One-rocket multi-satellite self-series launching structure of small high-orbit satellite

Abstract

The invention provides a one-rocket multi-satellite self-series launching structure of a small high-orbit satellite. The structure comprises a plurality of series modules, wherein each series module comprises a force bearing cylinder and a cabin body, and the series modules are directly connected with the first end face of the force bearing cylinder of the next series module through the second endface of the force bearing cylinder of the previous series module to form a multi-satellite self-series combination body; and multiple force bearing cylinders, wherein the column sections of the forcebearing cylinders have the same diameter, the column section of at least one force bearing cylinder protrudes out of the-Z direction of the cabin body, and the column section of at least one force bearing cylinder protrudes out of the + Z direction of the cabin body.

Description

technical field [0001] The invention relates to the field of aerospace technology, in particular to a self-tandem launching structure of one rocket and multiple satellites for small high-orbit satellites. Background technique [0002] In order to save launch and development costs, it has become more and more common for medium and high orbit satellites to launch multiple satellites with one rocket. There are three main configurations for multiple satellites with one rocket. One is multi-satellite parallel connection, such as Beidou navigation MEO satellite; the other is rocket Internal support, such as Beidou navigation satellite; one is self-serial multi-satellite, such as ABS-3A, Eutelsat 115West B launched by Boeing BSS-702SP; ABS-2B, Eutelsat 117 West B and other satellites. [0003] Under the constraints of load type, quantity and volume, it is difficult to realize the parallel launch configuration of medium and high orbit satellites, especially high orbit communication ...

AI Technical Summary

Problems solved by technology

[0004] The purpose of the present invention is to provide a self-tandem launch structure of one rocket and multiple satellites for small high-orbit satellites, so as to solve the problems of flexible configuration, high cost performance and high reliability of the existing small high-orbit satellites.

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