A spatial multi-dimensional single-ring variable configuration mechanism

Abstract

A multi-dimensional single-ring space-based variable configuration mechanism relates to a variable configuration mechanism. This invention addresses the problem that existing spacecraft are all fixed in shape, making it difficult to meet the ever-evolving needs of aerospace. The invention comprises a nozzle module assembly, an antenna module assembly, and a telescope module assembly; the nozzle module assembly, antenna module assembly, and telescope module assembly are sequentially connected. This invention belongs to the field of aerospace equipment technology.

Description

Technical Field

[0001] The invention relates to a variable configuration mechanism and belongs to the technical field of aerospace equipment. Background Art

[0002] For a long time, spacecraft have adopted a fixed-shape design. However, with the development of the aerospace industry, the requirements for spacecraft missions are becoming increasingly stringent. The fixed shape of traditional spacecraft has severely restricted the breadth of spacecraft missions. However, variable-configuration spacecraft with a variable-configuration design can adopt multiple configurations and switch between them, greatly expanding the breadth of spacecraft missions and providing a new path for spacecraft development. Existing spacecraft are all fixed in shape, making it difficult to meet the growing needs of aerospace. Summary of the Invention

[0003] In order to solve the problem that existing spacecraft are all fixed in shape and cannot meet the ever-developing aerospace needs, the present invention proposes a spatial multi-dimensional single-ring variable configuration mechanism.

[0004] The technical solution adopted by the present invention to solve the above problems is as follows: the present invention includes a nozzle module assembly, an antenna module assembly and a telescope module assembly;

[0005] The nozzle module assembly, the antenna module assembly and the telescope module assembly are connected in sequence.

[0006] Further, the nozzle module assembly includes a first hinge, a first nozzle module and a second nozzle module;

[0007] The first nozzle module and the second nozzle module are arranged side by side, and the first nozzle module is connected to the second nozzle module through a first hinge.

[0008] Furthermore, the antenna module assembly includes a second hinge, a third hinge, a seventh hinge, an eighth hinge, a first antenna module, and a second antenna module;

[0009] One end of the first antenna module is connected to the second nozzle module via a second hinge, and the other end of the first antenna module is connected to the telescope module assembly via a third hinge;

[0010] One end of the second antenna module is connected to the first nozzle module through the eighth hinge, and the other end of the second antenna module is connected to the telescope module assembly through the seventh hinge.

[0011] Further, the telescope module assembly includes a fourth hinge, a fifth hinge, a sixth hinge, a first telescope module, a second telescope module, a third telescope module and a fourth telescope module;

[0012] One side of the first telescope module is connected to the other end of the first antenna module through a third hinge, the other side of the first telescope module is connected to one side of the second telescope module through a fourth hinge, the other side of the second telescope module is connected to one side of the third telescope module through a fifth hinge, the other side of the third telescope module is connected to one side of the fourth telescope module through a sixth hinge, and the other side of the fourth telescope module is connected to the other end of the second antenna module through a seventh hinge.

[0013] The beneficial effects of the present invention are as follows: the present invention designs a single-ring 8R mechanism and designs three drive positions for the target configuration, which solves the problem of multiple drive configurations and complex control of complex deformable structures; at the same time, a spacecraft configuration scheme is provided, which can enable the spacecraft to have "conventional cruise state", "on-orbit working state" and "orbit change-braking state" through mutual cooperation between modules; the change between configurations can be achieved by relying only on three active hinges, which simplifies the control problem of the variable configuration mechanism.

[0014] The present invention only needs to drive two of the eight hinges to achieve the switching of the target configuration. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 This is a top view of the present invention in a cruising state;

[0016] Figure 2 This is a schematic diagram of the cruise state of the present invention;

[0017] Figure 3 It is a schematic diagram of the working state of the present invention;

[0018] Figure 4 This is a schematic diagram of the track change-braking state of the present invention;

[0019] Figure 5 This is a schematic diagram of the first deformation process of the present invention;

[0020] Figure 6 This is a schematic diagram of the second process of the present invention;

[0021] Figure 7 This is a schematic diagram of the third process of the present invention;

[0022] Figure 8 Schematic diagram of the change process of the three forms of the present invention;

[0023] Figure 9 It is a schematic diagram of the present invention changing from the "track change-braking state" to the "on-track working state";

[0024] Figures 1 to 8In the figure, 1-first hinge, 2-second hinge, 3-third hinge, 4-fourth hinge, 5-fifth hinge, 6-sixth hinge, 7-seventh hinge, 8-eighth hinge, 9-first nozzle module, 10-second nozzle module, 11-first antenna module, 12-second antenna module, 13-first telescope module, 14-second telescope module, 15-third telescope module, 16-fourth telescope module. DETAILED DESCRIPTION

[0025] Specific implementation method 1: Figures 1 to 7 As shown, a spatial multi-dimensional single-ring variable configuration mechanism includes a nozzle module assembly, an antenna module assembly and a telescope module assembly;

[0026] The nozzle module assembly, the antenna module assembly and the telescope module assembly are connected in sequence.

[0027] Specific implementation method 2: Figures 1 to 7 As shown, the nozzle module assembly includes a first hinge 1, a first nozzle module 9 and a second nozzle module 10;

[0028] The first nozzle module 9 and the second nozzle module 10 are arranged side by side, and the first nozzle module 9 is connected to the second nozzle module 10 via a first hinge 1 .

[0029] Specific implementation method three: Figures 1 to 7 As shown, the antenna module assembly includes a second hinge 2, a third hinge 3, a seventh hinge 7, an eighth hinge 8, a first antenna module 11 and a second antenna module 12;

[0030] One end of the first antenna module 11 is connected to the second nozzle module 10 via the second hinge 2, and the other end of the first antenna module 11 is connected to the telescope module assembly via the third hinge 3;

[0031] One end of the second antenna module 12 is connected to the first nozzle module 9 via the eighth hinge 8 , and the other end of the second antenna module 12 is connected to the telescope module assembly via the seventh hinge 7 .

[0032] Specific implementation method four: Figures 1 to 7 As shown, the telescope module assembly includes a fourth hinge 4, a fifth hinge 5, a sixth hinge 6, a first telescope module 13, a second telescope module 14, a third telescope module 15 and a fourth telescope module 16;

[0033] One side of the first telescope module 13 is connected to the other end of the first antenna module 11 through the third hinge 3, the other side of the first telescope module 13 is connected to one side of the second telescope module 14 through the fourth hinge 4, the other side of the second telescope module 14 is connected to one side of the third telescope module 15 through the fifth hinge 5, the other side of the third telescope module 15 is connected to one side of the fourth telescope module 16 through the sixth hinge 6, and the other side of the fourth telescope module 16 is connected to the other end of the second antenna module 12 through the seventh hinge 7.

[0034] The first nozzle module 9 , the second nozzle module 10 , the first antenna module 11 , the second antenna module 12 , the first telescope module 13 , the second telescope module 14 , the third telescope module 15 and the fourth telescope module 16 constitute a unit 8R mechanism.

[0035] Among them, the third hinge 3 and the seventh hinge 7 are perpendicular to the outside of the plane, the second hinge 2, the fourth hinge 4, the sixth hinge 6 and the eighth hinge 8 are arranged at a high position, and the first hinge 1 and the fifth hinge 5 are arranged at a low position.

[0036] How it works

[0037] When a spacecraft is cruising in space, it is in "conventional cruising state". When it needs to change to "on-orbit working state", such as Figure 8 The two hinges shown are driven, the two hinges are locked, and the other hinges are driven to achieve the switching of "on-track working state".

[0038] When the spacecraft needs to change from "normal cruise state" to "orbit change-braking state", such as Figure 9 The two hinges shown are driven, the two hinges are locked, and the other hinges are driven to achieve the switching of "track change-braking state".

[0039] The above description is merely a preferred embodiment of the present invention and does not constitute any form of limitation to the present invention. Although the present invention has been disclosed as a preferred embodiment as above, it is not intended to limit the present invention. Any technician familiar with the present profession can make some changes or modifications to equivalent embodiments of equivalent changes using the technical content disclosed above without departing from the scope of the technical solution of the present invention. However, any simple modification, equivalent replacement and improvement of the above embodiments made according to the technical essence of the present invention, within the spirit and principles of the present invention, without departing from the content of the technical solution of the present invention, shall still fall within the scope of protection of the technical solution of the present invention.

Claims

1. A spatial multi-dimensional single-ring variable configuration mechanism, characterized in that: including a nozzle module assembly, an antenna module assembly and a telescope module assembly; The nozzle module assembly, the antenna module assembly and the telescope module assembly are connected in sequence; The nozzle module assembly comprises a first hinge (1), a first nozzle module (9) and a second nozzle module (10); The first nozzle module (9) and the second nozzle module (10) are arranged side by side, and the first nozzle module (9) is connected to the second nozzle module (10) via a first hinge (1); The antenna module assembly includes a second hinge (2), a third hinge (3), a seventh hinge (7), an eighth hinge (8), a first antenna module (11), and a second antenna module (12); One end of the first antenna module (11) is connected to the second nozzle module (10) via a second hinge (2), and the other end of the first antenna module (11) is connected to the telescope module assembly via a third hinge (3); One end of the second antenna module (12) is connected to the first nozzle module (9) via an eighth hinge (8), and the other end of the second antenna module (12) is connected to the telescope module assembly via a seventh hinge (7); The telescope module assembly includes a fourth hinge (4), a fifth hinge (5), a sixth hinge (6), a first telescope module (13), a second telescope module (14), a third telescope module (15) and a fourth telescope module (16); One side of the first telescope module (13) is connected to the other end of the first antenna module (11) via a third hinge (3), the other side of the first telescope module (13) is connected to one side of the second telescope module (14) via a fourth hinge (4), the other side of the second telescope module (14) is connected to one side of the third telescope module (15) via a fifth hinge (5), the other side of the third telescope module (15) is connected to one side of the fourth telescope module (16) via a sixth hinge (6), and the other side of the fourth telescope module (16) is connected to the other end of the second antenna module (12) via a seventh hinge (7); The third hinge (3) and the seventh hinge (7) are perpendicular to the outside of the plane, the second hinge (2), the fourth hinge (4), the sixth hinge (6) and the eighth hinge (8) are arranged at a high position, and the first hinge (1) and the fifth hinge (5) are arranged at a low position.

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