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A Near-Zero-Expansion Lattice Structure

A lattice structure, near-zero expansion technology, applied in the aerospace field, can solve the problems of difficult processing and mass production, difficult to control, poor characteristics, etc., to achieve easy engineering practical application, adjustable thermal expansion coefficient, simple structural design Effect

Active Publication Date: 2022-05-24
BEIJING INSTITUTE OF TECHNOLOGYGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0009] (1) Near-zero characteristics are not good
Although the above design can achieve the change of the linear expansion coefficient of the structure from negative to positive, the design with a large control range has poor near-zero characteristics, and the design with good near-zero characteristics has problems such as difficulty in regulation.
[0010] (2) Difficulty in processing and mass production
Although the above design can achieve near-zero expansion characteristics, the design and processing of the spatial lattice structure is relatively difficult, and the sample is usually processed by additive manufacturing, but the demand for the lattice unit is large in practical applications. Manufacturing is obviously not suitable for mass production and processing, and has certain limitations

Method used

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  • A Near-Zero-Expansion Lattice Structure
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Examples

Experimental program
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Effect test

Embodiment 1

[0052] This embodiment discloses a near-zero expansion lattice structure:

[0053] 1) A near-zero-expansion lattice structure, through regular-shaped unit cells such as Figure 5 The contact points 5 shown are arranged and connected, and the overall arrangement effect is as follows figure 1 shown;

[0054] 2) The unit cell includes an inner frame 2, a microstructure and an outer frame 1; the inner frame 2 and the outer frame 1 are center-symmetrical structures; the plurality of microstructures are fixed outside the inner frame 2 in a center-symmetrical manner; the The outer frame 1 puts the inner frame 2 and the microstructure in it, and the unit cell structure is as figure 2 shown;

[0055] 3) The microstructure is composed of a fixed bearing edge 3 and a dynamic adjustment edge 4; the fixed bearing edge 3 is a symmetrical structure, and it is necessary to ensure that every two fixed bearing edges 3 are connected as in-plane line contact; the dynamic adjustment edge 4 Sym...

Embodiment 2

[0061] Keep steps 1) to 3) in Example 1 unchanged, take L Actuation =11mm, W R，outer Taking it as 5.5mm, and putting the set parameters into equations (1) to (7), the linear expansion coefficient of the microstructure is calculated to be -29.8ppm. Then the linear expansion coefficient of the microstructure is brought into the overall structure for simulation, and the linear expansion coefficient of the unit cell structure is measured to be 0.38ppm.

Embodiment 3

[0063] Keep steps 1) to 3) in Example 1 unchanged, take L Actuation =13mm, W R，outer Take it as 6.9mm, put the set parameters into equations (1) to (7), and calculate the linear expansion coefficient of the microstructure to be -36.5ppm. Then, the linear expansion coefficient of the microstructure is brought into the overall structure for simulation, and the linear expansion coefficient of the unit cell structure is measured to be 0.46ppm.

[0064] In the above embodiment, the measured linear expansion coefficients of the unit cell structure are 0.23, 0.38 and 0.46, respectively. This shows that with the regular arrangement of the cell knot shape, the resulting figure 1 For the lattice structure shown, the deformation amounts are only 0.023mm / m, 0.038mm / m and 0.046mm / m when the temperature difference is 100 degrees Celsius. This shows that in extreme environments, even when encountering huge temperature differences caused by environmental changes, the overall deformation o...

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Abstract

The invention relates to a nearly zero-expansion lattice structure, which belongs to the field of aerospace. The object of the invention is to provide a nearly zero-expansion lattice structure in order to solve the problem that the spacecraft is prone to failure during service in an extreme environment. The structure can select materials commonly used in spacecraft, and the structure has near-zero expansion characteristics by using a certain design. After simulation tests, the linear expansion coefficient of the structure can reach 1×e ‑7 Order of magnitude, good thermal stability, the selected test materials are titanium alloy and aluminum alloy, which are commonly used structural materials in spacecraft, with stable and reliable functions, and are replaceable. In terms of processing, due to the low complexity of the design structure, additive manufacturing technology or mechanical processing technology can be used to process and manufacture the structure, which has strong practical applicability.

Description

technical field [0001] The invention relates to a near-zero expansion lattice structure, which belongs to the field of aerospace. Background technique [0002] In recent years, composite materials with light weight, high strength, stiffness and excellent thermal properties have gradually been widely used in the aerospace field, while lattice structural materials have advantages in thermal, electrical and optical properties, and as a potential Lightweight materials have attracted attention. Therefore, in the aerospace field, the lattice structure is usually adopted for corresponding design and application. [0003] In space, due to the complex heating conditions of aircraft, and the obvious changes in the heating conditions of satellites over time during orbital operation, they are often subject to large temperature differences in a short period of time. In the lunar environment, the temperature of the lunar surface can vary from 93k to 395k, and due to the small rotation p...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/22B64G1/66G06F30/15G06F30/23G06F113/10
CPCB64G1/22B64G1/66G06F30/15G06F30/23G06F2113/10
Inventor 郭晓岗梁博于华斌宋维力雷红帅陈明继
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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