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Space Tether System Deployment Control Mechanism Ground Test Device

A technology of a space tether system and a control mechanism, which is applied in the aerospace field, can solve problems such as simulation simulation of a control mechanism without considering the deployment of the tether, and achieve the effects of simple structure, low cost and easy realization.

Active Publication Date: 2017-09-12
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, there are still deficiencies. Due to the space limitation of the ground test system, the maximum length of the tether deployment is only 3m, and the simulation of the work of the tether deployment control mechanism is not considered. However, the tether length of the actual space tether system can reach several ten kilometers

Method used

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  • Space Tether System Deployment Control Mechanism Ground Test Device
  • Space Tether System Deployment Control Mechanism Ground Test Device
  • Space Tether System Deployment Control Mechanism Ground Test Device

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Embodiment Construction

[0022] The structural principle and working principle of the present invention will be further described in detail below in conjunction with the accompanying drawings.

[0023] According to figure 1 , figure 2 , image 3 , Figure 4 , a space tether system deployment control mechanism ground test device, including a base 1, the base 1 is provided with a pay-off mechanism; the right side of the servo motor A2 is provided with a guide wheel 5; the right side of the guide wheel 5 is provided with a deployment control mechanism; the right side of the expansion control mechanism is provided with a tension measuring mechanism; the right side of the tension measuring mechanism is provided with a speed measuring device; the right side of the speed measuring device is provided with a take-up mechanism; the display panel 13 is connected with the speed measuring device and the strain sensor.

[0024] The pay-off mechanism includes a servo motor A2, a pay-off wheel 3, a guide wheel 5 ...

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Abstract

The invention discloses a ground testing device for an unfolding control mechanism of a space tied rope system. The ground testing device comprises a base, a rope unwinding mechanism, the unfolding control mechanism, a tension measuring mechanism, a speed measuring device, a rope winding mechanism and a display panel are arranged on the base, the rope unwinding mechanism, the unfolding control mechanism and the tension measuring mechanism complete tensioning and releasing of a tied rope on a base station spacecraft, the unfolding speed and the unfolding tension of the tied rope are changed by changing the friction force between the tied rope and a turbine shaft to control the unfolding process of the space tied rope system, and the speed measuring device, the rope winding mechanism and the display panel achieve the functions of measuring the tied rope speed, recycling the tied rope and setting and displaying parameters. The ground testing device has the advantages of being simple in structure, low in cost and suitable for the tied rope as long as 1 Km.

Description

technical field [0001] The invention belongs to the field of aerospace technology, in particular to a ground test device for a space tether system deployment control mechanism. Background technique [0002] The space tether system is a new type of space vehicle formed by connecting a small spacecraft with a base station spacecraft through a tether, and it is a very promising development direction of space science. It has broad application prospects in near-Earth space and deep space exploration, such as microgravity generation, satellite attitude stabilization, spacecraft launch and orbit transfer, tether-assisted spacecraft reentry, tether rendezvous and capture systems, and space debris removal. In addition to earth observation and deep space exploration. In the research and application of the space tether system, the deployment control mechanism of the tether system is the main component to realize the precise release of the tether from the base station spacecraft accord...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01L5/04B64G1/64
Inventor 王长青杜崇刚李爱军吴佳楠王鑫王盼冰
Owner NORTHWESTERN POLYTECHNICAL UNIV
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