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CubeSat Catapult and catapulting method applying same

A catapult and cube technology, which is applied in the direction of aircraft, aerospace aircraft, docking devices of aerospace aircraft, etc., to achieve the effect of ensuring performance, ensuring accuracy, and avoiding bumps

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

[0004] Based on this, it is necessary to provide a cube star catapult that can eject the cube star after the hatch is opened to a preset angle to avoid collisions in order to solve the problem that the surface of the star and the hatch are collided when the hatch is opened. , also provides a kind of ejection method that applies above-mentioned cube star catapult simultaneously

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

[0061] 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.

[0062] 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, biolo...

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Abstract

The invention provides a CubeSat catapult, comprising: a shell structure including a chamber body and a chamber cover, wherein the chamber body is internally provided with a catapulting guide rail; acatapulting structure used with the catapulting guide rail to carry and catapult a CubeSat; a locking structure for locking or unlocking the chamber cover and the chamber body; a chamber cover self-locking structure for locking the chamber cover opened to a preset angle; and a guide rail blocking structure that may extend out of or contract into the catapulting guide rail, wherein the chamber cover self-locking structure is linked with the guide rail blocking structure, the guide rail blocking structure contracts into the catapulting guide rail after the chamber cover self-locking structure locks the chamber cover, and the catapulting structure can slide along the catapulting guide rail and catapult the CubeSat. Therefore, the catapulting structure can only perform catapulting after the chamber cover is opened to a preset angle; collision between the CubeSat and the chamber cover is avoided, launching accuracy is guaranteed, and the CubeSat can be launched out of the chamber safely. The invention also provides a catapulting method of CubeSats.

Description

technical field [0001] The invention relates to the technical field of cube star launch, in particular to a cube star catapult and an ejection method thereof. Background technique [0002] The separation of traditional satellites and launch vehicles often adopts the combination of tape and explosive bolts. This separation technology is relatively mature and is widely used on large satellites. However, with the rapid development of cube stars and microsatellites, the advantages of cube stars lie in their small size, light weight and convenient launch. Due to the complexity, weight and high cost of traditional separation methods, it is difficult to reflect the advantages of pico-satellites. [0003] In the field of pico-satellites, more "cage" structures are adopted, that is, the star is installed in the "cage" of the separation mechanism, and the fire attack device is used as the device to open the hatch. The hatch is opened, and the star is ejected from the separation mec...

Claims

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Application Information

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Patent Type & Authority Applications(China)
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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