CN220010090U - Satellite unfolding mechanism for reducing sun wing shadows - Google Patents
Satellite unfolding mechanism for reducing sun wing shadows Download PDFInfo
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- CN220010090U CN220010090U CN202321719760.9U CN202321719760U CN220010090U CN 220010090 U CN220010090 U CN 220010090U CN 202321719760 U CN202321719760 U CN 202321719760U CN 220010090 U CN220010090 U CN 220010090U
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Abstract
The utility model discloses a satellite unfolding mechanism for reducing sun wing shadows, which relates to the field of satellites and comprises a star body and a sun wing assembly arranged on the side wall of the star body; the solar wing assembly comprises a solar wing main body, a wing body unfolding mechanism, a sliding assembly, a first locking/releasing unit and a second locking/releasing unit; the fixed end of the wing body unfolding mechanism is arranged on the side wall of the star body, and the rotating end of the wing body unfolding mechanism is connected with the fixed part of the sliding component; the solar wing main body is arranged on the sliding part of the sliding component; the first locking/releasing unit is arranged on the side wall of the star body, and is locked on the solar wing main body in the contracted position; the fixed end of the second locking/releasing unit is arranged on the side wall of the star, and in the contracted position, the locking end of the second locking/releasing unit is connected with the solar wing body; in the release position, the solar wing body is disengaged from the second locking/release unit. The utility model has the effect of reducing the shielding of the satellite shadow to the solar wing.
Description
Technical Field
The utility model relates to the field of satellites, in particular to a satellite unfolding mechanism for reducing sun wing shadows.
Background
At present, most of solar wings used by satellites are unfolded in a body-mounted manner, and the distance between a battery piece and a star is relatively short after the solar wings are unfolded. If the satellite is large in size, the shadow of the satellite can be projected onto the solar wing, so that the shielding part of the battery piece cannot work normally to generate electricity.
Disclosure of Invention
In order to reduce the problem of shielding the solar wing by the satellite shadow, the utility model provides a satellite unfolding mechanism for reducing the solar wing shadow.
In order to solve the problems, the technical scheme of the utility model is as follows:
a satellite deployment mechanism for reducing sun wing shadows, comprising,
a star;
at least one solar wing assembly arranged on the side wall of the star; the solar wing assembly includes: the solar wing comprises a solar wing main body, a wing body unfolding mechanism, a sliding assembly, a first locking/releasing unit and a second locking/releasing unit;
the fixed end of the wing body unfolding mechanism is arranged on the side wall of the star body, and the rotating end of the wing body unfolding mechanism is connected with the fixed part of the sliding component and is used for driving the sliding component to swing from a contracted position to a release position;
the sliding part of the sliding component is provided with the solar wing main body and is used for driving the solar wing main body to slide and keep away from the star;
the first locking/releasing unit is arranged on the side wall of the star body, and in the contracted position, the first locking/releasing unit is locked on the solar wing main body;
the fixed end of the second locking/releasing unit is arranged at the fixed end of the star or the wing body unfolding mechanism, and in the contracted position, the locking end of the second locking/releasing unit is connected with the solar wing main body; the unlocking position of the second locking/releasing unit corresponds to the releasing position.
The utility model relates to a satellite unfolding mechanism for reducing sun wing shadows, which comprises an inner slide bar serving as a fixed part, an outer slide rail serving as a sliding part and an elastic piece, wherein the inner slide bar is a fixed part;
one end of the inner slide rod is arranged at the rotating end of the wing body unfolding mechanism, the outer slide rail is fixed on the side wall of the solar wing main body, and the outer slide rail is connected with the inner slide rod in a sliding manner;
the elastic piece is arranged between the rotating end of the wing body unfolding mechanism and the outer sliding rail,
or, the elastic piece is arranged between the inner slide rod and the outer slide rail.
