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Method for manufacturing memory alloy spacecraft unlocking drive element

A technology of driving components and memory alloys, which is applied to space navigation equipment, space navigation vehicles, aircraft, etc., can solve the problems of not meeting the requirements of large displacement, large thrust, small elongation, and large restoring force. The effect of batch consistency, stable recovery force and recovery strain performance, and convenient loading and unloading

Active Publication Date: 2013-10-09
西安赛特新材料科技股份有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The purpose of the present invention is to provide a manufacturing method of memory alloy spacecraft unlocking drive elements, which solves the problem that the existing drive elements have large restoring force but small elongation and cannot meet the requirements of large displacement and large thrust

Method used

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  • Method for manufacturing memory alloy spacecraft unlocking drive element

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0044] (1) The raw material prepared with Ti-49.2% (at) Ni binary composition is prepared by casting, forging and rolling into a Ф10㎜ bar, which is machined after heat treatment to make a diameter and length of Ф7.78 0 -0.036 ㎜×84.5±0.1㎜ component blank. Mf=23.8°C Ms=49.2°C As=81.15°C Af=104.5°C of the alloy element.

[0045] (2) Make attached figure 1For the mold shown, the height of the center hole of the mold is 76mm, and the diameter of the center hole is Ф8 0 -0.036 mm.

[0046] (3) Put the component blank with a diameter of Ф7.78 and the mold into the refrigerator to cool at -20°C for 40 minutes.

[0047] (4) Put the ice cubes made at minus 20°C in a plastic bag between the two indenters of the press that is in contact with the component blank, and cool the indenters for 10 minutes.

[0048] (5) attached figure 1 Quickly assemble the mold, put the element blank into the mold hole, quickly remove the cooling bag, and put the mold filled with the drive element blank...

Embodiment 2

[0053] Raw materials prepared with Ti-49.8% (at) Ni% binary components, Ф10㎜ bars prepared by casting, forging and rolling, and machined after heat treatment to make diameter and length Ф7.78 0 -0.036 ㎜×42.25±0.1㎜ two component blanks. Mf=20.2°C, Ms=52.3°C, As=63.8°C, Af=92.9°C of the alloy element.

[0054] (1) Make attached figure 1 For the mold shown, the height of the center hole of the mold is 76mm, and the diameter of the center hole is Ф8 0 -0.036 mm.

[0055] (2) Repeat steps (2)-(5) of Example 1, and put the two blanks into the center hole of the mold at the same time.

[0056] (3) Press the billet to 7.2% at a rate of 1.0mm / min and unload it. Take out the mold and drive components, loosen the clamp screws, and take out the drive components.

[0057] (4) The drive element specification is Ф8×39.95㎜. Recovery stressб r ﹦381MPa, elongation ΔL﹦1.91mm, recovery strain ε﹦4.51%.

[0058] (5) The combined length (or height) of the driving elements is 79.9mm, and th...

Embodiment 3

[0060] (1) Using Ti-47.2% (at) Ni-10% (at) Zr-2% (at) Cu quaternary components as raw materials, Ф10㎜ bars prepared by casting, forging, rolling, after heat treatment Machined to make diameter and length Ф7.78 0 -0.036 ㎜×28.33±0.1㎜ three component blanks. Mf=37.5°C Ms=61.3°C As=112.3°C Af=135.5°C of the alloy element.

[0061] (2) Make attached figure 1 For the mold shown, the height of the center hole of the mold is 76mm, and the diameter of the center hole is Ф8 0 -0.036 mm.

[0062] (3) Repeat steps (2)-(5) of Example 1, and put three blanks into the center hole of the mold at the same time.

[0063] (4) Press the billet to 7.5% at a rate of 0.5 mm / min and then unload it. Take out the mold, loosen the clamp screw, and take out the drive element.

[0064] (5) The drive element specification is Ф8×26.65㎜. Recovery stressб r ﹦410MPa, elongation ΔL﹦1.22mm, recovery strain ε﹦4.63%.

[0065] (6) The combined length (or height) of the driving elements is 79.95mm, and th...

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Abstract

The invention discloses a method for manufacturing a memory alloy spacecraft unlocking drive element. The method comprises the following steps of: cooling a drive element blank and a mold to be below a phase transformation point Mf of a drive element material; pressing the drive element blank in the mold, thus obtaining the spacecraft unlocking drive element. The mold comprises an upper pressing plate, a lower pressing plate, and a clamp, wherein a central hole is formed between the upper pressing plate and the lower pressing plate and is used for accommodating the drive element blank; positioning tanks or positioning tables are respectively arranged on the upper pressing plate and the lower pressing plate for matched positioning. The manufacturing method refers to manufacturing the drive element by compressing a high-precision shape memory alloy bar billet in a detachable mold, and is simple, feasible, convenient in detachment and low in preparation cost; one-step preparation of multiple elements with the axis ratio of less than 5 (the ratio of the length to diameter is less than or equal to 5) can be realized. The drive element prepared by the manufacturing method is uniform in deformation, high in dimensional accuracy and high in drive resilience and recovery strain.

Description

technical field [0001] The invention belongs to the technical field of manufacturing components of spacecraft equipment, and relates to a manufacturing method of a TiNi shape memory alloy spacecraft unlocking driving component. Background technique [0002] In the field of aerospace, due to the special environment, after the rocket takes the spacecraft into space, the battery panels and communication antenna devices of the spacecraft need to be unlocked and opened to work. Components for a key unlocking device of an aerospace vehicle are required to have a large thrust (under the condition of 2.4 mm displacement, maintain 8 kN force) and a large displacement (greater than 3.2 mm) to meet the needs. Due to the special environment where the spacecraft is located, the traditional mechanical method cannot be used due to its large size and complicated mechanism. At present, most spacecraft unlocking devices adopt the method of explosion unlocking, which causes vibration to the s...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C22F1/10C22F1/16C22C19/03C22C30/02B64G1/22
Inventor 王卫民罗斌莉陈文龙杨华斌牛忠杰薛飒樊梦婷
Owner 西安赛特新材料科技股份有限公司
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