Cubesat brake sail de-orbit device

A technology of cube satellites and brake sails, which is applied in the field of spacecraft deorbiting, can solve the problems of space debris affecting the normal operation of other satellites, and achieve the effects of reducing the difficulty of ground control, strong anti-vibration ability, and good integrity

Active Publication Date: 2016-07-27
NANJING UNIV OF SCI & TECH
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  • Summary
  • Abstract
  • Description
  • Claims
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Problems solved by technology

[0008] The object of the present invention is to provide a cube satellite braking sail deorbiting device, which is suitable for deorbiting cube satellites with small volume and light weight, and solves the problem that the cube satellite cannot be deorbited within a specified time after completing the task and thus becomes space debris. Problems with normal operation of other satellites

Method used

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  • Cubesat brake sail de-orbit device
  • Cubesat brake sail de-orbit device
  • Cubesat brake sail de-orbit device

Examples

Experimental program
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Embodiment

[0063] Embodiment: Taking a three-unit cube star as an example

[0064] combine Figure 1~Figure 11 , a CubeSat braking sail deorbiting device whose size occupies the space of the entire CubeSat 1U (10cm*10cm*10cm). Consists of two identical CubeSat brakesail de-orbit subassemblies. CubeSat brake sail derailment sub-device is made up of derailment device 28 and the dividing plate 27 that is arranged on the top of derailment device 28.

[0065] The off-track device 28 is a center-symmetrical structure, including a main frame 5, an upper end cover 6, a sail storage room guide rail 2, a Hall sensor, a base plate 25 and two deployment mechanisms, and the main frame 5 is Z-shaped, with the center of the main frame 5 as The center of symmetry divides the main frame 5 into two identical sub-chambers 1, and the two deployment mechanisms are respectively arranged in the two sub-chambers 1.

[0066] The sub-chamber 1 of the main frame 5 is divided into an inner cavity and an outer ca...

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Abstract

The invention discloses a cubesat brake sail de-orbit device. The cubesat brake sail de-orbit device is composed of two completely identical cubesat brake sail de-orbit sub-devices. Each cubesat brake sail de-orbit sub-device comprises a de-orbit device body and a partition board arranged on the top of the de-orbit device body, wherein the de-orbit device body is of a central symmetry structure and comprises a main frame, an upper end cover, a sail storage chamber guide rail, a Hall sensor, a base plate and two expanding mechanisms, the main frame is Z-shaped, the main frame is divided into two identical chambers with the center of the main frame as the symmetry center, and the two expanding mechanisms are arranged in the two chambers respectively. Four film sails are expanded in four directions by means of tape spring masts to increase the normal sectional area of satellite movement, so as to successfully solve the problem that a cubesat stays on the original track for a long time after fulfilling a task and becomes space debris.

Description

technical field [0001] The invention belongs to the field of spacecraft de-orbiting, and in particular relates to a cube satellite braking sail de-orbiting device. Background technique [0002] In recent years, with the rapid development and great achievements of human space technology, human space activities have also produced a large number of space debris (also known as space junk). The existence of space debris seriously threatens the safety of spacecraft in orbit and restricts the development of human space technology. How to slow down the growth of space debris has become an urgent problem at home and abroad. The Inter-Agency Space Debris Coordination Committee (IADC) recommends that if a satellite cannot reorient to a graveyard orbit, it should be able to de-orbit itself within 25 years after completing its mission or within 30 years after launch, and enter the dense atmosphere to burn up. [0003] CubeSat has gradually become a research hotspot at home and abroad b...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/62B64G1/00
CPCB64G1/62B64G1/2427
Inventor 梁振华曾玉堂张翔廖文和莫乾坤于永军郑侃
Owner NANJING UNIV OF SCI & TECH
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