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Integration satellite compact in layout

A satellite and layout technology, applied in the aerospace field, can solve problems such as low resource utilization, limited configuration and layout, and weak load-carrying capacity of the plate-frame structure.

Inactive Publication Date: 2016-01-13
SHANGHAI ENG CENT FOR MICROSATELLITES
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AI Technical Summary

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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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 invention provides an integrated satellite compact in layout. The integrated satellite comprises a bottom plate, and a mounting flange is arranged on the surface of the bottom plate; the mounting flange is used for arranging of an inner-satellite load device, and therefore a first force transmission path for the inner-satellite load device is formed. The four opposite angles of the surface of the bottom plate are each provided with a partition plate, and a top plate is supported by the four partition plates; and an outer-satellite load device is arranged on the top plate, and therefore a second force transmission path for the outer-satellite load device is formed. The integration satellite compact in layout has the beneficial effects that the integrated satellite configuration with the load as the center is provided, and the scheme of carrying out layout around the load is achieved; and meanwhile, the structural scheme with two main force transmission paths and one secondary force transmission path for the combined action is designed, the mechanic environment of the loads is optimized, the design complexity and the design pressure of a satellite structure and a load structure are reduced, and the bearing ratio of the satellite structure is improved.

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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IPC IPC(8): B64G1/10
Inventor 张文巧宋炜胥朱振才李华旺诸成王建平
Owner SHANGHAI ENG CENT FOR MICROSATELLITES
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