CN108801737A - A kind of micro- truss compression test part of increasing material manufacturing - Google Patents
A kind of micro- truss compression test part of increasing material manufacturing Download PDFInfo
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- CN108801737A CN108801737A CN201810799265.0A CN201810799265A CN108801737A CN 108801737 A CN108801737 A CN 108801737A CN 201810799265 A CN201810799265 A CN 201810799265A CN 108801737 A CN108801737 A CN 108801737A
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- truss
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- material manufacturing
- increasing material
- compression test
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N1/00—Sampling; Preparing specimens for investigation
- G01N1/28—Preparing specimens for investigation including physical details of (bio-)chemical methods covered elsewhere, e.g. G01N33/50, C12Q
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- Health & Medical Sciences (AREA)
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- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The present invention relates to structural material fields, and in particular to arrives a kind of miniature truss compression test part of increasing material manufacturing.The micro- truss compression test part of increasing material manufacturing of the present invention, including：Micro- truss, for the truss structure of pyramid cell element quadrate array composition；Upper covering and lower covering, the platy structure being square are connected to symmetrical two sides of micro- truss；Wherein, micro- truss and the upper covering and lower covering are integrally formed using increasing material manufacturing technique.Integrally formed structure of the invention avoids because the fatigue point that connection member occurs, increases the fatigue life of testpieces, improve the optimization design and Strength Analysis Theory of micro- truss mechanism, basis is played in aviation field further genralrlization application for the class formation.
Description
Technical field
The micro- truss compression test part of increasing material manufacturing of the present invention is related to structural material field, and in particular to arrives a kind of increasing material system
The miniature truss compression test part made.
Background technology
Micro- truss structure is currently to think the most promising superpower tough material of the advanced lightweight of a new generation in the world.It is conventionally manufactured
The main method of micro- truss structure be " investment casting " and " pressing lap method for brazing, the process is more complicated for both methods,
Difficulty of processing is big, and manufacturing cost is high, using micro- truss structure generally existing internal rod geometric dimension made of above method compared with
Greatly, the features such as inter-cell negligible amounts, its development is constrained in weight and multifunctionality.
Currently, China's aviation field begins to focus on the light-weight design that aircaft configuration is realized using micro- truss lattice material,
Mechanical behavior development systematic research for the class formation has great importance for the development of aeronautical technology.
And designed for the material grade mechanical test part of the micro- truss structure of increasing material manufacturing, perfect technical solution is there is no, is limited
The application and development of the micro- truss structure of increasing material manufacturing are made.
Invention content
The micro- truss compression test part of increasing material manufacturing of the present invention, it is at least one existing in the prior art to solve or overcoming
Problem.
The micro- truss compression test part of increasing material manufacturing of the present invention, including：
Micro- truss, for the truss structure of pyramid cell element quadrate array composition；
Upper covering and lower covering, the platy structure being square are connected to symmetrical two sides of micro- truss；
Wherein
Micro- truss is integrally formed using increasing material manufacturing technique with the upper covering and lower covering.
Preferably, the shank diameter of the pyramid cell element is 0.7mm~1.0mm, the vertex of the pyramid cell element to institute
The length for stating bottom center's point of pyramid cell element is 5mm~10mm.
Preferably, the number of plies of the pyramid cell element between the upper covering and lower covering is 2~5 layers.
Preferably, the longest edge length dimension of the upper covering and lower covering is 50mm~100mm, the length ruler of most short side
Very little is 0.5mm~1.2mm.
Preferably, the micro- truss compression test part of the increasing material manufacturing uses titanium alloy material.
Advantageous effect：
The micro- truss compression test part of increasing material manufacturing of the present invention, the mechanical behavior to carry out the micro- truss structure of increasing material manufacturing are ground
Study carefully, improve the optimization design and Strength Analysis Theory of micro- truss mechanism, is the class formation in aviation field further genralrlization application
Play basis.
Description of the drawings
Fig. 1 is the simple structure diagram of the present invention；
Fig. 2 is the front view of the present invention；
Fig. 3 is the configuration diagram of the miniature truss of the present invention；
Wherein, the upper coverings of 1-, covering under 2-, the micro- truss of 3-.
Specific implementation mode
To make the present invention be more easily understood, the present invention is described in detail below with reference to attached drawing.
In the description of the present invention, it is to be understood that, term "center", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or positional relationship of the instructions such as "left", "right", "vertical", "horizontal", "top", "bottom" "inner", "outside" is based on attached drawing institute
The orientation or positional relationship shown, is merely for convenience of description of the present invention and simplification of the description, and does not indicate or imply the indicated dress
It sets or element must have a particular orientation, with specific azimuth configuration and operation, therefore should not be understood as protecting the present invention
The limitation of range.
Such as the micro- truss compression test part of increasing material manufacturing that Fig. 1 and Fig. 3 is the present invention, the micro- truss compression test part of increasing material manufacturing
Using titanium alloy material, including：
If Fig. 3 is micro- truss 3, for the truss structure of pyramid cell element quadrate array composition；
Such as Fig. 1 or Fig. 2, it is symmetrical to be connected to micro- truss 3 for upper covering 1 and lower covering 2, the platy structure being square
Two sides, upper covering 1 and lower covering 2 play the role of d type and the micro- truss of support, while holding when as compression test
Section, micro- truss play the role of carrying, support two side skins；
Wherein, this hair that micro- truss 3 uses increasing material manufacturing technique integrally formed, integrally formed with upper covering 1 and lower covering 2
Bright structure is not in traditional structure because fatigue rupture point caused by connection, increases the stability and service life of structure.
In embodiment, it is contemplated that the load-carrying efficiency of increases material manufacturing technology characteristic and structure of the invention, setting, pyramid born of the same parents
The shank diameter of member is 0.7mm~1.0mm, and the length of bottom center's point on the vertex of pyramid cell element to pyramid cell element is 5mm
~10mm, the number of plies of the pyramid cell element between upper covering 1 and lower covering 2 are 2~5 layers, the longest of upper covering 1 and lower covering 2
Edge lengths size is 50mm~100mm, and the length dimension of most short side is 0.5mm~1.2mm.
It is last it is to be noted that：The above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations.To the greatest extent
Present invention has been described in detail with reference to the aforementioned embodiments for pipe, it will be understood by those of ordinary skill in the art that：It is still
Can be with technical scheme described in the above embodiments is modified, or which part technical characteristic is equally replaced
It changes；And these modifications or replacements, the essence for various embodiments of the present invention technical solution that it does not separate the essence of the corresponding technical solution
God and range.
Claims (5)
1. a kind of micro- truss compression test part of increasing material manufacturing, which is characterized in that including：
Micro- truss (3), for the truss structure of pyramid cell element quadrate array composition；
Upper covering (1) and lower covering (2), the platy structure being square are connected to symmetrical two of micro- truss (3)
Side；Wherein
Micro- truss (3) is integrally formed using increasing material manufacturing technique with the upper covering (1) and lower covering (2).
2. the micro- truss compression test part of increasing material manufacturing according to claim 1, which is characterized in that the bar of the pyramid cell element
The length of a diameter of 0.7mm~1.0mm, bottom center's point on the vertex of the pyramid cell element to the pyramid cell element is
5mm~10mm.
3. the micro- truss compression test part of increasing material manufacturing according to claim 1, which is characterized in that the pyramid cell element is in institute
It is 2~5 layers to state the number of plies between covering (1) and lower covering (2).
4. the micro- truss compression test part of increasing material manufacturing according to claim 1, which is characterized in that the upper covering (1) and
The longest edge length dimension of lower covering (2) is 50mm~100mm, and the length dimension of most short side is 0.5mm~1.2mm.
5. the micro- truss compression test part of increasing material manufacturing according to claim 1, which is characterized in that the micro- purlin of increasing material manufacturing
Frame compression test part uses titanium alloy material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810799265.0A CN108801737A (en) | 2018-07-19 | 2018-07-19 | A kind of micro- truss compression test part of increasing material manufacturing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810799265.0A CN108801737A (en) | 2018-07-19 | 2018-07-19 | A kind of micro- truss compression test part of increasing material manufacturing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108801737A true CN108801737A (en) | 2018-11-13 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201810799265.0A Pending CN108801737A (en) | 2018-07-19 | 2018-07-19 | A kind of micro- truss compression test part of increasing material manufacturing |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109489467A (en) * | 2018-11-23 | 2019-03-19 | 西安航天发动机有限公司 | A kind of airspace engine heat exchange component and preparation method thereof |
| CN111703067A (en) * | 2020-05-29 | 2020-09-25 | 同济大学 | Composite energy absorption structure based on square unit twin crystal type micro-truss structure and 3D printing method thereof |
| CN112881128A (en) * | 2021-02-04 | 2021-06-01 | 航天科工防御技术研究试验中心 | Tensile sample for additive manufacturing lattice structure material and tensile test method |
| CN113125259A (en) * | 2021-04-12 | 2021-07-16 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Quasi-static compression test piece with lattice structure and test method |
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| CN206719530U (en) * | 2017-07-19 | 2017-12-08 | 中国空空导弹研究院 | A kind of support bar and the undercarriage and aircraft using the support bar |
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| CN204356959U (en) * | 2014-12-23 | 2015-05-27 | 中国建筑第八工程局有限公司 | 3D prints truss cassette ceiling |
| CN206719530U (en) * | 2017-07-19 | 2017-12-08 | 中国空空导弹研究院 | A kind of support bar and the undercarriage and aircraft using the support bar |
| CN108009336A (en) * | 2017-11-28 | 2018-05-08 | 北京航空航天大学 | A kind of micro- truss structure carrying and the Multipurpose Optimal Method of thermal protection structure |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109489467A (en) * | 2018-11-23 | 2019-03-19 | 西安航天发动机有限公司 | A kind of airspace engine heat exchange component and preparation method thereof |
| CN111703067A (en) * | 2020-05-29 | 2020-09-25 | 同济大学 | Composite energy absorption structure based on square unit twin crystal type micro-truss structure and 3D printing method thereof |
| CN111703067B (en) * | 2020-05-29 | 2021-05-11 | 同济大学 | Composite energy absorption structure based on square unit twin crystal type micro-truss structure and 3D printing method thereof |
| CN112881128A (en) * | 2021-02-04 | 2021-06-01 | 航天科工防御技术研究试验中心 | Tensile sample for additive manufacturing lattice structure material and tensile test method |
| CN112881128B (en) * | 2021-02-04 | 2023-03-21 | 航天科工防御技术研究试验中心 | Tensile sample for additive manufacturing lattice structure material and tensile test method |
| CN113125259A (en) * | 2021-04-12 | 2021-07-16 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Quasi-static compression test piece with lattice structure and test method |
| CN113125259B (en) * | 2021-04-12 | 2022-10-28 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Quasi-static compression test piece with lattice structure and test method |
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Application publication date: 20181113 |
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