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A controllable self-protection small tether ejection release mechanism

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

Active Publication Date: 2022-06-24
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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  • A controllable self-protection small tether ejection release mechanism
  • A controllable self-protection small tether ejection release mechanism
  • A controllable self-protection small tether ejection release mechanism

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Experimental program
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Embodiment Construction

[0031] The present invention will be further explained below in conjunction with the accompanying drawings.

[0032] like figure 1 As shown, the present invention provides a controllable self-protection small tethered ejection release mechanism, including a satellite simulator 45, an ejection separation module, a tether cutting module, a tension control module, a spool base module and a base platform;

[0033] The satellite simulator 45 is provided with a guide cone 46, which is connected to the ejection separation module; the guide cone 46 includes an electromagnet. The spool base module extends out of the tether 44 to connect with the satellite simulator 45 . The tether 44 is preferably a Dyneema tether, which melts instantly when it hits the heating wire and can be more effective than conventional shearing

[0034] The ejection separation module is as Figure 2-3 As shown, it includes a butt cone 1, a damping rubber 2, a first fixing piece 3, a toothless gear 4, a first ...

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Abstract

The invention discloses a controllable self-protecting small tethered ejection release mechanism, which comprises a satellite simulator, an ejection separation module, a tether cutting module, a tension control module, a bobbin base module and a base platform, and can effectively simulate tethered satellites The entire release process of the star includes ejection separation, tension control, tether cutting, state measurement and buffering and vibration reduction; the unique ejection drive structure is adopted, which makes the ejection part smaller than the previous research, and the reliability performance is also significantly improved. When a special situation occurs, the electric heating material cutter in the tether cutting module can cut the tether faster and more effectively; the braking method adopted in the tension control module can control the tension of the tether more effectively and smoothly; the spool base module can effectively Non-contact detection of the length and speed of the tether, and at the same time, it can play a good role in buffering and damping at the end of the release.

Description

technical field [0001] The invention belongs to the technical field of space tethered satellite systems, in particular to a controllable self-protection small tethered ejection release mechanism. Background technique [0002] As a new type of space vehicle, tethered satellites have received extensive attention. The most critical issue is how to reliably release sub-satellites, which requires a complete set of reusable release mechanisms for ground physical simulation experiments. Researchers at home and abroad have carried out research on the tether release mechanism. In foreign research, Menon et al. designed the braking part of the release mechanism. Its operation mode is as follows: the worm is driven to drive the turbine to rotate, the tether inlet is designed on the turbine, and the number of turns of the tether is changed by the rotation of the turbine to make friction. force changes. Lorenzo et al. designed a release mechanism, which is controlled by electromagnetic...

Claims

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Application Information

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Patent Type & Authority Patents(China)
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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