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Method for making space remote sensor bracket and space remote sensor bracket

A technology of space remote sensor and manufacturing method, which is applied in the direction of machine platform/support, supporting machine, mechanical equipment, etc., can solve problems such as poor performance, and achieve the effects of good thermal conductivity, high precision, and light weight

Active Publication Date: 2015-05-06
浙江驰宇空天技术有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0012] Based on the above, it can be seen that how to realize aluminum alloy composite materials to replace traditional aluminum alloy or titanium alloy materials with poor performance on space sensor brackets is a problem that must be solved in the current space remote sensor manufacturing process

Method used

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  • Method for making space remote sensor bracket and space remote sensor bracket
  • Method for making space remote sensor bracket and space remote sensor bracket
  • Method for making space remote sensor bracket and space remote sensor bracket

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0049] Such as figure 1 As shown, the manufacturing method of the space remote sensor bracket in this embodiment includes the following specific steps:

[0050] Step 1: Decompose the required space remote sensor support into several decomposed components that meet the required physical and mechanical properties through physical model analysis;

[0051] in,

[0052] The physical model analysis includes physical model analysis such as finite element mechanical analysis and modal analysis, which can verify the strength and perform modal frequency analysis through simulation calculations;

[0053] The decomposed member may be a decomposed member such as a plate member or a tubular member;

[0054] Step 2: processing the aluminum matrix composite material blank and making it into the decomposed component;

[0055] Step 3: Assemble and weld the manufactured disassembled components into the space remote sensor bracket to be manufactured, wherein the aluminum matrix composite mater...

Embodiment 2

[0058] The manufacturing method of the space remote sensor bracket of the present embodiment includes the following specific steps:

[0059] Such as Figure 2-Figure 3 As shown, step 1: through the physical model analysis, the space remote sensor support ( figure 1 The shown space remote sensor support) is decomposed into 8 decomposed components that meet the required physical and mechanical properties; and the decomposed components are plate-shaped components;

[0060]Step 2: processing the aluminum matrix composite material blank and making it into the plate-shaped member;

[0061] Step 3: Combine and weld the manufactured plate-like components into the space remote sensor bracket to be manufactured.

[0062] Wherein, making the disassembled components sequentially includes lightweight machining and stress relief aging heat treatment.

[0063] Such as Figure 4 As shown, the lightweight machining includes the following steps:

[0064] Step S1: Grinding the aluminum matr...

Embodiment 3

[0069] In this embodiment, on the basis of Embodiment 2, the steps of stress relief aging heat treatment are further determined;

[0070] The stress-relief aging heat treatment adopts a precise annealing method; the precise annealing method sequentially includes three decomposition steps of annealing, aging and annealing;

[0071] The annealing is: heating the decomposed component to 220-230°C (preferably 225°C) at a heating rate of 2-4°C / min (preferably 3°C / min) and keeping it for 11-13hr (preferably 12hr), then naturally cooling to room temperature ;

[0072] The aging is: heating the decomposed components to 150-160°C (preferably 155°C) at a heating rate of 0.75-1.25°C / min (preferably 1.00°C / min), and cooling to - 115~-125°C (-120°C) is preferred and maintained for 2hr±10min (preferably 2hr).

[0073] In the specific implementation process, the decomposed components are placed in a high-temperature furnace for the annealing and aging steps. In order to further ensure the ...

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Abstract

The invention discloses a method for making a space remote sensor bracket and the space remote sensor bracket, which are designed for solving the problems that an existing space remote sensor bracket made of a common aluminium alloy or titanium alloy material has poor performance and an aluminium-based composite material process cannot be used for making a large-scale three-dimensional component. The method for making the space remote sensor bracket comprises the following specific steps of: the step 1, by physical model analysis, decomposing the space remote sensor bracket which needs to be made into a plurality of decomposition components which meet the physical and mechanical characteristics required by the space remote sensor bracket; the step 2, processing an aluminium-based composite material blank and making the aluminium-based composite material blank into the decomposition components; and the step 3, combining and welding the made decomposition components into the required space remote sensor bracket by a tool, wherein aluminium-based composite material is ceramic-containing aluminium-based composite material. The space remote sensor bracket is a spliced structure formed by connecting a plurality of decomposition components made of the ceramic-containing aluminium-based composite material by a tool combining and welding method.

Description

technical field [0001] The invention relates to a manufacturing method of a space remote sensor support and the space remote sensor support. Background technique [0002] Ceramic-containing aluminum-based composite materials usually have low density formed by ceramic powder and metal materials, and have the advantages of low expansion, high stability of ceramic materials, low plasticity and good thermal conductivity of metal materials, so they are suitable for space remote sensing Aerospace equipment such as device brackets. [0003] The following three methods are usually used to prepare aluminum matrix composites: [0004] 1: Pressureless impregnation; [0005] 2: Pressure impregnation; [0006] 3: Powder metallurgy. [0007] The above three methods can produce high volume fraction (ceramic volume content above 40%) silicon carbide particle reinforced aluminum alloy composite materials, and all have very good physical properties, which are very suitable for the product...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B23P15/00F16M11/00F16M13/02
Inventor 李照东庞晓燕王子亮张洪立
Owner 浙江驰宇空天技术有限公司
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