Small Satellite carrier

A carrier and satellite technology, which is applied in the aerospace field to achieve the effects of reduced scale, rapid response capability and less dead weight

Active Publication Date: 2018-12-18
BEIHANG UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The object of the present invention is to provide a kind of small satellite carrier, to solve the technical problem existing in the prior art

Method used

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Embodiment Construction

[0049] The technical solutions of the present invention will be clearly and completely described below in conjunction with the accompanying drawings. Apparently, the described embodiments are some of the embodiments of the present invention, but not all of them. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

[0050] In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer" etc. The indicated orientation or positional relationship is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the referred device or element must have a specific orientation, ...

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Abstract

The invention relates to the technical field of aerospace, in particular to a small satellite carrier. The utility model comprises a fairing cabin, three sub-cabins, two sub-cabins, two sub-cabins, one sub-cabin and a tail section which are serially connected in series. The power of the first sub-stage and the second sub-stage are both solid-liquid hybrid rocket motors, and the power of the thirdsub-stage is solid rocket motors. The small satellite carrier provided by the invention adopts a solid-liquid hybrid rocket engine for the power of the first sub-stage and the second sub-stage, the liquid oxidant is physically isolated from the solid fuel before ignition, the safety is high, and the maintenance cost is reduced; the solid-liquid hybrid rocket engine is used for the power of the first sub-stage and the second sub-stage. The third stage is powered by solid rocket motor with high mass ratio, low dead weight and the same payload, which effectively reduces the size of the small satellite carrier and improves the quick response capability. The small satellite carrier provided by the invention can ensure the commercial value and economic benefit, and also has the quick response ability.

Description

technical field [0001] The invention relates to the field of aerospace technology, in particular to a small satellite carrier. Background technique [0002] Small satellites have the advantages of small size, light weight, low cost, short development period, and fast and flexible launch methods. The number of small satellites launched accounts for more than half of the total number of satellite launches, and this proportion is still increasing. [0003] At present, in response to the requirements of small satellite launches, there is an urgent need for small satellite carriers with fast response capabilities, so as to achieve the purpose of preempting opportunities and quickly targeting in time, and while considering commercial value, it is necessary to pay more attention to its low-cost economy benefit. [0004] That is to say, how to ensure its commercial value and economic benefits while having rapid response capability is a technical problem that existing small satellit...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/40
CPCB64G1/403B64G1/404
Inventor 蔡国飙王鹏程李晓刚李承恩何凌飞于瑞鹏王中烁郭子豪
Owner BEIHANG UNIV
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