An all-in-one satellite with a compact layout

A satellite and layout technology, applied in the aerospace field, can solve the problems of high requirements for satellite design, low utilization of space utilization of bearing tube structure, and poor adaptability of small and medium satellites.

Inactive Publication Date: 2017-10-27
SHANGHAI ENG CENT FOR MICROSATELLITES
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  • Abstract
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Problems solved by technology

[0003] The above five structural forms have their own shortcomings: the space utilization rate of the bearing tube structure is low, and the adaptability to small and medium satellites is poor; the structure of the truss structure is complex, the resource utilization rate is low, and the configuration layout is limited; the frame panel structure has limited bearing capacity. , the total mass of the satellite is mostly within 1000kg; the load capacity of the plate frame structure is weak, and the total mass of the satellite is mostly within 500kg; the cage structure has high requirements for the comprehensive design level of the satellite

Method used

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  • An all-in-one satellite with a compact layout
  • An all-in-one satellite with a compact layout
  • An all-in-one satellite with a compact layout

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Embodiment Construction

[0022] The specific implementation of a compact layout integrated satellite provided by the present invention will be described in detail below in conjunction with the accompanying drawings.

[0023] attached figure 1 Shown is a schematic structural diagram of the satellite described in this specific embodiment, with figure 2 is attached figure 1 Exploded view of the structure shown. Reference attached figure 1 And attached figure 2 As shown, the satellite includes a lower skirt 10 , a bottom plate 11 , a mounting flange 12 , a bulkhead 13 and a top plate 14 . The lower satellite skirt 10 is arranged on the lower surface of the bottom plate 11 , and the mounting flange is arranged on the upper surface opposite to the lower surface of the bottom plate 11 . Separators 13 are respectively arranged on the four diagonal corners of the upper surface. The four partitions 13 are arranged around the mounting flange 12 on the upper surface and support the top plate 14 .

[0024...

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Abstract

The present invention provides an integrated satellite with a compact layout, which includes a bottom plate, and a mounting flange is arranged on the surface of the bottom plate, and the mounting flange is used to set up the on-satellite load equipment, thereby forming a first line for the on-satellite load equipment. Force transmission path; the surface of the bottom plate is further provided with a baffle on each of the four diagonal corners, and the four baffles support a top plate, and the top plate is used to set the extraterrestrial load equipment, thereby forming a pair of extraterrestrial load equipment the second force transmission path. The advantage of the present invention is that it proposes a load-centered integrated satellite configuration, realizes a layout around the load, and designs a structural scheme in which two main force transmission paths and one secondary force transmission path work together , realize the optimization of the mechanical environment of the load, reduce the complexity and pressure of the design of the satellite structure and load structure, and improve the bearing ratio of the satellite structure.

Description

technical field [0001] The invention relates to the field of aerospace technology, in particular to an integrated satellite with a compact layout. Background technique [0002] At present, satellite configurations at home and abroad mainly adopt the following five structural forms: load-bearing tube structure, truss structure, frame panel structure, plate frame structure, and cage structure. The load-bearing tube structure has a large bearing capacity and is easy to arrange large storage tanks. Its typical application models include the French SPOT series, Dong 3 platform, and Dong 4 platform; the truss structure has strong scalability and adaptability, and its typical application models include the American TIROS platform and MMS platform; the frame and panel structure is flexible in disassembly and assembly, good in openness, easy to integrate, and universal in design. The manufacturing cost is low, and its typical application model is CAST platform; the cage structure is...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/10
Inventor 诸成张文巧李华旺朱振才王建平陈博常亮宋炜胥何涛刘瑞吉彦超
Owner SHANGHAI ENG CENT FOR MICROSATELLITES
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