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Stacked satellite assembly structure

A combined and stacked technology, applied in the aerospace field, can solve the problems of inability to achieve inter-satellite interconnection, locking, unlocking and separation, and achieves the effects of reducing occupancy, improving utilization, reducing dynamic coupling and lateral torsion

Active Publication Date: 2021-08-10
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0004] The present invention intends to provide a stacked satellite assembly structure, which solves the problem that the existing stacked satellite structure technology cannot realize inter-satellite interconnection and locking, and unlocking and separation

Method used

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Embodiment

[0020] as attached Figure 1 to Figure 3 Shown: a stacked satellite assembly structure, including a hollow satellite bracket 1, a support plate 2 is provided directly above the satellite bracket 1, and four magnetic currents are arranged circumferentially between the support plate 2 and the satellite bracket 1 The variable damper 4, the center of the top of the satellite support 1 is also provided with an air spring 5 with a gap between it and the support plate 2, and the four magnetorheological dampers 4 and the support plate 2 can play the role of shock absorption.

[0021] Support plate 2 is provided with 3 groups of multi-layer satellite monomers, adopts five layers in the present embodiment, and each layer of satellite monomer 3 groups is all made up of four satellite monomers 3, and each satellite monomer 3 and existing technology The satellites in the structure are the same, and each satellite monomer 3 is provided with a limit hole 6 and a limit boss 7 on the same diag...

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Abstract

The invention discloses a stacked satellite assembly structure, and particularly relates to the technical field of aerospace. The stacked satellite assembly structure comprises a satellite support, satellite single bodies are arranged on the satellite support, limiting holes and limiting bosses are arranged on the satellite single bodies, and the limiting holes and the limiting bosses located on the tops of the satellite single bodies can be clamped on the limiting bosses and the limiting holes corresponding to the bottoms of the other satellite single bodies at the same time. An interconnection stand column is arranged on the outer wall of the other diagonal line of each satellite single body, a groove is formed in the top of each interconnection stand column, a protrusion is arranged at the bottom of each interconnection stand column, rigid pressing plates are jointly connected to the side walls of the satellite single bodies at the connecting positions of all the satellite single bodies in the same longitudinal direction, and a first explosive bolt is arranged between each rigid pressing plate and the corresponding satellite single body. By the adoption of the technical scheme, the problems that interconnection locking and unlocking separation between satellites cannot be achieved through an existing stacked satellite structure technology are solved, and space resources in a fairing can be utilized to the maximum extent.

Description

technical field [0001] The invention relates to the field of aerospace technology, in particular to a stacked satellite assembly structure. Background technique [0002] The Internet satellite system consists of ground segment, space segment and user segment. Among them, the ground segment is the gateway station, which realizes the connection with the feeder link between satellites, terminal access authentication, channel management and other operation control, system operation management and maintenance, and the interface with the Internet; the user segment is mainly composed of fixed terminals and vehicle-mounted, ship-borne, and airborne terminals; the space segment consists of hundreds or even more satellites forming a constellation to achieve global coverage. [0003] In order to speed up the construction of constellations, prolong the working life of the full state, reduce launch and maintenance costs, improve economic benefits, and provide technology accumulation for...

Claims

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Application Information

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IPC IPC(8): B64G1/64
CPCB64G1/648B64G1/645
Inventor 刘质加陈金宝董家宇邓卫华王治易陈传志江安澜吴迪霍伟航宋志成崔继云张迎雪罗晟
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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