General plane fuselage axis type load processing method

An aircraft fuselage and processing method technology, which is applied in electrical digital data processing, special data processing applications, computer-aided design, etc., can solve problems such as large workload and complex calculation, and achieves improved work efficiency, reduced time and workload. , the effect of improving the accuracy of load calculation

Active Publication Date: 2016-10-12
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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Problems solved by technology

In the past, it was usually necessary to establish a beam element model with the given aerodynamic load points and each frame station point as nodes through Patran, constrain the node displacement at each frame station point, apply loads at each aerodynamic load point, and obtain each constraint The constraint reaction force of each fr

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  • General plane fuselage axis type load processing method
  • General plane fuselage axis type load processing method
  • General plane fuselage axis type load processing method

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[0016] 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 with reference to the accompanying drawings in the embodiments of the present invention. Throughout the drawings, the same or similar reference numbers refer to the same or similar elements or elements having the same or similar functions. The described embodiments are some, but not all, of the embodiments of the present invention. The embodiments described below with reference to the accompanying drawings 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 those of ordinary skill in the art without creative work fall within the protection scope of the present invention. The embodiments of the present inv...

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Abstract

The invention relates to a general plane fuselage axis type load processing method. The method includes the steps that 1, an axis type load curve schematic diagram is drawn according to a load curve and a plane fuselage axis and is divided into multiple preset graphs according to a preset rule, and centroid coordinates of each preset graph are calculated; 2, the areas of the preset graphs formed in the step 1 are calculated, wherein the areas of the preset graphs are load values of centroid points of the preset graphs; 3, the load values of the centroid points of the multiple preset graphs are distributed to all frame stations, and the load values of all the frame stations are overlaid, wherein the frame stations are projection points, on the fuselage axis, of a fuselage frame. The loads of the frame stations can be calculated through simple mathematic graph calculation, the process of constructing a finite element analysis model is omitted, time and workload are reduced, working efficiency is improved, and the load calculation precision of the frame stations is improved.

Description

technical field [0001] The invention belongs to the technical field of aircraft design, and in particular relates to a general-purpose aircraft fuselage axial load processing method. Background technique [0002] For general-purpose aircraft, due to the small size of the aircraft structure, the general form of the aerodynamic load on the aircraft fuselage is the aerodynamic force on the unit length of the fuselage axis, and the unit is N / m. The points of the stations are not consistent, and the load calculation of each point of the aerodynamic load needs to be distributed to the points of each frame station. [0003] For example, in the aerodynamic load of a certain type of aircraft fuselage, the load density of a series of points along the axis of the fuselage is given. To use this load, the load needs to be processed into the points on each frame of the fuselage. Load, in order to meet the use requirements of the load, it is an ideal processing method to analyze and proce...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/15G06F2113/28
Inventor 杜正兴王玉张平贵张增光
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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