A two-dimensionally driven, retractable fan-shaped solar wing

Abstract

The present invention discloses a two-dimensionally driven repeatedly deployable fan-shaped solar wing, comprising a two-dimensional driving mechanism, a pressing and releasing device, a solar wing restraining mechanism, a flexible wing surface, a wing surface repeatedly deployable and retractable mechanism, a fixed box plate, a movable box plate, and a box plate restraining mechanism; the two-dimensional driving mechanism is connected to the fixed box plate, the pressing and releasing device is connected to the spacecraft body, the fixed box plate, and the movable box plate, the solar wing restraining mechanism is connected to the spacecraft, the flexible wing surface is connected to the wing surface repeatedly deployable and retractable mechanism, the fixed box plate and the movable box plate, the wing surface repeatedly deployable and retractable mechanism is fixedly connected to the fixed box plate and the movable box plate, and together realizes the repeated deployment and retraction of the flexible wing surface, the box plate restraining mechanism is fixedly connected to the fixed box plate, and cooperates with the movable box plate to realize the deployment or folding and pressing of the movable box plate and the fixed box plate. The present invention has the characteristics of two-dimensional rotation, repeated folding and pressing on the spacecraft body, small folding envelope, large deployment ratio, and light weight, and can reliably realize the repeated deployment and retraction of the fan-shaped solar wing.

Description

Technical Field

[0001] The present invention belongs to the technical field of solar wings, and in particular relates to a two-dimensionally driven fan-shaped solar wing that can be repeatedly extended and retracted. Background Art

[0002] Currently, most spacecraft solar panels utilize a rigid substrate and deploy using a one-time deployment and locking mechanism. They lack the ability to retract and retract repeatedly, have a large retraction envelope, and are primarily used on non-returnable spacecraft. However, for applications such as lunar and Mars exploration, which require spacecraft return, traditional rigid, one-time deployment and locking solar panels are insufficient. During docking and orbital maneuvers, the deployed solar panels experience significant overloads, and the requirements for retraction are unsatisfactory. However, two-dimensional, retractable solar panels can be retracted and compacted for orbital control, reducing the load on the spacecraft and the panels.

[0003] Therefore, there is an urgent need to provide a solar wing that can reliably achieve two-dimensional drive, repeated extension and retraction, repeated folding and pressing against the spacecraft body, and has a small folding envelope. Summary of the Invention

[0004] The purpose of the present invention is to provide a two-dimensionally driven, repeatedly retractable fan-shaped solar wing with a simple structure, which can realize two-dimensional drive, repeated retraction and pressing against the spacecraft body, and has the characteristics of high rigidity, small retraction envelope, large retraction ratio and light weight.

[0005] In order to solve the above problems, the technical solution of the present invention is:

[0006] A two-dimensionally driven, repeatedly deployable and retractable fan-shaped solar wing, comprising: a two-dimensional drive mechanism, a compression and release device, a solar wing restraint mechanism, a flexible wing surface, a wing surface repeatedly deployable and retractable mechanism, a fixed box plate, a movable box plate, and a box plate restraint mechanism;

[0007] The fixed end of the two-dimensional drive mechanism is fixed to the spacecraft body, and the electrical transmission output end of the two-dimensional drive mechanism is connected to the fixed box plate; it is used to perform two-dimensional solar orientation when the fan-shaped solar wing is unfolded;

[0008] The flexible wing surface is provided between the fixed box plate and the moving box plate. When the fan-shaped solar wing is folded, both sides of the flexible wing surface are respectively adhered to and folded into one body with the fixed box plate and the moving box plate.

[0009] The compression and release devices are respectively connected to the fixed box plate, the movable box plate and the spacecraft body, and are used to constrain the fan-shaped solar wing to the spacecraft body or release the restraining force between the fan-shaped solar wing and the spacecraft body;

[0010] The solar wing restraint mechanism is connected to the spacecraft body and is used to restrain the fixed box plate and the movable box plate to the spacecraft body or release the restraint force between the fixed box plate and the movable box plate and the spacecraft body;

[0011] The wing surface repeated deployment and retraction mechanism is respectively connected to the fixed box plate, the flexible wing surface and the moving box plate, and is used to realize repeated deployment and retraction of the flexible wing surface;

[0012] The box plate restraint mechanism is fixedly connected to the fixed box plate and is used to realize the expansion or folding and pressing of the movable box plate relative to the fixed box plate.

[0013] According to an embodiment of the present invention, the two-dimensional drive mechanism envelops the first drive assembly, the second drive assembly, and the electrical transmission device;

[0014] The rotation axis of the first drive assembly and the rotation axis of the second drive assembly are perpendicular to each other, the first drive assembly can rotate 0 to 180 degrees, and the second drive assembly can rotate 0 to 360 degrees.

[0015] The electrical transmission device is used to transmit power and signals of the fan-shaped solar wing, realizing power and signal transmission when the first drive component and the second drive component rotate at any angle.

[0016] According to one embodiment of the present invention, the compression release device includes an upper compression support sleeve, a lower compression support sleeve, an explosive device, and a compression rod assembly;

[0017] Among them, the upper clamping support sleeve is connected to the moving box plate, the lower clamping support sleeve is connected to the fixed box plate, the pyrotechnic device is connected to the spacecraft body, and the clamping rod assembly is fixedly connected to the moving box plate, the fixed box plate and the spacecraft body respectively through the upper clamping support sleeve, the lower clamping support sleeve and the pyrotechnic device.

[0018] According to one embodiment of the present invention, the solar wing restraint mechanism includes a drive assembly, a first capture claw, and a second capture claw;

[0019] The first capturing claw and the second capturing claw rotate under the action of the driving assembly and cooperate with the moving box plate to achieve the retraction and compression of the spacecraft body and the moving box plate.

[0020] According to one embodiment of the present invention, the airfoil repeated deployment and retraction mechanism includes a drive transmission assembly, a strut assembly, a fixed support, a moving support, an adapter frame, a sun gear, and a planetary gear;

[0021] Wherein, the moving support rotates relative to the fixed support under the action of the driving transmission assembly;

[0022] The strut assembly is fixedly connected to the rigid struts of the flexible wing surface;

[0023] The sun gear is fixedly mounted on the fixed support, and the planetary gears are fixedly mounted on the moving support;

[0024] The output shaft of the driving transmission assembly passes through the through hole on the fixed support and is connected to the adapter frame; the adapter frame, the fixed support and the moving support are installed through a pin shaft and have rotational freedom.

[0025] Due to the adoption of the above technical solution, the present invention has the following advantages and positive effects compared with the prior art:

[0026] 1) The two-dimensionally driven, repeatedly deployable and retractable fan-shaped solar wing in one embodiment of the present invention realizes the repeated deployment and retraction of the solar wing only through a two-dimensional driving mechanism, a solar wing constraint mechanism, a wing surface repeated deployment and retraction mechanism, and a box plate constraint mechanism, and has a simple structure.

[0027] 2) The fan-shaped solar wing provided by the present invention has a two-dimensional drive mechanism with two drive components, which can realize the two-dimensional rotation of the fan-shaped solar wing and the orientation of the sun;

[0028] 3) The fan-shaped solar wing provided by the present invention is able to be repeatedly folded and pressed against the spacecraft body by a two-dimensional driving mechanism and a solar wing restraint mechanism, and the folding envelope is small.

[0029] 4) The solar wing provided by the present invention unfolds in a fan shape, has higher unfolding stiffness and a larger fold-to-expand ratio. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Figure 1 Schematic diagram of a two-dimensionally driven, retractable, and repeatable fan-shaped solar wing in a folded state according to one embodiment of the present invention;

[0031] Figure 2 Schematic diagram of a two-dimensionally driven, retractable, and repeatedly expandable fan-shaped solar wing in an expanded state according to one embodiment of the present invention;

[0032] Figure 3 is a schematic diagram of a two-dimensional driving mechanism in one embodiment of the present invention;

[0033] Figure 4 is a schematic diagram of a compression release device in one embodiment of the present invention;

[0034] Figure 5 is a schematic diagram of a solar wing restraint mechanism in one embodiment of the present invention;

[0035] Figure 6 Schematic diagram of a wing surface repeated deployment and retraction mechanism in one embodiment of the present invention;

[0036] Figure 7It is a cross-sectional view of the airfoil repeated deployment and retraction mechanism in one embodiment of the present invention.

[0037] Description of reference numerals:

[0038] 1: Two-dimensional driving mechanism; 11: First driving assembly; 12: Second driving assembly; 13: Electric transmission device; 2: Compression and release device; 21: Upper compression support sleeve; 22: Lower compression support sleeve; 23: Explosive device; 24: Compression rod assembly; 3: Solar wing restraint mechanism; 31: Driving assembly; 32: Capture claw 1; 33: Capture claw 2; 4: Flexible wing surface; 5: Wing surface repeated extension and retraction mechanism; 51: Driving transmission assembly; 52: Strut group; 53: Fixed support; 54: Moving support; 56: Adapter frame; 57: Sun gear; 58: Planetary gear; 6: Fixed box plate; 7: Moving box plate; 8: Box plate restraint mechanism. DETAILED DESCRIPTION

[0039] The following is a further detailed description of a two-dimensionally driven, retractable, fan-shaped solar wing proposed by the present invention in conjunction with the accompanying drawings and specific embodiments. The advantages and features of the present invention will become more apparent from the following description and claims.

[0040] Please see Figure 1 and Figure 2 This embodiment provides a two-dimensionally driven, repeatedly deployable fan-shaped solar wing, comprising: a two-dimensional drive mechanism 1, a compression and release device 2, a solar wing constraint mechanism 3, a flexible wing surface 4, a wing surface repeated deployment and retraction mechanism 5, a fixed box plate 6, a movable box plate 7, and a box plate constraint mechanism 8.

[0041] The fixed end of the two-dimensional drive mechanism 1 is fixed to the spacecraft body, and the electrical transmission output end of the two-dimensional drive mechanism is connected to the fixed box plate 6; it is used to perform two-dimensional solar orientation when the fan-shaped solar wing is unfolded.

[0042] A flexible wing surface 4 is provided between the fixed box panel 6 and the moving box panel 7. When the fan-shaped solar wing is folded, both sides of the flexible wing surface 4 are respectively fitted and folded together with the fixed box panel 6 and the moving box panel 7.

[0043] The compression and release device 2 is respectively connected to the fixed box plate 6, the movable box plate 7 and the spacecraft body, and is used to constrain the fan-shaped solar wing to the spacecraft body or release the restraining force between the fan-shaped solar wing and the spacecraft body.

[0044] The solar wing restraint mechanism 3 is connected to the spacecraft body and is used to restrain the fixed box panel 6 and the movable box panel 7 to the spacecraft body or release the restraint force between the movable box panel 7 and the fixed box panel 6 and the spacecraft body.

[0045] The wing surface repeated deployment and retraction mechanism 5 is respectively connected to the fixed box plate 6, the flexible wing surface 4 and the moving box plate 7, so as to realize the repeated deployment and retraction of the flexible wing surface 4.

[0046] The box panel restraint mechanism 8 is fixedly connected to the fixed box panel 6 and is used to realize the expansion or contraction and compression of the movable box panel 7 relative to the fixed box panel 6.

[0047] Further, see Figure 3 The two-dimensional drive mechanism 1 includes a first drive component 11, a second drive component 12, and an electrical transmission device 13. The rotation axis of the first drive component 11 and the rotation axis of the second drive component 12 are perpendicular to each other. The first drive component 11 can rotate 0 to 180 degrees, and the second drive component 12 can rotate 0 to 360 degrees.

[0048] The power transmission device 13 is used to transmit power and signals of the fan-shaped solar wings, realizing power and signal transmission when the first drive component 11 and the second drive component 12 rotate at any angle.

[0049] Please see Figure 4 The compression and release device 2 includes an upper compression support sleeve 21, a lower compression support sleeve 22, an explosive device 23, and a compression rod assembly 24. The upper compression support sleeve 21 is connected to the movable box plate 7, the lower compression support sleeve 22 is connected to the fixed box plate 6, and the explosive device 23 is connected to the spacecraft body. The compression rod assembly 24 is fixedly connected to the movable box plate 7, the fixed box plate 6, and the spacecraft body respectively through the upper compression support sleeve 21, the lower compression support sleeve 22, and the explosive device 23.

[0050] Please see Figure 5 The solar wing restraint mechanism 3 includes a drive assembly 31, a first capture claw 32, and a second capture claw 33. The first and second capture claws 32, 33 rotate under the action of the drive assembly 31, cooperating with the movable box panel 7. The compression force of the solar wing restraint mechanism 3 is transmitted between the fixed box panel 6 and the movable box panel 7 via the compression release device 2, thereby achieving the retraction and compression of the spacecraft body and the fixed box panel 6 and the movable box panel 7.

[0051] Please see Figure 6 、 Figure 7 The airfoil retractable mechanism 5 includes a drive transmission assembly 51, a strut assembly 52, a fixed support 53, a kinematic support 54, an adapter 56, a sun gear 57, and planetary gears 58. The kinematic support 52 rotates relative to the fixed support 53 under the action of the drive transmission assembly 51. The strut assembly 52 of the airfoil retractable mechanism 5 is fixedly connected to the rigid struts of the flexible airfoil 4. The sun gear 57 is fixedly mounted on the fixed support 53, and the planetary gears 58 are fixedly mounted on the kinematic support 54. The output shaft of the drive transmission assembly 51 passes through a through-hole in the fixed support 53 and connects to the adapter 56. The adapter 56 is mounted to the fixed support 53 and the kinematic support 54 via a pin, allowing for rotational freedom.

[0052] The deployment and retraction of the wing surface retractable mechanism 5 is performed by driving the transmission assembly 51 to drive the adapter 56, causing the planetary gear 58 to rotate around the sun gear 57. Therefore, the moving support 54 rotates around the fixed support 53, and the wing surface retractable mechanism 5 is deployed and retracted.

[0053] The following describes the working process of the above-mentioned two-dimensional driven retractable fan-shaped solar wing:

[0054] In the initial state, the two sides of the flexible wing surface 4 are respectively folded together with the fixed box plate 6 and the movable box plate 7, and the flexible wing surface 4 is folded and compacted under the action of the compression release device 2, the solar wing constraint mechanism 3, and the box plate constraint mechanism 8.

[0055] The expansion steps are as follows:

[0056] The compression release device 2 is detonated and unlocked, releasing the constraints between the moving box plate 7, the fixed box plate 6, and the spacecraft body;

[0057] The solar wing restraint mechanism 3 is actuated to release the restraints between the moving box plate 7, the fixed box plate 6, and the spacecraft body;

[0058] The first driving assembly 11 of the two-dimensional driving mechanism 1 is actuated to rotate the fan-shaped solar wing 90° around the rotation axis of the first driving assembly 11;

[0059] The second drive assembly 12 of the two-dimensional drive mechanism 1 is actuated to rotate the fan-shaped solar wing 180° around the rotation axis of the second drive assembly 12;

[0060] The box plate restraint mechanism 8 is actuated to release the restraint between the moving box plate 7 and the fixed box plate 6;

[0061] The wing surface repeats the action of the unfolding and retracting mechanism 5, rotating and unfolding the flexible wing surface 4 from the folded state into a circular shape, and works together with the wing surface tensioning mechanism to apply a certain preload force;

[0062] The box panel restraint mechanism 8 is activated to continue pulling the movable box panel 7 toward the fixed box panel 6, and works together with the wing surface tensioning mechanism to continue applying preload force.

[0063] The steps for folding are as follows:

[0064] The box plate restraint mechanism 8 is actuated to release the restraint between the moving box plate 7 and the fixed box plate 6;

[0065] The wing surface repeats the action of the unfolding and retracting mechanism 5, rotating and folding the flexible wing surface 4 from the unfolded state;

[0066] The boxboard restraint mechanism 8 is actuated to pull the moving boxboard 7 toward the fixed boxboard 6, and works together with the flexible wing surface 4, the fixed boxboard 6, and the buffer foam on the moving boxboard 7 to apply a compressive force;

[0067] The second drive assembly 12 of the two-dimensional drive mechanism 1 is actuated to rotate the fan-shaped solar wing 180° around the rotation axis of the second drive assembly 12;

[0068] The first driving assembly 11 of the two-dimensional driving mechanism 1 is actuated to rotate the fan-shaped solar wing 90° around the rotation axis of the first driving assembly 11;

[0069] The solar wing restraint mechanism 3 is activated to connect and fix the moving box plate 7, the fixed box plate 6 and the spacecraft body.

[0070] The above-mentioned unfolding step and folding step can be repeated.

[0071] The embodiments of the present invention have been described in detail above with reference to the accompanying drawings, but the present invention is not limited to the above embodiments. Even if various changes are made to the present invention, if these changes fall within the scope of the claims of the present invention and their equivalents, they still fall within the scope of protection of the present invention.

Claims

1. A two-dimensionally driven, retractable, fan-shaped solar wing, characterized in that: include: Two-dimensional driving mechanism, compression and release device, solar wing restraint mechanism, flexible wing surface, wing surface repeated extension and retraction mechanism, fixed box plate, moving box plate, box plate restraint mechanism; The fixed end of the two-dimensional drive mechanism is fixed to the spacecraft body, and the electrical transmission output end of the two-dimensional drive mechanism is connected to the fixed box plate; it is used to perform two-dimensional solar orientation when the fan-shaped solar wing is unfolded; The flexible wing surface is provided between the fixed box board and the moving box board. When the fan-shaped solar wing is folded, both sides of the flexible wing surface are respectively adhered to and folded into one body with the fixed box board and the moving box board; The compression and release devices are respectively connected to the fixed box plate, the movable box plate and the spacecraft body, and are used to constrain the fan-shaped solar wing to the spacecraft body or release the restraining force between the fan-shaped solar wing and the spacecraft body; The solar wing restraint mechanisms are respectively connected to the spacecraft body and are used to restrain the fixed box plate and the movable box plate to the spacecraft body or release the restraint force between the fixed box plate, the movable box plate and the spacecraft body; The wing surface repeated extension and retraction mechanism is connected to the fixed box plate, the flexible wing surface and the moving box plate, and is used to realize repeated extension and retraction of the flexible wing surface; The box plate restraint mechanism is fixedly connected to the fixed box plate and is used to realize the expansion or folding and pressing of the movable box plate relative to the fixed box plate.

2. The two-dimensionally driven, retractable, fan-shaped solar wing according to claim 1, characterized in that: The two-dimensional drive mechanism envelops the first drive assembly, the second drive assembly, and the electrical transmission device; The rotation axis of the first drive assembly and the rotation axis of the second drive assembly are perpendicular to each other, the first drive assembly can rotate 0 to 180 degrees, and the second drive assembly can rotate 0 to 360 degrees. The electrical transmission device is used to transmit power and signals of the fan-shaped solar wing, realizing power and signal transmission when the first drive component and the second drive component rotate at any angle.

3. The two-dimensionally driven, retractable, fan-shaped solar wing according to claim 1, characterized in that: The compression release device includes an upper compression support sleeve, a lower compression support sleeve, an explosive device, and a compression rod assembly; Among them, the upper clamping support sleeve is connected to the moving box plate, the lower clamping support sleeve is connected to the fixed box plate, the pyrotechnic device is connected to the spacecraft body, and the clamping rod assembly is fixedly connected to the moving box plate, the fixed box plate and the spacecraft body respectively through the upper clamping support sleeve, the lower clamping support sleeve and the pyrotechnic device.

4. The two-dimensionally driven, repeatedly extendable and retractable fan-shaped solar wing according to claim 1, characterized in that: The solar wing restraint mechanism includes a drive assembly, a first capture claw, and a second capture claw; The first capturing claw and the second capturing claw rotate under the action of the driving assembly and cooperate with the moving box plate to achieve the retraction and compression of the spacecraft body and the moving box plate.

5. The two-dimensionally driven, retractable, fan-shaped solar wing according to claim 1, characterized in that: The wing surface repeated deployment and retraction mechanism includes a drive transmission assembly, a strut assembly, a fixed support, a moving support, an adapter frame, a sun gear, and a planetary gear; Wherein, the moving support rotates relative to the fixed support under the action of the driving transmission assembly; The strut assembly is fixedly connected to the rigid struts of the flexible wing surface; The sun gear is fixedly mounted on the fixed support, and the planetary gears are fixedly mounted on the moving support; The output shaft of the driving transmission assembly passes through the through hole on the fixed support and is connected to the adapter frame; the adapter frame, the fixed support and the moving support are installed through a pin shaft and have rotational freedom.

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