The satellite unfolding mechanism for reducing sun wing shadows comprises a plurality of fixed blocks, and a rotating block and a rotating torsion piece which correspond to the fixed blocks;
the rotating block is rotationally connected with the fixed block; the rotating block is provided with convex points, the rotating torsion piece is of an S-shaped structure, one end of the rotating torsion piece is fixed on the fixed block, and the other end of the rotating torsion piece slides on the convex points and drives the convex points to drive the rotating block to move;
the side wall of the rotating block is fixed with the end part of the inner slide rod.
According to the satellite unfolding mechanism for reducing sun wing shadows, the fixed block is provided with the fixed-position pin, the rotating block is provided with the rotating-position pin, and when the satellite unfolding mechanism is in a release position, the fixed-position pin is clamped with the rotating-position pin to fix the rotating block.
The satellite deployment mechanism for reducing solar wing shadows of the present utility model, the first locking/releasing unit includes a compression release mechanism body, a rope structure, and a fusing structure;
the compaction release mechanism main body is fixed on the side wall of the star, and the rope structure is arranged between the solar wing main body and the compaction release mechanism main body when the solar wing main body is in a contracted position; the fusing structure is arranged on the compaction release mechanism main body and used for fusing the rope structure.
The satellite unfolding mechanism for reducing sun wing shadows is characterized in that the rotation axis of the rotating block is the rotation axis of the sun wing body, and the rotation axis of the sun wing body is defined as a basic line.
The second locking/releasing unit comprises at least one releasing block which is a fixed end and a connecting rod which is a locking end; the release block is fixed on the side wall of the star, the connecting rod is fixed on the solar wing main body, and the length direction of the connecting rod is parallel to the foundation line;
the release block is provided with a release slot, the release slot is arranged by taking the basic line as an axis, and one end of the release slot is provided with an opening; when the connecting rod is in the contracted position, the connecting rod is positioned in the tripping groove; when in the release position, the connecting rod is positioned at the opening of the tripping slot.
According to the satellite unfolding mechanism for reducing sun wing shadows, the elastic piece is the spring sleeved on the inner slide rod, one end of the spring is fixed on the side wall of the rotating end of the wing unfolding mechanism, and the other end of the spring is abutted against the end part of the outer slide rail, which faces the star.
According to the satellite unfolding mechanism for reducing the sun wing shadow, the end part of the inner slide rod, which is away from the rotating end of the wing body unfolding mechanism, is provided with at least one positioning pin, and the inner wall of the outer slide rail is provided with a positioning hole corresponding to the positioning pin for locking the sun wing body to a preset sliding position.
According to the satellite unfolding mechanism for reducing the sun wing shadow, the number of the fixing blocks in each wing body unfolding mechanism is two, and when the satellite unfolding mechanism is in a contracted position, the fixing blocks are positioned on two sides of the sun wing;
the number of the release blocks in each second locking/releasing unit is two, the release blocks are respectively positioned between the fixed blocks and the solar wing main body, and the end parts of the connecting rods are respectively positioned in the corresponding tripping grooves.
According to the satellite unfolding mechanism for reducing sun wing shadows, the outer sliding rail is fixed on the side wall of the sun wing body, and the side wall is connected with the compression release mechanism.
By adopting the technical scheme, the utility model has the following advantages and positive effects compared with the prior art:
1. through the connection of wing body expansion mechanism and slip subassembly, realize after the release of solar wing main part, solar wing main part keeps away from the star for solar wing main part is not in the star and shelters from the shadow area that produces, improves the whole utilization ratio of battery on the solar wing main part from this.
2. The wing body unfolding mechanism is matched with the second locking/releasing unit, so that after the solar wing body rotates to a releasing position, the connecting rod is separated from the tripping slot, and the solar wing body is far away from the star under the action of the spring; the structure is simple and convenient.
