic relation between the factors is proposed, and meanwhile, the theory resolution and an optimal solution of the load distribution of the hinge joints of the connection area are quickly and effectively determined.

Description

technical field [0001] The invention relates to the technical field of aircraft structural strength design, in particular to a method for distributing loads at hinge points connecting fuselage and empennage based on vertical tail loads. Background technique [0002] At present, large-scale transport aircraft at home and abroad mostly adopt a high-level tail and swept-wing layout to improve the control efficiency of the rudder surface; since the center of pressure of the horizontal tail and the vertical tail of this layout are relatively behind, the concentrated load transmitted from the tail to the fuselage Relatively high, forming a complex connection area of ​​the so-called "large load, multiple joints, super statically indeterminate" system. The structure of the complex connection area is seriously stressed and the force transmission is complicated. The unsatisfactory load distribution of the hinge points in the connection area will directly affect the key links of flight...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/17G06F30/23G06F2119/06
Inventor 张洪智田晶晶惠红军张育宏
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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