Arrangement method of airfoil doors
A layout method and technology of airfoil openings, applied in special data processing applications, instruments, electrical digital data processing, etc., can solve problems such as large stress and uneconomical, achieve performance improvement, cost reduction, and increase stiffness
Active Publication Date: 2014-02-26
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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Problems solved by technology
[0002] Most of the trailing edge of the airfoil is equipped with various system pipelines, which need to be opened frequently for maintenance of various systems, so the trailing edge skin is generally designed as a detachable or openable cover, and the trailing edge needs to be installed with the wing during actual use. Since the rigidity of the box section is much greater than that of the rear edge during design, this will cause the rear edge to generate greater stress than the box section when subjected to the same deformation, so that the structure of the rear edge is earlier than the box section. Destruction; Since the trailing edge is not the main structure in the airfoil structure, it is very uneconomical to increase the weight of the trailing edge to increase the stiffness of the trailing edge
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[0020] Below in conjunction with accompanying drawing, the present invention is described in further detail:
[0021] 1) The maximum deformation area of the airfoil box section where the flap is arranged is determined through the calculation of the finite element model, see figure 1 As shown; the shaded area indicated by the numbers 3 and 4 in the figure is the maximum deformation area shown by the finite element calculation results, and the maximum deformation is L. This model should be brought into the model of the whole machine or the airfoil box section where the flap is located;
[0022] 2) Leave an initial gap between the two adjacent flaps above the maximum deformation area (the gap value can be L);
[0023] 3) For the model in step 2), continue to use finite elements to calculate the maximum deformation, and obtain the maximum deformation L1, compare the new deformation L1 with the initial gap value L, if L1 is greater than L, modify the initial gap value L, Make L≥...
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An arrangement method of airfoil doors is characterized by comprising the steps of firstly, leading an airfoil to be subjected to finite element analysis to obtain the maximum deformation region of an airfoil box of doors needing to be arranged; secondly, during a door arrangement process, reserving the region between the doors to form a plurality of initial gaps between the doors; thirdly, leading the airfoil of the above door arrangement mode to be subjected to finite element analysis again, and calculating the maximum amount of deformation of the gap region; fourthly, comparing the maximum amount of deformation with a gap value, if the maximum amount of deformation is larger than the gap value, computing interference between adjacent doors and adjusting the initial gap value to enable a final gap value to be no less than the sum of the initial gap value and the interference amount; fifthly, filling the gap with rubber profiles. Compared with the prior art, the arrangement method of the airfoil doors has the advantages of improving performance, reducing costs and the like. A trailing edge structure guarantees the functions of the tailing edge structure and meanwhile enables a tailing edge to bear certain box deformation, and the rigidity of the tailing edge can be improved without too much weight added.
Description
technical field [0001] The invention belongs to the technical field of aircraft structure design, and in particular relates to a method for arranging a wing cover. Background technique [0002] Most of the trailing edge of the airfoil is equipped with various system pipelines, which need to be opened frequently for maintenance of various systems, so the trailing edge skin is generally designed as a detachable or openable cover, and the trailing edge needs to be installed with the wing during actual use. Since the rigidity of the box section is much greater than that of the rear edge during design, this will cause the rear edge to generate greater stress than the box section when subjected to the same deformation, so that the structure of the rear edge is earlier than the box section. Destruction; Since the trailing edge is not the main structure in the airfoil structure, it is very uneconomical to increase the weight of the trailing edge in order to increase the stiffness of...
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IPC IPC(8): G06F17/50
Inventor 达磊熊伟贾欲明胡昌宏
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA