CubeSat Catapult and catapulting method applying same

A catapult and cube technology, applied in the field of satellite launch, can solve the problems of cube star damage and versatility, achieve great lateral stability, make full use of resources, and avoid damage

Pending Publication Date: 2018-04-20
星际漫步(北京)航天科技有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] Based on this, it is necessary to provide a safe separation of cubesats, avoiding damage, and capable of ejecting various sizes for the problems of cubesat damage caused by the explosion of the...

Method used

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  • CubeSat Catapult and catapulting method applying same
  • CubeSat Catapult and catapulting method applying same
  • CubeSat Catapult and catapulting method applying same

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Embodiment Construction

[0066] In order to make the purpose, technical solution and advantages of the present invention clearer, the cube star catapult and its ejection method of the present invention will be further described in detail through the following embodiments in conjunction with the accompanying drawings. It should be understood that the specific embodiments described here are only used to explain the present invention, not to limit the present invention.

[0067] see figure 1 , the present invention provides a cube star catapult 100, the cube star catapult 100 is used to eject the cube star, so that the cube star is ejected out of the cabin, for the university to carry out aerospace science research and education, for the ocean, atmospheric environment It has the characteristics of low cost, high functional density, short development cycle, and fast entry into orbit for monitoring and communication of ships, aviation vehicles, etc., space imaging, communication, atmospheric research, biol...

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Abstract

The invention provides a CubeSat catapult, comprising: a shell structure including a chamber body, a chamber cover and a combination plate, wherein the combination plate can divide the chamber body into a plurality of catapulting channels, and a catapulting guide rail is arranged in the chamber body; a plurality of catapulting structures, wherein each catapulting structure includes a spiral springand a catapulting carrier plate, the catapulting carrier plates are used for bearing a CubeSat and can slide along the catapulting guide rail, and the section of each spiral spring is in polygonal shape; and a locking structure arranged on the shell structure and used for locking or unlocking the chamber cover and the chamber body, wherein after the locking structure unlocks the chamber cover andthe chamber body and the chamber cover opens to a preset angle, the spiral springs drive the catapulting carrier plates to slide along the catapulting guide rail to catapult the CubeSat. The CubeSatcatapult is capable of catapulting CubeSats of various sizes at the premise of avoiding damage to the CubeSats and is more universal. The invention also provides a catapulting method of CubeSats.

Description

technical field [0001] The invention relates to the technical field of satellite launch, in particular to a CubeSat catapult and an catapult method thereof. Background technique [0002] The separation of traditional satellites and launch vehicles often adopts the combination of tape and explosive bolts. This kind of separation technology is relatively mature and is widely used on large satellites. However, the fire attack device may produce fine particles at the moment of explosion. After these fine particles enter the satellite, if the optical lens and so on, it will cause great damage to the satellite's components. In addition, the explosion impact force of the explosion bolt may affect the release of the cube star. The current release of cubesats below 12U usually uses a special catapult to realize the in-orbit release of the satellite, which is extremely poor in versatility. In addition, the catapult for 12U is mainly imported or uses the same release method as the sma...

Claims

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Application Information

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IPC IPC(8): B64G1/64
CPCB64G1/645
Inventor 吴前进
Owner 星际漫步(北京)航天科技有限公司
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