CN110287524A - A kind of aircraft joint part improved method and aircraft joint part - Google Patents
A kind of aircraft joint part improved method and aircraft joint part Download PDFInfo
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- CN110287524A CN110287524A CN201910412479.2A CN201910412479A CN110287524A CN 110287524 A CN110287524 A CN 110287524A CN 201910412479 A CN201910412479 A CN 201910412479A CN 110287524 A CN110287524 A CN 110287524A
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- 238000000034 method Methods 0.000 title claims abstract description 38
- 239000000463 material Substances 0.000 claims abstract description 51
- 238000004458 analytical method Methods 0.000 claims abstract description 17
- 238000010276 construction Methods 0.000 claims abstract description 14
- 238000012916 structural analysis Methods 0.000 claims abstract description 13
- 210000003205 muscle Anatomy 0.000 claims abstract description 10
- 238000012216 screening Methods 0.000 claims abstract description 4
- 238000013461 design Methods 0.000 claims description 31
- 229910000838 Al alloy Inorganic materials 0.000 claims description 14
- 238000004519 manufacturing process Methods 0.000 claims description 13
- 238000012545 processing Methods 0.000 claims description 8
- 238000005457 optimization Methods 0.000 claims description 5
- 238000000137 annealing Methods 0.000 claims description 4
- 238000009826 distribution Methods 0.000 claims description 4
- 229910052751 metal Inorganic materials 0.000 claims description 3
- 239000002184 metal Substances 0.000 claims description 3
- 239000000956 alloy Substances 0.000 description 4
- 238000010586 diagram Methods 0.000 description 4
- 230000007547 defect Effects 0.000 description 3
- 208000020442 loss of weight Diseases 0.000 description 3
- 238000005452 bending Methods 0.000 description 2
- 239000002994 raw material Substances 0.000 description 2
- 235000006508 Nelumbo nucifera Nutrition 0.000 description 1
- 240000002853 Nelumbo nucifera Species 0.000 description 1
- 235000006510 Nelumbo pentapetala Nutrition 0.000 description 1
- 238000005299 abrasion Methods 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- 239000004411 aluminium Substances 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000035800 maturation Effects 0.000 description 1
- 230000000704 physical effect Effects 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/15—Vehicle, aircraft or watercraft design
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/17—Mechanical parametric or variational design
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/06—Power analysis or power optimisation
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Abstract
The present invention provides a kind of aircraft joint part improved method and aircraft joint part.This method comprises: carrying out mechanics property analysis to original part, the mechanical analysis result of original part is obtained；Structural analysis is carried out to original part, obtains the results of structural analysis of original part；According to mechanical analysis result and results of structural analysis, the structure of original part is improved, new construction is obtained；Wherein, new construction includes three ribs, web and axis, and axis is fixedly connected by first rib with one end of web, and the second rib will be fixedly connected in the middle part of axis and web, axis is fixedly connected by the second rib with the other end of web, and the hole that adjacent two muscle and axis and web are surrounded in three muscle is lightening hole；According to preset Structural strength calls, results of structural analysis and mechanical analysis as a result, determining performance indicator；On the basis of meeting performance indicator, screening aeronautical material selects the selection of material；The outline drawing of new parts is designed according to the characteristic of the selection of material and new construction.
Description
Technical field
The invention belongs to field of airplane design, a kind of aircraft joint part improved method and aircraft connector zero are provided
Part.
Background technique
In airplane parts design, the selection of material is a highly important ring, and reasonably the selection of material is related to product
Performance, service life, reliability, cost and equipment it is advanced, and update with the development of science and technology with equipment upgrade requirement plus
Play, importance are also constantly increasing, and therefore, material selection is the most essential steps of airplane parts design.In general, it designs
Personnel only develop new product on original form (or drawing), or use for reference original shape both domestic and external, so often will be with
The preceding material sleeve once having is used in new design.Designer proposes on the basis of analyzing part time job condition to material used
The performance requirement of material.Operating condition refer to stress form (stretch, compression, bending, torsion or bending it is compound etc.), load character
(static load, dynamic load, impact, load distribution etc.), by fretting wear situation；Working environment (such as surrounding medium, operating temperature
Deng)；And the particular/special requirements such as conductive, thermally conductive.Preliminary material selection is designed according to the service performance of material.So-called usability
Can, refer to that material can guarantee that part works normally the prerequisite performance of institute.It includes mechanical property, physical property and chemically
Energy.The service performance of part is primarily referred to as the mechanical property of material, and when general selection, top priority is correctly analysis part
Operating condition and main failure mode, accurately to judge main mechanical properties index required by part.
As shown in Figure 1, such aircraft mainly plays connection function with important joint part, bear dead load, intensity requirement compared with
It is high.Aluminum alloy materials are generallyd use, rib is thicker in structure, and it is wider with web junction, guaranteed by thick and solid rib enough
Intensity, materials are more, and weight is larger.Major defect is that part quality is big, high production cost.
Summary of the invention
The present invention provides a kind of aircraft joint part improved method and aircraft joint part, is able to solve part quality
Greatly, the problem of high production cost.
In a first aspect, providing a kind of aircraft joint part improved method, comprising:
Mechanics property analysis is carried out to original part, obtains the mechanical analysis result of the original part；
Structural analysis is carried out to original part, obtains the results of structural analysis of the original part；
According to the mechanical analysis result and the results of structural analysis, the structure of the original part is improved, is obtained new
Structure；Wherein, the new construction includes three ribs, web and axis, and first rib, which fixes one end of the axis and the web, to be connected
It connects, the second rib will be fixedly connected in the middle part of the axis and the web, and the second rib consolidates the other end of the axis and the web
Fixed to connect, the hole that adjacent two muscle and axis and web are surrounded in three muscle is lightening hole；
According to preset Structural strength calls, results of structural analysis and mechanical analysis as a result, determining performance indicator；
On the basis of meeting the performance indicator, screening aeronautical material selects the selection of material；
The outline drawing of new parts is designed according to the characteristic of the selection of material and the new construction.
Further, the characteristic and the new construction according to the selection of material design new parts outline drawing it
Afterwards, the method also includes:
According to the three-dimensional digital-to-analogue of new parts described in the shape G- Design, by the new knot of three-dimensional digital-to-analogue design of the new parts
The method of processing parts of structure；
The technique for working out the new parts according to the selection of material and the new construction；
Mold tooling needed for the new parts is designed, manufactures processing.
Blank dimension needed for designing new parts, and designed by part streamline requirement and produce metal streamline along size knot
The blank that the distribution of structure shape and machine-finish allowance are 5mm.
Process and manufacture the new parts；Wherein, datum level is milled out first, then part overall structure is digitized
Programming, mills out shape using Digital manufacturing, reaches the requirement of high-precision size；
Initial workpiece identification.
Further, the stress form of the original part and the stress form of the new parts are all that axial support carries
Lotus.
Further, the specific strength of the selection of material is higher than the material of the original part.
Further, the selection of material is 7050 aluminium alloys, material lift 35% of the tensile strength than original part.
Further, the optimization method of the structure for improving the original part is Mechanics Criterion method.
Further, the fit tolerance of the new parts uses basic hole system.
It further, should be using annealing woollen when processing and manufacture the new parts.
Second aspect provides a kind of aircraft joint part, comprising: three ribs, web and axis；
Wherein, the axis is fixedly connected by first rib with one end of the web, and the second rib is by the axis and the web
Middle part be fixedly connected, the axis is fixedly connected by the second rib with the other end of the web, adjacent two in three muscle
The hole that muscle and axis and web are surrounded is lightening hole.
Further, second rib vertically with the web.
Advantages of the present invention: by being detected in detail to aircraft with joint part, relevant information is compiled, is carried out relevant
Experimental analysis judges the principal mode and reason of failure, on the basis of analyzing part time job condition, proposes to material therefor
Performance requirement selects new suitable material.Find out intrinsic defect, propose corrective measure, it is ensured that the effective utilization of part and
Improve the ability that part resists failure.The part newly designed not only proof strength requirement, also reduces material utilization amount, optimizes
Dimensional structure, removes and reduces the internal stress of part, to improve part service life.Aircraft loss of weight is played simultaneously
Purpose of design.
Figure of description
Fig. 1 is the schematic diagram of original part in the prior art.
Fig. 2 is design cycle schematic diagram provided by the invention.
Fig. 3 is the schematic diagram of new parts provided by the invention.
Wherein, one-piece parts are divided into rib 1, web 2 and axis 3；Flank design has lightening hole 4a, lightening hole 4b.
Fig. 4 is the schematic diagram of new parts provided by the invention.
Specific implementation
The present invention is described in further detail below:
Element Design and material selection are closely related in entire design concept.Because material greatly influences product or portion
The selection of material just must be taken into consideration in the initial period in function, manufacturing method and the cost of part, a successful design.Material selection
With design the reasonable structure snd size of components, and according to the function of products or components, analyze the load that it is born and go forward side by side
Row stress is to guarantee part safe operation and service life.
The failure mode and mechanism and feedback of understanding product are to improve components or the new production of initiative to detail of design
The important channel of product.So-called failure refers to that aircraft product or components lose the behavior of its predetermined function during military service.Fly
The failure mode of machine components is mainly shown as fracture, abrasion and corrosion.The failure mode of part and its specific operating condition
It is undivided.By deep scene, relevant information is compiled, carries out relevant experimental analysis, judges the main shape of failure
Formula and reason find out intrinsic defect, propose corrective measure, determine the main mechanical properties index that selected materials should meet,
The information with Practical significance is provided for correct selection, it is ensured that the effective utilization of part and the ability for improving part resistance failure.
Final design not only can guarantee service performance out, but also can mitigate weight, reduce the part of material cost.
As shown in Fig. 2, a kind of aircraft joint part improved method provided by the invention, comprising the following steps:
Step 1, the original part of analysis: as shown in Figure 1, the main stress form of original part is axial support loads, commonly
Although aluminium alloy intensity can satisfy the requirement of the part, it is more apparent compared to Modern New high-strength aluminum alloy disadvantage.
So Novel aluminum alloy material can be selected to substitute primary aluminum alloy material, service life and the safety system of part can be greatly improved
Number.
Step 2, structural analysis, original part are entity component structure, and the big weight weight of volume, space hold is big, influences it
His spare part assembles and is not easy to the manipulation of other parts.It is required according to certain type machine aircaft configuration, designs new construction (such as Fig. 3
With shown in Fig. 4) include three ribs 1, web 2 and axis 3；Design has the first lightening hole 4a and the second lightening hole 4b between rib and rib.
Portion's size gabarit of new parts becomes smaller；And it devises two lightening holes and reduces materials.The outer dimension of new parts, which changes, to be subtracted
It ensure that part strength while few material utilization amount.
Step 3, material selection, while according to Structural strength calls and analysis as a result, determining performance indicator.Screening is domestic
LD5 aluminium alloy is changed to 7050 aluminium alloys by the aeronautical material of outer maturation, initial option.Compare two kinds of material performance index LD5 aluminium
Strength of alloy 365MPa, 7050 aluminium alloy tensile strength 495MPa.7050 aluminium alloy of material selection of new design elements,
Tensile strength is than raw material LD5 aluminum alloy lifting 35%.
Step 4 requires to redesign part size structure according to the characteristic of the selection of material and product design, also
It is to say according to the stress form of new parts, structure and meet aircraft loss of weight and need to design new External Shape figure.Outside new parts
Shape G- Design optimizes dimensional structure, and structural optimization method uses Mechanics Criterion method.The fit tolerance of new parts uses base
Hole system.
Step 5, the three-dimensional digital-to-analogue for designing new parts, by the part processing side of the three-dimensional digital-to-analogue design new construction of new parts
Method；The technique for working out new parts.
Step 6 is designed mold tooling needed for new parts, manufacture processing.
Step 7 is designed blank dimension needed for new parts, and designs by part streamline requirement and produce metal stream
The blank that line is 5mm along the distribution of dimensional structure shape and machine-finish allowance.
Step 8, part processing and manufacture, new parts should be easy to process using annealing woollen.Datum level is milled out first, then
Digitlization programming is carried out to part overall structure, shape is milled out using Digital manufacturing, reaches the requirement of high-precision size.
Step 9, initial workpiece identification.
Newly-designed part rib size gabarit becomes smaller；And it devises two lightening holes and reduces materials.
Newly-designed outer dimension, which changes, ensure that part strength while reducing material utilization amount.
7050 aluminium alloy of material selection of new design elements, tensile strength is than raw material LD5 aluminum alloy lifting 35%.
New parts outline drawing design optimization dimensional structure, structural optimization method use Mechanics Criterion method.
The fit tolerance of new parts uses basic hole system.
New parts should be easy to process using annealing woollen.
This method improve after part can satisfy product parts size require, guarantee design service performance while,
It is able to satisfy the needs of aircraft loss of weight again, overcomes the big disadvantage of original pts wt.
Claims (10)
1. a kind of aircraft joint part improved method characterized by comprising
Mechanics property analysis is carried out to original part, obtains the mechanical analysis result of the original part；
Structural analysis is carried out to original part, obtains the results of structural analysis of the original part；
According to the mechanical analysis result and the results of structural analysis, the structure of the original part is improved, new construction is obtained；
Wherein, the new construction includes three ribs, web and axis, and the axis is fixedly connected by first rib with one end of the web, the
Two ribs will be fixedly connected in the middle part of the axis and the web, and the second rib, which fixes the other end of the axis and the web, to be connected
It connects, the hole that adjacent two muscle and axis and web are surrounded in three muscle is lightening hole；
According to preset Structural strength calls, results of structural analysis and mechanical analysis as a result, determining performance indicator；
On the basis of meeting the performance indicator, screening aeronautical material selects the selection of material；
The outline drawing of new parts is designed according to the characteristic of the selection of material and the new construction.
2. the method according to claim 1, wherein the characteristic according to the selection of material and the new knot
After structure designs the outline drawing of new parts, the method also includes:
According to the three-dimensional digital-to-analogue of new parts described in the shape G- Design, new construction is designed by the three-dimensional digital-to-analogue of the new parts
Method of processing parts；
The technique for working out the new parts according to the selection of material and the new construction；
Mold tooling needed for the new parts is designed, manufactures processing.
Design new parts needed for blank dimension, and designed by part streamline requirement and produce metal streamline along dimensional structure outside
The blank that shape distribution and machine-finish allowance are 5mm.
Process and manufacture the new parts；Wherein, datum level is milled out first, then digitlization volume is carried out to part overall structure
Journey mills out shape using Digital manufacturing, reaches the requirement of high-precision size；
Initial workpiece identification.
3. the method according to claim 1, wherein the stress form and the new parts of the original part
Stress form is all axial support loads.
4. the method according to claim 1, wherein the specific strength of the selection of material is higher than the original part
Material.
5. the method according to claim 1, wherein the selection of material is 7050 aluminium alloys, tensile strength
Than the material lift 35% of original part.
6. the method according to claim 1, wherein the optimization method of the structure for improving the original part
For Mechanics Criterion method.
7. according to claim 1, which is characterized in that the fit tolerance of the new parts uses basic hole system.
8. aircraft according to claim 2 joint part improved method, which is characterized in that process and manufacture described new zero
It should be using annealing woollen when part.
9. a kind of aircraft joint part characterized by comprising three ribs, web and axis；
Wherein, the axis is fixedly connected by first rib with one end of the web, and the second rib will be in the axis and the web
Portion is fixedly connected, and the axis is fixedly connected by the second rib with the other end of the web, in three muscle adjacent two muscle with
The hole that axis and web are surrounded is lightening hole.
10. part according to claim 8, which is characterized in that second rib vertically with the web.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910412479.2A CN110287524A (en) | 2019-05-17 | 2019-05-17 | A kind of aircraft joint part improved method and aircraft joint part |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201910412479.2A CN110287524A (en) | 2019-05-17 | 2019-05-17 | A kind of aircraft joint part improved method and aircraft joint part |
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| CN110287524A true CN110287524A (en) | 2019-09-27 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115615929A (en) * | 2022-12-13 | 2023-01-17 | 苏州点线空间科技有限公司 | Mechanical part surface defect detection method and system based on laser scanning |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB157310A (en) * | 1919-02-27 | 1922-06-08 | John William Rapp | Improvements in airplane ribs |
| CN202485854U (en) * | 2012-03-09 | 2012-10-10 | 陕西飞机工业（集团）有限公司 | Integrated static pressure sensing part |
| CN203612814U (en) * | 2013-08-23 | 2014-05-28 | 中国航空工业集团公司西安飞机设计研究所 | Truss type integral support |
| CN106650045A (en) * | 2016-12-05 | 2017-05-10 | 大连理工大学 | Optimized design and strength analysis method of secondary box section structure |
-
2019
- 2019-05-17 CN CN201910412479.2A patent/CN110287524A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB157310A (en) * | 1919-02-27 | 1922-06-08 | John William Rapp | Improvements in airplane ribs |
| CN202485854U (en) * | 2012-03-09 | 2012-10-10 | 陕西飞机工业（集团）有限公司 | Integrated static pressure sensing part |
| CN203612814U (en) * | 2013-08-23 | 2014-05-28 | 中国航空工业集团公司西安飞机设计研究所 | Truss type integral support |
| CN106650045A (en) * | 2016-12-05 | 2017-05-10 | 大连理工大学 | Optimized design and strength analysis method of secondary box section structure |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115615929A (en) * | 2022-12-13 | 2023-01-17 | 苏州点线空间科技有限公司 | Mechanical part surface defect detection method and system based on laser scanning |
| CN115615929B (en) * | 2022-12-13 | 2023-03-14 | 苏州点线空间科技有限公司 | Mechanical part surface defect detection method and system based on laser scanning |
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