Spatial multi-dimensional single-ring variable configuration mechanism

Abstract

The invention discloses a spatial multi-dimensional single-ring variable configuration mechanism, and relates to a variable configuration mechanism. The invention aims to solve the problem that the existing spacecraft is in a fixed shape and is difficult to meet the increasingly developing aerospace demand. The device comprises a spray pipe module assembly, an antenna module assembly and a telescope module assembly. The spray pipe module assembly, the antenna module assembly and the telescope module assembly are connected in sequence. The invention belongs to the technical field of aerospace equipment.

Description

Technical Field

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

[0002] For a long time, spacecraft have been designed with a fixed shape. However, with the development of the aerospace field, the requirements for spacecraft for aerospace missions have been increasing. The fixed shape of traditional spacecraft has seriously restricted the mission breadth of spacecraft. The variable configuration spacecraft with variable configuration design can have multiple configurations, and different configurations can be switched between each other, which greatly improves the mission breadth of spacecraft and provides a new path for the development of spacecraft. Existing spacecraft are all fixed in shape, which is difficult to meet the growing aerospace needs. Summary of the invention

[0003] The present invention aims to solve the problem that existing spacecrafts are all fixed in shape and cannot meet the ever-growing aerospace needs, and further 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: the present invention comprises 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] Further, 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 the third hinge, the other side of the first telescope module is connected to one side of the second telescope module through the fourth hinge, the other side of the second telescope module is connected to one side of the third telescope module through the fifth hinge, the other side of the third telescope module is connected to one side of the fourth telescope module through the sixth hinge, and the other side of the fourth telescope module is connected to the other end of the second antenna module through the 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 driving positions for the target configuration, thereby solving the problem of multiple driving configurations and complex control of complex deformable structures; at the same time, a spacecraft configuration scheme is provided, and through the mutual cooperation between modules, the spacecraft can have "conventional cruising state", "on-orbit working state" and "orbit change-braking state"; the changes between configurations can be achieved by relying only on three active hinges, thereby simplifying 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 cruising 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 deformation process of the present invention;

[0022] Figure 8 It is a schematic diagram of the change process of the three forms of the present invention;

[0023] Fig. 9 It is a schematic diagram of the present invention changing from a "track change-braking state" to an "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 the 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] Among them, 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 Two hinges are driven, 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 "conventional cruise state" to "orbit change-braking state", such as Fig. 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 is only a preferred embodiment of the present invention and does not limit the present invention in any form. Although the present invention has been disclosed as a preferred embodiment as above, it is not used to limit the present invention. Any technician familiar with this profession can make some changes or modify the technical contents disclosed above into equivalent embodiments without departing from the scope of the technical solution of the present invention. However, any simple modification, equivalent replacement and improvement made to the above embodiments without departing from the content of the technical solution of the present invention, based on the technical essence of the present invention, within the spirit and principles of the present invention, still fall within the protection scope of the technical solution of the present invention.

Claims

1. A spatial multi-dimensional single-ring variable configuration mechanism, characterized in that: It includes 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.

2. A spatial multi-dimensional single-ring variable configuration mechanism according to claim 1, characterized in that: 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).

3. A spatial multi-dimensional single-ring variable configuration mechanism according to claim 1 or 2, characterized in that: The antenna module assembly comprises 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).

4. A spatial multi-dimensional single-ring variable configuration mechanism according to claim 3, characterized in that: The telescope module assembly comprises 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) through a third hinge (3), the other side of the first telescope module (13) is connected to one side of the second telescope module (14) through a fourth hinge (4), the other side of the second telescope module (14) is connected to one side of the third telescope module (15) through a fifth hinge (5), the other side of the third telescope module (15) is connected to one side of the fourth telescope module (16) through 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) through a seventh hinge (7).

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