Configuration of satellite loaded with large deployable antenna with double reflecting surfaces

A dual-reflector, satellite configuration technology, used in transportation and packaging, space navigation equipment, space navigation aircraft, etc., can solve the problems of satellite weight, envelope size restrictions, etc., and achieve wide application and promotion value and structural stability. , the effect of high precision requirements

Active Publication Date: 2016-04-20
SHANGHAI SATELLITE ENG INST
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AI Technical Summary

Problems solved by technology

[0004] As a big aerospace country, my country's satellite industry is in a period of vigorous development, and the demand for satellites that can be loaded with large-caliber and large-scale deployable antennas is becoming more and more urgent. However, due to the constraints of the launch vehicle fairing, loading a large-scale deployable There are strict restrictions on the envelope size and so on. The above factors have put forward strict restrictions on the layout design of the satellite configuration of the large-scale deployable antenna equipped with double reflectors.

Method used

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  • Configuration of satellite loaded with large deployable antenna with double reflecting surfaces
  • Configuration of satellite loaded with large deployable antenna with double reflecting surfaces

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Embodiment Construction

[0029] The present invention will be described in detail below in conjunction with specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but do not limit the present invention in any form. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0030] Aiming at the large-scale expandable parabolic antenna of the "feed array + double reflector antenna" system, the present invention provides a fully utilized envelope space, large cell area, fully optimized use of space and reasonable assembly to meet the requirements of "feed array + The large-scale deployable parabolic dish antenna of the dual-reflector antenna system is the satellite configuration required for the retraction and on-orbit deployment.

[0031] The invention provides a satellite ...

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Abstract

The invention provides configuration of a satellite loaded with a large deployable antenna with double reflecting surfaces. The relative position relation of a feed source array, a main reflecting surface and an auxiliary reflecting surface in an in-orbit flight state is guaranteed, main force transfer path design is optimized through design of a payload capsule in a truss structure style and reasonable layout and placement while the constraint conditions about enveloping of a fairing of a carrier rocket and correct deployment of the large deployable antenna are met, compactness and reasonableness of structure space of the large deployable antenna in a folded state can be guaranteed, meanwhile, the deploy path requirement of the large deployable antenna is met, and the area of a satellite solar cell array is guaranteed by fully using the enveloping space provided by the carrier rocket.

Description

technical field [0001] The invention relates to the field of satellite technology in aerospace technology, in particular to a satellite configuration equipped with a large-scale deployable antenna with double reflectors. Background technique [0002] According to the configuration design experience of existing satellites, such as optical satellite cameras, electronic reconnaissance satellite antennas, and communication satellite large-scale reflector antennas are directly installed on the satellite platform as satellite payload components to maintain their working conditions. On-orbit flight is basically the same as on the ground, but the configuration design technology of satellites with large deployable antennas is quite different. Due to the large size of the large deployable antenna, which is far beyond the allowable range of the envelope of the launch vehicle's fairing, it needs to be folded within the allowable envelope of the launch vehicle's fairing through configura...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/66
CPCB64G1/222B64G1/66
Inventor 陈汀陈国忠徐增
Owner SHANGHAI SATELLITE ENG INST
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