Drawings
FIG. 1 is a schematic view showing the overall structure of a satellite deployment mechanism in a retracted position for reducing solar wing shadows according to an embodiment of the present utility model
FIG. 2 is a schematic view showing the overall structure of a release position of a satellite deployment mechanism for reducing solar wing shadows according to an embodiment of the present utility model
FIG. 3 is a schematic view of a satellite deployment mechanism for reducing solar wing shadows and a second lock/release unit according to an embodiment of the present utility model
FIG. 4 is a schematic diagram of a slip assembly of a satellite deployment mechanism for reducing solar wing shadows according to an embodiment of the present utility model
FIG. 5 is a schematic view of a structure of a connection torsion plate of a satellite deployment mechanism for reducing solar wing shadows according to an embodiment of the present utility model
Reference numerals illustrate: 1. a star; 2. a solar wing body; 3. a wing body unfolding mechanism; 4. a slip assembly; 5. a first locking/releasing unit; 6. a second locking/releasing unit; 7. an inner slide bar; 8. an outer slide rail; 9. an elastic member; 10. a fixed block; 11. a rotating block; 12. rotating the torsion sheet; 13. releasing the block; 14. a connecting rod; 15. tripping and slotting; 16. a positioning pin; 17. positioning holes; 18. a fixed in place pin; 19. and rotating the pin in place.
Detailed Description
A satellite deployment mechanism for reducing sun wing shadows according to the present utility model is described in further detail below with reference to the drawings and detailed description. The advantages and features of the present application will become more fully apparent from the following description and appended claims.
Referring to FIGS. 1 and 2, in one embodiment, the present utility model provides a satellite deployment mechanism for reducing sun wing shadows, at least one solar wing assembly disposed on a side wall of a star 1; the solar wing assembly comprises a solar wing main body 2, a wing body unfolding mechanism 3, a sliding assembly 4, a first locking/releasing unit 5 and a second locking/releasing unit 6; wherein, when the solar wing main body 2 is contracted and positioned on the side wall of the star 1, the solar wing main body is in a contracted position; when the solar wing main body 2 is unfolded on the side wall of the star body 1, the solar wing main body 2 and the star body 1 form an included angle of 90 degrees, and the solar wing main body is a release position.
The fixed end of the wing body unfolding mechanism 3 is arranged on the side wall of the star 1, and the rotating end of the wing body unfolding mechanism 3 is connected with the fixed part of the sliding component 4 and is used for driving the sliding component 4 to swing from the contracted position to the release position; the solar wing body 2 is arranged at the sliding part of the sliding assembly 4, so that the solar wing body 2 is far away from the star 1 when in the release position.
The first locking/releasing unit 5 is provided at a side wall of the star 1, and in the retracted position, the first locking/releasing unit 5 is locked to the solar wing main body 2.
The fixed end of the second locking/releasing unit 6 is arranged at the fixed end of the star 1 or the wing body unfolding mechanism 3, and in the contracted position, the locking end of the second locking/releasing unit 6 is connected with the solar wing main body 2; in the release position, the solar wing body 2 is disengaged from the second locking/releasing unit 6, i.e. the unlocking position of the second locking/releasing unit 6 corresponds to the release position.
The main working procedure of the satellite unfolding mechanism is as follows: is fixed to the solar wing body 2 by the first locking/releasing unit 5 such that the solar wing body 2 is in a retracted position; when the first locking/releasing unit 5 releases the solar wing body 2, the solar wing body 2 is driven by the wing body unfolding mechanism 3 by means of the sliding component to rotate; the second locking/releasing unit 6 is used to prevent the movement of the solar wing body 2 on the slip assembly 4 before the solar wing body 2 is rotated to the release position; and when the solar wing body 2 is transferred to the release position, the second locking/releasing unit 6 releases the solar wing body 2, so that the solar wing body 2 is far away from the star 1 under the action of the sliding component 4.
Through the scheme, the solar wing main body 2 is not in the shadow area generated by shielding of the star 1, so that the influence of the shadow on the solar wing main body 2 is reduced, and the overall utilization rate of the battery on the solar wing main body 2 is improved.
