Fusing type compression release mechanism and release method thereof

A release mechanism and fuse-type technology, applied in motor vehicles, aerospace equipment, space navigation equipment, etc., can solve the problems of high cost, large pressing force, and heavy weight of the pressing and releasing mechanism, and achieve low cost and high pressure. Small tightening force and weight reduction effect

Active Publication Date: 2015-09-09
SHANGHAI AEROSPACE SYST ENG INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0005] Aiming at the problems existing in the above-mentioned prior art, the present invention proposes a fuse-type compression release mechanism and its release method, which has a simple str

Method used

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  • Fusing type compression release mechanism and release method thereof
  • Fusing type compression release mechanism and release method thereof
  • Fusing type compression release mechanism and release method thereof

Examples

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Embodiment Construction

[0028] The following is a detailed description of the embodiments of the present invention. This embodiment is implemented on the premise of the technical solution of the present invention, and detailed implementation methods and specific operating procedures are provided, but the protection scope of the present invention is not limited to the following implementation example.

[0029] like figure 1 Shown is an exploded view of the fuse-type compression release mechanism of the present invention, which includes: an end cap 2 connected to a load-bearing rope 1 in sequence, a heater 3 , a fixing section 4 , a separating spring 5 and a separating section 6 . like figure 2 Shown is a schematic diagram of the compression state of the fuse type compression release mechanism of the present invention, as image 3 As shown in its cross-sectional view, the fixed section 4 is provided with a heater groove and a separation spring groove, which are respectively used to accommodate the h...

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Abstract

The invention discloses a fusing type compression release mechanism and a release method thereof, wherein the release mechanism comprises a bearing rope, a heater, a fixed section, a separate spring and a separate section; the fixed section, the separate spring and the separate section are sequentially connected to the bearing rope; the separate spring is in compression state; the heater is placed on the bearing rope; two ends of the bearing rope defines the prolapse of the fixed section and the separate section; the release method comprises following steps: S91: connecting a main body structure to the fixed section and connecting a separate body to the separate section; S92: powering the heater and fusing the bearing rope; and S93: ejecting the separate body to the outside with the separate section under the effect of the separate spring. The fusing type compression release mechanism and the release method thereof has the advantages of light weight, simple structure, low cost and high reliability of releasing.

Description

technical field [0001] The invention relates to a compression release device, in particular to a fusing type compression release mechanism and a release method thereof. Background technique [0002] With the rapid development of aerospace technology, the development of small-sized, high-performance, and lightweight micro-satellites has become one of the key development areas of international aerospace groups. The various structural products on micro-satellites, such as communication antennas, small expandable solar cell arrays, etc., need to be compressed in the retracted state so that the structure of the launching section will not be damaged. The structure can be expanded. [0003] The current separation of spacecraft, such as the separation of satellites and rockets, the separation of stars, the release of battery wings or antennas, all use explosive bolts and other separation devices that use explosives as cutting power. This separation device has the characteristics of...

Claims

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Application Information

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IPC IPC(8): B64G1/22B64G1/44B64G1/64
Inventor 侯建文王滢红刘大利吕亮亮彭福军马嘉
Owner SHANGHAI AEROSPACE SYST ENG INST
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