Method for calculating stress of aircraft fuselage frame under bending load
An aircraft fuselage and bending load technology, which is applied in calculation, computer-aided design, special data processing applications, etc., can solve the problems of low calculation accuracy, lag in calculation process, long calculation time, etc., and achieves simple calculation and advanced design work progress. Effect
Active Publication Date: 2018-05-29
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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[0003] The purpose of the present invention is to provide a method for calculating the stress of an ordinary frame of an aircraft fuselage under bending loads, so as to solve the problems of lag in the calculation process, low calculation accuracy, and long calculation time in the prior art
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[0030] 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.
[0031] Such as figure 1 As shown in the schematic diagram of the aircraft fuselage structure, the ordinary frame 1 is the main load-bearing part of the aircraft fuselage structure, and a plurality of ordinary frames 1 surrounding a circle are arranged in parallel and then passed through the stringers 3 arranged in parallel with the axis of the fuselage. The ordinary frame 1 completes the fixing of the structure, and the skin 2 is laid on the outside of the ordinary frame 1, which constitutes the aircraft fuselage structure.
[0032] Such as figure 2 As shown in the schematic cross-sectional view of the ordinary frame of the aircraft, the ordinary frame 1 is composed of an L-shaped fra...
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The invention relates to a method for calculating a stress of an aircraft fuselage frame under a bending load, and belongs to the technical field of aircraft structure strength analysis. The method comprises the following steps of 1, calculating a bending moment M of a total load of an aircraft at the frame, and positive stresses sigma generated on fuselage skin and stringer by the bending momentM; 2, enabling resultant force F of the positive stresses sigma generated on the skin and the stringer to be equivalent to axial force, and generating a section load qm by the axial force; 3, according to the section load qm, working out a maximum bending moment Mmax in a frame plane; and 4, according to the maximum bending moment Mmax, working out the frame stress sigma q. According to the methodfor calculating the stress of the aircraft fuselage frame under the bending load, the defects of a finite element method used generally at present are overcome, so that the calculation is simpler andmore convenient; and in addition, by utilizing the method, the frame stress can be calculated without waiting for completion of structure design in an initial stage of aircraft design, so that the design work progress is greatly advanced.
Description
technical field [0001] The invention belongs to the technical field of aeronautical structure strength analysis, in particular to a method for calculating the stress of an ordinary frame of an aircraft under a bending load. Background technique [0002] Ordinary frame is the most common structure on the aircraft. Its function is to bear the load on the aircraft, keep the shape of the fuselage intact, and provide support for the skin of the fuselage. The strength analysis of the common frame is an important content of the strength analysis of the aircraft structure, and it is the basic condition to ensure the safety of the aircraft. Obtaining the stress of the common frame is the prerequisite for the strength analysis. The previous analysis method is to use finite element method to complete huge and complex analysis with the help of computer, but this analysis method must wait until the structural design is completed, which will make the strength design work lag and repeat. ...
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Login to View More IPC IPC(8): G06F17/50
CPCG06F30/15G06F2119/06
Inventor 薛应举张引利冯雅君
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA