A Stress Calculation Method of Ordinary Frame of Aircraft Fuselage Under Bending Load
A common stress technology, applied in the field of stress calculation of ordinary frames of aircraft under bending load, can solve the problems of lag in the calculation process, low calculation accuracy, long calculation time, etc., and achieve the effect of early design work progress and simple calculation.
Active Publication Date: 2021-05-25
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 mechanism.
[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 the stress of an ordinary frame of an aircraft fuselage under the action of a bending load, which belongs to the technical field of aircraft structure strength analysis, and comprises the following steps: Step 1: calculating the bending moment M of the overall load of the aircraft at the ordinary frame, and The normal stress σ generated by the bending moment M on the fuselage skin and stringers; Step 2: The resultant force F of the normal stress σ generated on the skin and stringers is equivalent to an axial force, and the axial force generates a tangential load q m ;Step 3: According to the tangential load q m Find the maximum bending moment M in the frame plane max ;Step 4: According to the maximum bending moment M max Find the ordinary frame stress σ q . The method for calculating the stress of an ordinary frame of an aircraft under a bending load overcomes the disadvantages of the commonly used finite element method and makes the calculation easier; in addition, the method can be used in the initial stage of aircraft design without waiting for the structural design to be completed. The calculation of ordinary frame stress can be carried out, which greatly advances the design work schedule.
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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IPC IPC(8): G06F30/23G06F119/14
CPCG06F30/15G06F2119/06
Inventor 薛应举张引利冯雅君
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA