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Foldable separated satellite platform and assembling and use method thereof

A satellite platform, a separate technology, applied in the field of satellite platforms, can solve the problem of large-aperture long-focus optical satellite centroid offset, etc., to achieve the effect of facilitating design, smooth optical path, and reducing the centroid of the whole star

Inactive Publication Date: 2019-11-15
SHANGHAI SATELLITE ENG INST
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  • Abstract
  • Description
  • Claims
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Problems solved by technology

This remote sensing micro-satellite does not solve the problems of large-aperture and long-focus optical satellite centroid offset

Method used

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  • Foldable separated satellite platform and assembling and use method thereof
  • Foldable separated satellite platform and assembling and use method thereof
  • Foldable separated satellite platform and assembling and use method thereof

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Embodiment Construction

[0028] 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.

[0029] The expandable and separate satellite platform of the present invention solves the problem of satellite centroid offset, reduces the interference of light pressure moment, effectively suppresses the influence of flexibility and the coupling effect of inertia product, and ensures that the satellite can achieve high precision and high precision in orbit. The stable flight state is suitable for large-aperture and long-focus optical satellites. It solves the problems of excessive satellite inertia and...

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Abstract

The invention provides a foldable separated satellite platform. The foldable separated satellite platform comprises a first satellite sub-platform, a second satellite sub-platform and a third satellite sub-platform. The first satellite sub-platform, the second satellite sub-platform and the third satellite sub-platform are connected through extensible assemblies. During launching, the three satellite sub-platforms are closed to form the whole satellite platform, and the extensible assemblies are contracted. After a satellite enters an orbit, the first satellite sub-platform, the second satellite sub-platform and the third satellite sub-platform are unfolded and connected through the extensible assemblies, and the extensible assemblies are stretched. The foldable separated satellite platform is suitable for a large-caliber long-focus optical satellite, the problems that after the whole satellite enters the orbit, the satellite inertia is too large, and the mass center of the whole satellite deviates out of the satellite body are solved, and satellite control system design is benefited.

Description

technical field [0001] The invention relates to the technical field of spacecraft equipment, in particular to a deployable and detachable satellite platform. Background technique [0002] With the improvement of the ground resolution of geostationary orbit satellites, the aperture of the remote sensing payload is getting larger and larger. When the geostationary orbit achieves 1-2m resolution to observe the earth, the aperture of the film camera optical system used is about 20m, which is limited by the capability of the launch vehicle. Restrictions, the payload needs to be folded for launch, and the payload is unfolded after the satellite enters orbit. [0003] Traditional payloads and satellite platforms adopt a docking installation method, that is, the payload is directly installed on the platform and connected through electronic and mechanical interfaces. If a traditional satellite platform is used, the primary and secondary mirrors of the thin-film optical camera are in...

Claims

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Application Information

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IPC IPC(8): B64G1/10B64G1/22
CPCB64G1/10B64G1/22B64G1/222
Inventor 许浩李文龙孔祥龙杨丽丽刘刚钱勇陈昌亚
Owner SHANGHAI SATELLITE ENG INST
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