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
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  • Description
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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 cube star catapult, comprising: a shell structure, including a cabin and a hatch cover; the cabin has an ejection guide rail; the ejection structure cooperates with the ejection guide rail, and is used to carry and eject the cube star ; the locking structure is used to lock or unlock the hatch cover and the cabin body; the hatch cover self-locking structure is used to lock the hatch cover opened to a preset angle; and the locking structure of the guide rail can be extended or retracted. Back to the ejection guide rail, the hatch cover self-locking structure is linked with the guide rail locking structure; after the hatch cover self-locking structure locks the hatch cover, the guide rail locking structure retracts the ejection guide rail, so The ejection structure can slide along the ejection guide rail and eject the cube star. In this way, the ejection structure can only be ejected after the hatch is opened to a preset angle, so as to avoid collision between the CubeSat and the hatch, ensure the accuracy of launch, and make the CubeSat safely out of the cabin. The invention also provides a method for ejecting the cube star.

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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