The specific structure of the satellite deployment mechanism for reducing solar wing shadows of the present embodiment is further described below:
referring to fig. 3 and 4, in the present embodiment, the sliding assembly 4 includes an inner slide 7 that is a fixed portion, an outer slide rail 8 that is a sliding portion, and an elastic member 9;
one end of the inner slide bar 7 is arranged at the rotating end of the wing body unfolding mechanism 3, the outer slide rail 8 is fixed on the side wall of the solar wing main body 2, and the outer slide rail 8 is connected with the inner slide bar 7 in a sliding manner; the elastic member 9 is disposed between the rotating end of the wing body unfolding mechanism 3 and the outer slide rail 8, and when in the retracted position, the elastic member 9 is in a rebound state.
The length direction of the inner slide rod 7 is vertical to the rotating end rotating shaft of the wing body unfolding mechanism 3; when the wing body unfolding mechanism 3 rotates to the release position, the solar wing body 2 is separated from the second locking/releasing unit 6, and the outer slide rail 8 slides on the inner slide rail 7 under the pushing action of the elastic piece 9, so that the solar wing body 2 is far away from the star body 1.
Referring to fig. 1, 3 and 4, in the present embodiment, the wing body deployment mechanism 3 includes a plurality of fixed blocks 10, and a rotating block 11 and a rotating torsion piece 12 corresponding to the fixed blocks 10;
referring to fig. 5, a rotating block 11 is rotatably coupled to a fixed block 10, and bumps are provided on the rotating block 11; the rotary torsion plate 12 is in an S-shaped structure, one end of the rotary torsion plate 12 is fixed on the fixed block 10, and the other end of the rotary torsion plate 12 slides on the salient point; in the retracted position, the rotary knob 12 is in a rebound state; in the unfolding process, the arc-shaped surface of the rotary torsion piece 12 drives the convex points to rotate, the convex points drive the rotary block 11 to move, and the possibility that the convex points are separated from the rotary torsion piece 12 is reduced under the arrangement of the S-shaped structure.
Wherein the side wall of the rotating block 11 and the end part of the inner slide rod 7 are fixed.
The number of the fixing blocks 10 in each wing body unfolding mechanism is two, and when the wing body unfolding mechanism is in a contracted position, the fixing blocks 10 are positioned on two sides of the solar wing; the rotating torsion piece 12 is arranged on the rotating shaft between the rotating block 11 and the fixed block 10 in a penetrating way, so that the rotating torsion piece 12 rotates more stably.
Referring to fig. 5, the fixed block 10 is provided with a fixed-in-place pin 18, the rotating block 11 is provided with a rotating-in-place pin 19, and in the release position, the fixed-in-place pin 18 is clamped with the rotating-in-place pin 19 to fix the rotating block; the rotation is achieved at 90 °.
Referring to fig. 1 and 2, in the present embodiment, the first locking/releasing unit 5 includes a compression release mechanism main body, a rope structure, and a fusing structure;
the compression release mechanism main body is fixed on the side wall of the star 1, and the rope structure is arranged between the solar wing main body 2 and the compression release mechanism main body when the solar wing main body is in the contracted position; the fusing structure is arranged on the compaction release mechanism main body and is used for fusing the rope structure.
Further provided, the first locking/releasing unit 5 is a compression release mechanism used in the satellite field in the prior art; the main function is to release the solar wing main body 2; when the solar wing body 2 needs to be released, the rope of the rope structure is fused by the fusing structure.
Referring to fig. 1 and 3, in the present embodiment, the rotation axis of the rotation block 11 is the rotation axis of the solar wing body 2, and defines the rotation axis of the solar wing body 2 as a base line.
The second locking/releasing unit 6 comprises at least one releasing block 13, which is a fixed end, a connecting rod 14, which is a locking end; the releasing block 13 is fixed on the side wall of the star 1, the connecting rod 14 is fixed on the solar wing main body 2, and the length direction of the connecting rod 14 is parallel to the foundation line.
