A configuration design of micro-satellites adapting to the launch of multiple satellites in a cylindrical fairing space

Abstract

The present invention provides a micro-satellite configuration design suitable for launch of multiple satellites with one arrow in the space of a cylindrical fairing, including: a fairing, a satellite main body, and a facet; the overall appearance of the fairing is cylindrical, and the satellite main body is embedded Installed inside the fairing; the facet is located on one side of the satellite main body; the fixed solar wing is installed on the rear side of the satellite main body through a bracket; the unfolded solar wing is installed on both sides of the satellite main body through a hinge; the The ground load is fixedly installed on the top of the satellite main body; the invention has the advantages of reasonable structural design and reasonable space design through the improvement of the micro-satellite configuration design adapted to the cylindrical fairing space launch of multiple satellites, and solves the problem of satellite main body and rectification. The problem of low utilization of cover space is adapted to the launch requirements of multiple satellites in one rocket, and satisfies the advantages of satellite centroid error requirements when satellites and rockets are separated, thereby effectively solving the problems and deficiencies proposed by the present invention.

Description

technical field [0001] The invention relates to the technical field of satellite configuration design and structure design, and more specifically, relates to a configuration design of micro-satellites suitable for launching multiple satellites with one arrow in a cylindrical fairing space. Background technique [0002] The satellite is launched into space by a carrier rocket, and the installation position of the satellite in the carrier rocket is inside the fairing of the rocket, and the space inside the fairing of the carrier rocket is usually cylindrical. [0003] In the context of satellite miniaturization and integration, constellations and multi-satellite networking missions bring more and more demand for multi-satellite launches with one rocket. Requirements, the configuration of the satellite is required to better match the cylindrical space inside the launch vehicle fairing. [0004] The common configurations of existing satellites are mostly cubes, polygonal cylind...

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Problems solved by technology

[0004] The common configurations of existing satellites are mostly cubes, polygonal cylinders or cylinders. The cube configuration is more adaptable to the equipment in the satellite, but there is a large gap between the outer side of the satellite and the rocket fairing; the polygonal cylinder or cylinder In the single-satellite launch state, the three-body satellite can adapt more to the space between the satellite and the fairing, but the space between the satellite and the satellite is greatly wasted during the multi-satellite launch, and due to the limitation of the outer envelope shape, it is not conducive to the deployment of the solar wing. layout design of

[0005] There are also some satellite configuration designs aimed at multiple satellites with one rocket, such as the wall-mounted satellite configuration of the center load-bearing tube in the rocket, which makes full use of the annular space between the load-bearing tube and the fairing, but the load-bearing tube itself occupies a certain amount of space. space, the overall space utilization in the fairing is still insufficient

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