Unlock instant, AI-driven research and patent intelligence for your innovation.

Repeatable variable configuration truss type spacecraft structure

A spacecraft structure and truss-type technology, applied in the field of aerospace, can solve the problems of fixed and closed spacecraft structure, difficulty in upgrading and maintaining spacecraft on-orbit maintenance equipment, and complex redundancy, etc., to achieve easy application and promotion, low density, The effect of large envelope space ratio

Active Publication Date: 2016-09-28
HARBIN INST OF TECH
View PDF6 Cites 14 Cited by
  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The purpose of the present invention is to provide a truss-type spacecraft structure with repeatable variable configuration to solve the problem that the existing spacecraft has a fixed and closed structure and complex redundancy, and it is difficult to realize on-orbit maintenance and equipment upgrade maintenance of spacecraft failures

Method used

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
View more

Image

Smart Image Click on the blue labels to locate them in the text.
Viewing Examples
Smart Image
  • Repeatable variable configuration truss type spacecraft structure
  • Repeatable variable configuration truss type spacecraft structure
  • Repeatable variable configuration truss type spacecraft structure

Examples

Experimental program
Comparison scheme
Effect test

specific Embodiment approach 1

[0028] Specific implementation mode one: combine Figure 1 to Figure 9 Describe this embodiment. This embodiment includes a docking ring 15, a bottom plate 16, a support frame 19, a transmission mechanism, a system drive mechanism, N-4 sets of truss configuration change mechanisms, two fixed support plates 17, and N-2 deployment Plate 18 and N-2 locking mechanisms;

[0029] The docking ring 15 is arranged on the bottom of the bottom plate 16, the system driving mechanism and the support frame 19 are all arranged on the top of the bottom plate 16, the bottom of the transmission mechanism is arranged on the system driving mechanism, and the top of the transmission mechanism is arranged on On the support frame 19, the two fixed support plates 17 are vertically arranged side by side on the support frame 19 and the two are oppositely arranged, and the N-2 expansion plates 18 are hinged at the edge of the bottom plate 16 in turn, and each expansion The plate 18 is correspondingly p...

specific Embodiment approach 2

[0032] Specific implementation mode two: combination Figure 1 to Figure 9 To describe this embodiment, the value of N in this embodiment ranges from 6 to 12. When the value of N is 6, there are 2 sets of truss variable configuration mechanisms, 4 expansion plates 18 and 4 locking mechanisms, and the appearance of the present invention in the folded state is a hexagonal prism; when the value of N is At 8 o'clock, there are 4 sets of truss variable configuration mechanisms, 6 expansion plates 18 and 6 locking mechanisms. Prismatic, nine prisms and other prisms.

[0033] The shape of the bottom plate 16 in the present invention is related to the specific value of N. When the value of N is 6, the bottom plate 16 is a hexagonal plate. Other unmentioned structures and connections are the same as those in the first embodiment.

specific Embodiment approach 3

[0034] Specific implementation mode three: combination figure 1 and Figure 4 Describe this embodiment, the system driving mechanism in this embodiment includes a total motor 1, a total reducer 2, a bearing bracket 3, a shaft coupling 4 and a bearing 5, the total motor 1 is arranged on the bottom plate 16, and the The output shaft of the total motor 1 is provided with a total reducer 2 , a bearing bracket 3 , a shaft coupling 4 and a bearing 5 in sequence. Other unmentioned structures and connections are the same as those in the first or second embodiment.

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

PUM

No PUM Login to View More

Abstract

The invention provides a repeatable variable configuration truss type spacecraft structure and relates to spacecrafts. An existing spacecraft is fixed, sealed, redundant and complex in structure, and on-orbit maintenance of spacecraft faults and equipment upgrade and maintenance are difficult to achieve. A docking ring is arranged at the bottom of a bottom plate, a system driving mechanism and a supporting frame are arranged on the top of the bottom plate, the bottom of a transmission mechanism is arranged on the system driving mechanism, the top of the transmission mechanism is arranged on the supporting frame, two fixed supporting plates are vertically and oppositely arranged on the supporting frame in parallel, the bottoms of N-2 unfolded plates are sequentially hinged to the edge of the bottom plate, each unfolded plate is correspondingly provided with a locking mechanism, every two adjacent unfolded plates are connected with the transmission mechanism through a corresponding truss variable configuration type mechanism, and the N-2 unfolded plates are folded and unfolded synchronously under the control of N-4 truss variable configuration type mechanisms and the transmission mechanism. The spacecraft structure is used in the aerospace and aviation field.

Description

technical field [0001] The invention relates to a variable-configuration truss-type spacecraft structure, which belongs to the field of aerospace. Background technique [0002] With manned spacecraft, space stations, long-lived satellites and other spacecraft operating in orbit for a long time, the future on-orbit service technology has great application prospects. With the increasingly complex structure and larger scale of satellite platforms, traditional satellite platforms have shown great limitations. For example, traditional satellites are mostly closed polyhedrons with unchanged structures. Usually, various subsystems such as thermal control, The integration of communication, attitude control, propulsion and other payloads together, coupled with the increased redundancy design to improve reliability, makes the entire satellite structure complex and difficult to achieve on-orbit maintenance. In short, the existing spacecraft have fixed and closed structures and complex...

Claims

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

Application Information

Patent Timeline
no application Login to View More
IPC IPC(8): B64G1/10B64G1/22
CPCB64G1/10B64G1/222B64G1/223
Inventor 郭宏伟刘荣强邓宗全赵冲岳洪浩
Owner HARBIN INST OF TECH