Box plate and frame combined type satellite configuration

A satellite configuration and combined technology, applied in the satellite field, can solve the problems of poor load adaptability, large structural weight and moment of inertia, and achieve the effect of small occupied space, customized requirements, and improved general performance.

Inactive Publication Date: 2021-10-29
北京微纳星空科技有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the load-bearing cylinder type usually needs to be redesigned due to changes in the size, weight and power consumption of the load; the closed box plate or frame structure will cause excessive structural weight and moment of inertia; the independent design of the platform requires part of the The extravehicular equipment is installed on the load, which has poor adaptability to the load

Method used

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  • Box plate and frame combined type satellite configuration
  • Box plate and frame combined type satellite configuration
  • Box plate and frame combined type satellite configuration

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Embodiment

[0064] This embodiment provides a box-board-frame combined satellite configuration; please refer to Figure 1-Figure 6 , figure 1 with figure 2 Schematic diagram of the structure of the box-board-frame combined satellite configuration provided for this embodiment, wherein, figure 1 The two unfolded sail panels are shown in the unfolded position, figure 2 The two unfolded sail panels are shown in their folded condition; image 3 Schematic diagram of the structure of the sailboard not shown, which is a box-board-frame combined satellite configuration, Figure 4 for image 3 Front view of the box-plate-frame combined satellite configuration shown, Figure 5 for Figure 4 A-A sectional view of the box-plate-frame combined satellite configuration shown, Image 6 It is a schematic structural diagram of the box-plate-frame combined satellite configuration, in which the two side plates of the platform box and the load plate are hidden.

[0065] The box-board-frame combined s...

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Abstract

The invention discloses a box plate and frame combined type satellite configuration, and relates to the technical field of satellites. The box plate and frame combined type satellite configuration comprises a platform cabin, a load cabin and a sailboard; the load cabin is located at the top of the platform cabin; the platform cabin comprises a platform box body and a platform frame structure; the load cabin comprises a load plate, a load frame structure and a load truss structure; the platform frame structure is arranged in the platform box body, the bottom of the platform frame structure is connected with the platform box body, and the top of the platform frame structure is connected with the load plate; the outer side face of the load frame structure is connected with the sailboard, and the inner side face of the load frame structure is connected with the load truss structure; the load frame structure and the load truss structure are both connected with the top of the load plate; and the bottom of the platform box body is connected with a butt joint ring. The invention aims to provide the box plate and frame combined type satellite configuration, so that the universal performance is improved to a certain extent, different customization requirements are met, and the box plate and frame combined type satellite configuration can be further suitable for satellites of various load types.

Description

technical field [0001] The invention relates to the technical field of satellites, in particular to a box-plate-frame combined satellite configuration. Background technique [0002] The satellite structure forms are divided into box-plate type, frame type and load-bearing cylinder type, etc.; the satellite structure in the prior art has the following schemes: scheme 1, adopt box-plate type or frame-type closed structure, and place the load in the cabin; scheme 2, platform Part of the independent design, the antenna, star sensor and other components are installed on the optical load to decouple from the load compartment; Option 3, adopt the center load-bearing cylinder-type satellite-borne integrated structure, install the platform equipment around the load-bearing cylinder, and the load itself Installed in the bearing cylinder. [0003] With the increasing number of satellite launch missions, payload customization and platform generalization of satellite structures have bec...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/10B64G1/22
CPCB64G1/10B64G1/1007B64G1/22
Inventor 刘断尘姜秀鹏高恩宇阎凯
Owner 北京微纳星空科技有限公司
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