A method of arranging an airfoil cover
An arrangement method and airfoil port technology, which can be used in special data processing applications, instruments, electrical digital data processing, etc., can solve problems such as uneconomical and large stress, and achieve the effects of cost reduction, performance improvement, and stiffness improvement.
Active Publication Date: 2016-12-28
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
View PDF3 Cites 0 Cited by
- Summary
- Abstract
- Description
- Claims
- Application Information
AI Technical Summary
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
Method used
the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
View moreImage
Smart Image Click on the blue labels to locate them in the text.
Smart ImageViewing Examples
Examples
Experimental program
Comparison scheme
Effect test
Embodiment Construction
[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≥...
the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More PUM
Login to View More Abstract
A method for arranging airfoil flaps is characterized in that, first, using finite element analysis on the airfoil to obtain the maximum deformation area of the airfoil box section where the flaps need to be arranged; secondly, during the arrangement of the flaps, Reserve this area between the flaps to form an initial gap between several flaps; thirdly, conduct finite element analysis on the airfoil of the above-mentioned flap layout to calculate the maximum deformation of the gap area; fourth, put the The maximum deformation is compared with the gap value, if the maximum deformation is greater than the initial gap value, the interference between adjacent flaps is calculated, and the initial gap value is adjusted so that the final gap value is not less than the sum of the initial gap value and the interference value; Fifth, fill the gap with rubber profiles. Compared with the prior art, the present invention has advantages and positive effects, such as performance improvement, cost reduction and the like. The trailing edge structure can make the trailing edge withstand a certain deformation of the box section while ensuring the structural function of the trailing edge, without paying too much weight to improve the rigidity of the trailing edge.
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...
Claims
the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More Application Information
Patent Timeline
Login to View More Patent Type & Authority Patents(China)
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