The release block 13 is provided with a release slot 15, the release slot 15 is arranged by taking a basic line as an axis, and one end of the release slot 15 is provided with an opening; in the retracted position, the connecting rod 14 is positioned in the trip slot 15; in the release position, the connecting rod 14 is located at the opening of the trip slot 15.
Further, the number of the releasing blocks 13 in each second locking/releasing unit 6 is two, the releasing blocks 13 are respectively located between the fixed block 10 and the solar wing main body 2, and the end parts of the connecting rods 14 are respectively located in the corresponding tripping grooves 15.
Wherein, the working process is as follows: before the solar wing main body 2 rotates to the release position, the connecting rods 14 are positioned in the release grooves 15, so that the solar wing main body 2 cannot slide on the inner slide rod 7 in the rotating process; when the solar wing main body 2 rotates to the release position, the connecting rod 14 moves to the opening end of the release slot 15, and then the connecting rod 14 is separated from the release block 13 under the pushing of the elastic piece 9; the solar wing body 2 will move on the inner slide bar 7 without the constraint of the second locking/releasing unit 6.
Referring to fig. 4, in the present embodiment, the elastic member 9 is a spring sleeved on the inner slide rod 7, one end of the spring is fixed to the side wall of the rotating end of the wing deployment mechanism 3, and the other end of the spring abuts against the end of the outer slide rail 8 facing the star 1.
The spring is further arranged to be compressed before the solar wing main body 2 is contracted to the release position, and has a certain elastic force; this is so that in the release position the spring is sprung back pushing the outer slide rail 8.
In another embodiment, the elastic member 9 may be disposed between the inner slide bar 7 and the outer slide bar 8; the spring is positioned in the outer slide rail 8, one end of the spring is fixed at the end of the outer slide rail 8 facing the star 1, and the other end of the spring is fixed at the end of the inner slide bar 7 facing away from the star 1; and the spring is in a stretched state before the contracted position to the released position.
Referring to fig. 4, in this embodiment, at least one positioning pin 16 is disposed at the end of the inner slide rod 7 facing away from the rotating end of the wing body unfolding mechanism 3, and a positioning hole 17 is formed on the inner wall of the outer slide rail 8 for locking the solar wing body 2 to a preset sliding position;
when in the release position, the solar wing main body is far away from the star body to a preset sliding position, and the positioning pin 16 is clamped in the positioning hole 17.
The positioning pin 16 is arranged at one end of the inner slide rod 7 far away from the rotating block 11, and the positioning hole 17 is arranged at one end of the outer slide rail 8 near to the rotating block 11; through the positioning holes 17 and the positioning pins 16, the inner slide rod 7 and the outer slide rail 8 are fixed after the solar wing main body 2 is pushed by the spring, so that the solar wing main body 2 is more stable;
the distance of the designated position can be more equal to the size of the star 1, and the shadow-generating area is calculated to be reasonably set.
In this embodiment, the outer sliding rail 8 is fixed on the solar wing body 2 and connected to the side wall of the compression release mechanism, that is, when in the retracted position, the outer sliding rail 8 is disposed towards one side of the star 1, so as to provide as many panels as possible on the solar wing body 2.
The satellite deployment mechanism principle for reducing sun wing shadows according to the present embodiment will be described below: when the solar wing is in the contracted position, the first locking/releasing unit 5 is fixed on the solar wing main body 2, the fusing structure promotes the rope in the rope structure to fuse, so that the solar wing main body 2 is separated from the first locking/releasing unit 5, and the rotating block 11 rotates and drives the sliding component 4 and the solar wing main body 2 to move under the acting force of the rotating torsion piece 12;
before the retracted position to the release position, the connecting rod 14 is positioned inside the release block 13 until the solar wing body 2 moves to the release position;
when the solar wing main body 2 is located at the release position, the connecting rod 14 is located at the opening of the release slot 15, and then the outer slide rail 8 is pushed under the action of the spring to move on the inner slide rail 7, so that the solar wing main body 2 is driven to be far away from the star 1 until reaching the preset sliding position.
