Controllable self-protection small tethered ejection releasing mechanism

A release mechanism and self-protection technology, applied in the field of space tethered satellite systems, to achieve effective smooth control, reduce impact, and improve reliability

Active Publication Date: 2020-07-24
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

It is not difficult to find that the tethered satellite release mechanism still has a lot of room for improvement

Method used

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  • Controllable self-protection small tethered ejection releasing mechanism
  • Controllable self-protection small tethered ejection releasing mechanism
  • Controllable self-protection small tethered ejection releasing mechanism

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Embodiment Construction

[0030] The present invention will be further explained below in conjunction with the accompanying drawings.

[0031] Such as figure 1 As shown, the present invention provides a controllable self-protection small tether ejection release mechanism, including a satellite simulator 45, an ejection separation module, a tether cutting module, a tension control module, a bobbin base module and a base platform;

[0032] A guide cone 46 is provided on the satellite simulator 45, and the guide cone is connected with the ejection separation module; the guide cone 46 includes an electromagnet. The spool base module protrudes from the tether 44 and is connected to the satellite simulator 45 . The tether 44 is preferably a Dyneema tether. This material will melt instantly when it encounters a heating wire, which can be more effective than traditional shearing. The ejection separation module is as follows: Figure 2-3 As shown, it includes docking cone 1, shock absorbing rubber 2, first fi...

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PUM

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Abstract

The invention discloses a controllable self-protection small tethered ejection releasing mechanism. The mechanism comprises a satellite simulator, an ejection separation module, a tether cut-off module, a tension control module, a spool base module and a base platform, and can effectively simulate the whole release process of tethered satellite sub-satellites, including ejection separation, tension control, tether cut-off, state measurement and buffer damping. A unique ejection driving structure is adopted, so that an ejection part is smaller and more exquisite than previously researched parts, meanwhile, the reliability is remarkably improved, and when a special situation occurs, an electric heating material cutter in the tether cut-off module can cut off a tether more quickly and more effectively; a braking mode adopted in the tension control module can more effectively and smoothly control the tension of the tether; and the spool base module can effectively carry out non-contact detection on the length and the speed of the tether, and can play a good role in buffering and damping at the tail end of the release end.

Description

technical field [0001] The invention belongs to the technical field of space tethered satellite systems, in particular to a controllable self-protecting small-sized tethered ejection release mechanism. Background technique [0002] As a new type of space vehicle, the tethered satellite has received widespread attention. The most critical issue is how to reliably release the sub-satellite, which requires a complete and reusable release mechanism for ground physical simulation experiments. Existing researchers at home and abroad have conducted research on the tether release mechanism. In foreign research, Menon et al. designed the braking part of the release mechanism. Its operation mode is: the worm drive drives the turbine to rotate, the tether inlet is designed on the turbine, and the turbine rotates to change the number of winding turns of the tether so that the friction force changes. Lorenzo et al. designed a release mechanism, which is controlled by electromagnetic fo...

Claims

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Application Information

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IPC IPC(8): B64G7/00B64G1/64
CPCB64G7/00B64G1/648
Inventor 余本嵩金栋平冯水良
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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