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triangle satellite configuration

A satellite configuration and triangular technology, which is applied to the power supply system of artificial satellites and aerospace vehicles, can solve the problems of high cost and long development cycle, and achieve the effects of low center of mass, saving launch costs, and mechanical stability

Active Publication Date: 2017-08-29
SHANGHAI SATELLITE ENG INST
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  • Abstract
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  • Claims
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Problems solved by technology

However, the cost of the invention is high and the development cycle is long

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Embodiment Construction

[0045] 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 modifications and improvements without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0046] In this example, if figure 1 , figure 2 , image 3 As shown, the triangular satellite configuration provided by the present invention includes a configuration body 5 and a solar cell array; the solar cell array is arranged on the outside of the configuration body; the configuration body includes a connected propulsion module and a service load cabin . The triangular satellite configuration provided by the present invention is triangular as a whole, and the interior is connected by a mod...

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Abstract

The invention provides a triangular satellite configuration comprising a configuration body and a solar battery array. The solar battery array is arranged on the outer side of the configuration body. The configuration body comprises a propulsion cabin and a service load cabin which are connected. The configuration body comprises a conical frame tube, a cylindrical frame tube, a start arrow butt joint ring and a triangular plate. The conical frame tube is connected with the cylindrical frame tube. The triangular plate is arranged between the conical frame tube and the cylindrical frame tube. The start arrow butt joint ring is arranged on the lower side of the periphery of the conical frame tube. The propulsion cabin is defined by the lower side face of the triangular plate, the conical frame tube and the start arrow butt joint ring. The service load cabin is defined by the upper side face of the triangular plate and the cylindrical frame tube. The invention further provides a corresponding system and an assembly method. By adoption of the integrated design concept, effective loads and a storage box are embedded into the configuration body of the satellite integrated configuration, the structure is compact, the center of mass is low, and inertia is small.

Description

technical field [0001] The invention relates to the overall design of a spacecraft, in particular to a triangular satellite configuration. Background technique [0002] At present, the general satellite configuration is complex, expensive, and has a long development cycle, which cannot meet the increasingly strong needs of users for low cost, fast response, and agile maneuvering. [0003] After searching the existing technology, it is found that the application number is 201310591599.6, and the patent name is a detachable micro-nano-satellite configuration. The invention discloses a detachable micro-nano-satellite configuration, which consists of a satellite body, a separate release satellite, a mechanical It is composed of net claws, flexible solar cell arrays, and variable-structure manipulators; the overall satellite configuration adopts a configuration in which the mother satellite carries multiple sub-satellites to realize the separation, release, and hovering functions...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/10B64G1/44
Inventor 毕振瀚袁金如李金岳李文峰
Owner SHANGHAI SATELLITE ENG INST
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