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Napi satellite orbit deployer

A technology of satellite orbit and Napier, which is applied in the direction of aircraft, spaceflight vehicle, and guidance device of spaceflight vehicle, etc. It can solve the problem of not being able to meet the diverse needs of the Napier satellite on-orbit deployment tasks, not having a single load and multiple Fixed-point release and other issues, to achieve the effect of good scalability, simple structure, and flexible layout

Active Publication Date: 2017-03-29
国创机器人创新中心(哈尔滨)有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

At present, the Napi satellite orbit deployer developed at home and abroad only has the function of single load and single full release, that is, it does not have the function of single load and multiple fixed-point release, which cannot meet the requirements of the Napi satellite on-orbit deployment task. diversity needs

Method used

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Embodiment Construction

[0036] The above and other technical features and advantages of the present invention will be described in more detail below in conjunction with the accompanying drawings.

[0037] Such as figure 1 , figure 2 and Figure 6 As shown, it is a structural schematic diagram of a Napi satellite orbit deployer, which includes: a body, a cover unlocking mechanism 11 , a separation ejection mechanism and a limit release mechanism 15 . The main body is used to carry the Napi satellite; the lid unlocking mechanism 11 is used to control the locking and unlocking of the lid; the separation and ejection mechanism is used to push the Napi satellite to separate from the main body at a constant speed; the limit release mechanism 15. It is used to limit and release the Napi satellite. The body includes a box cover assembly, a box body assembly and a cover 8. The box cover unlocking mechanism 11 is arranged on the body. The limit release mechanism 15 is located at the upper position of the b...

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Abstract

The invention provides a Napi satellite orbit deployer which is characterized by comprising a body, a box cover unlocking mechanism, a separation catapulting mechanism and a limiting release mechanism, wherein the body is used for bearing Napi satellites; the box cover unlocking mechanism is used for controlling locking and unlocking of a box cover; the separation catapulting mechanism is used for pushing the Napi satellites to be rapidly separated from the body; and the limiting release mechanism is used for limiting and releasing the Napi satellites. Compared with the prior art, through cooperative use of the separation catapulting mechanism of a separation spring set and the limiting release mechanism made of memory alloy material, the functions of single-time bearing and multiple times of attitude determination release of the Napi satellite orbit deployer are realized, the size and mass of the deployer and energy consumption are reduced, the advantage of low impact during the release process is realized, and excellent extensibility is also realized; and in addition, the limiting release mechanism is simple in structure, low in energy consumption, small in impact and flexible in arrangement mode.

Description

technical field [0001] The invention relates to the field of aerospace equipment, in particular to a Napi satellite orbit deployer. Background technique [0002] Picosatellites and nanosatellites refer to satellites with masses between 0.1kg and 1kg and 1kg and 10kg respectively. With the development of space technology and the diversification of missions in the future, Napi satellites with different functional characteristics can be combined in a certain number of modules for on-orbit formation flight, companion flight observation, and participation in constellation construction. In order to meet the established mission requirements, it is necessary to develop a specific Napi satellite orbit deployer. This deployer has the function of carrying multiple Napi satellites during the launch process and releasing the Napi satellites after reaching the predetermined orbit. At present, the Napi satellite orbit deployer developed at home and abroad only has the function of single l...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/64B64G1/24
CPCB64G1/242B64G1/645
Inventor 岳洪浩屠其晨杨飞邓宗全宋连杰
Owner 国创机器人创新中心(哈尔滨)有限公司
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