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Satellite propulsion service cabin structure

A service cabin, star and arrow technology, which is applied to the propulsion system devices of space navigation vehicles, space navigation equipment, space navigation vehicles, etc., can solve the problems of less connection points and less layout space, and achieves reduction of structural mass and satellite center of mass. , The effect of reducing the load of the star-arrow connection

Inactive Publication Date: 2020-01-17
BEIJING INST OF SPACECRAFT SYST ENG
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Problems solved by technology

[0004] The truss configuration corresponding to the load-bearing cylinder configuration, such as the BSS-702 platform, adopts the X-shaped layout of the truss bar system, so that the storage tanks can be arranged in parallel, but the X-shaped layout also leads to fewer connection points , less layout space for other thrust control devices such as gas cylinders

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  • Satellite propulsion service cabin structure
  • Satellite propulsion service cabin structure
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Embodiment Construction

[0024] The cabin structure according to the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0025] In order to realize a satellite structure that meets the requirements of large load capacity and multi-load adaptability, the propulsion service module structure of the present invention is proposed, and the specific implementation method is as follows.

[0026] According to the structure of the propulsion service cabin of the present invention, its main load-bearing structure is composed of a point-connected star-arrow docking ring 1, a main partition 2 and inclined partitions 3-6. Among them, the first inner rod 201, the second inner rod 202, the first outer rod 203, the second outer rod 204, the first upper rod 205, and the second upper rod 206 are embedded in the main partition 2, forming two sets of triangular planar truss units , the two groups of units are arranged symmetrically about the c...

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Abstract

The invention provides a satellite propulsion service cabin structure which is suitable for a satellite structure family system with large bearing and multi-load adaptive capacity requirements. According to the cabin structure, a main force bearing structure is composed of a satellite-rocket butt joint ring and beam-slab composite structural slabs, the beam-slab composite structural slabs form three sets of W-shaped plane truss units, and in a top view, the three sets of planes intersect at the central axis and are distributed in a star shape. According to the cabin structure, the four large spaces divided by the star-shaped truss are used for installing the storage tank, the lower portion of the storage tank is directly connected with the butt joint ring, the upper portion of the storagetank is connected with the truss joint through the pull rod, and the structural weight is greatly reduced through the storage tank connecting mode. The two smaller spaces of the invention allow to beused to mount gas cylinders. By means of the structure, the large bearing capacity of the propelling service cabin is ensured.

Description

technical field [0001] The invention belongs to the technical field of mechanical structures, and in particular relates to a satellite propulsion service module structure, which is suitable for a satellite structure family system with large load capacity and multi-load adaptability requirements. Background technique [0002] At present, the satellite structure with the largest carrying capacity is the communication satellite, which generally adopts a central load-bearing cylinder configuration. The maximum carrying capacity of the traditional communication satellite structure in my country is about 5600kg, and the international Alphabus platform has achieved 8600kg. In order to adapt to greater carrying capacity To improve the international competitiveness of my country's commercial satellites, it is urgent to develop a corresponding satellite propulsion service module structure. [0003] In the large-load satellite structure configuration, the configuration characteristics o...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/40
CPCB64G1/402
Inventor 高峰柴洪友邓宇华盛聪李伟杰王刚陈燕石文静白刚闫亮王晓宇
Owner BEIJING INST OF SPACECRAFT SYST ENG
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