The embodiments of the present application are described in detail above with reference to the drawings, but the present application is not limited to the above embodiments. Even if various changes are made to the present utility model, it is intended that such changes fall within the scope of the claims and the equivalents thereof.
Claims (10)
1. A satellite deployment mechanism for reducing sun wing shadows, comprising:
a star;
at least one solar wing assembly arranged on the side wall of the star; the solar wing assembly includes: the solar wing comprises a solar wing main body, a wing body unfolding mechanism, a sliding assembly, a first locking/releasing unit and a second locking/releasing unit;
the fixed end of the wing body unfolding mechanism is arranged on the side wall of the star body, and the rotating end of the wing body unfolding mechanism is connected with the fixed part of the sliding component and is used for driving the sliding component to swing from a contracted position to a release position;
the sliding part of the sliding component is provided with the solar wing main body and is used for driving the solar wing main body to slide and keep away from the star;
the first locking/releasing unit is arranged on the side wall of the star body, and in the contracted position, the first locking/releasing unit is locked on the solar wing main body;
the fixed end of the second locking/releasing unit is arranged at the fixed end of the star or the wing body unfolding mechanism, and in the contracted position, the locking end of the second locking/releasing unit is connected with the solar wing main body; the unlocking position of the second locking/releasing unit corresponds to the releasing position.
2. The satellite deployment mechanism for reducing solar wing shadows according to claim 1, wherein: the sliding component comprises an inner sliding rod which is a fixed part, an outer sliding rail which is a sliding part and an elastic piece;
one end of the inner slide rod is arranged at the rotating end of the wing body unfolding mechanism, the outer slide rail is fixed on the side wall of the solar wing main body, and the outer slide rail is connected with the inner slide rod in a sliding manner;
the elastic piece is arranged between the rotating end of the wing body unfolding mechanism and the outer sliding rail,
or, the elastic piece is arranged between the inner slide rod and the outer slide rail.
3. The satellite deployment mechanism for reducing solar wing shadows according to claim 2, wherein: the wing body unfolding mechanism comprises a plurality of fixed blocks, and a rotating block and a rotating torsion piece which correspond to the fixed blocks;
the rotating block is rotationally connected with the fixed block; the rotating block is provided with convex points, the rotating torsion piece is of an S-shaped structure, one end of the rotating torsion piece is fixed on the fixed block, and the other end of the rotating torsion piece slides on the convex points and drives the convex points to drive the rotating block to move;
the side wall of the rotating block is fixed with the end part of the inner slide rod.
4. The satellite deployment mechanism for reducing solar wing shadows according to claim 3, wherein: the fixed block is provided with a fixed in-place pin, the rotating block is provided with a rotating in-place pin, and when the fixed block is in a release position, the fixed in-place pin is clamped with the rotating in-place pin to fix the rotating block.
5. The satellite deployment mechanism for reducing solar wing shadows according to claim 2, wherein: the first locking/releasing unit comprises a compression release mechanism body, a rope structure and a fusing structure;
the compaction release mechanism main body is fixed on the side wall of the star, and the rope structure is arranged between the solar wing main body and the compaction release mechanism main body when the solar wing main body is in a contracted position; the fusing structure is arranged on the compaction release mechanism main body and used for fusing the rope structure.
6. The satellite deployment mechanism for reducing solar wing shadows according to claim 3, wherein: the rotation axis of the rotation block is the rotation axis of the solar wing main body, and the rotation axis of the solar wing main body is defined as a basic line;
the second locking/releasing unit comprises at least one releasing block which is a fixed end and a connecting rod which is a locking end; the release block is fixed on the side wall of the star, the connecting rod is fixed on the solar wing main body, and the length direction of the connecting rod is parallel to the foundation line;
the release block is provided with a release slot, the release slot is arranged by taking the basic line as an axis, and one end of the release slot is provided with an opening; when the connecting rod is in the contracted position, the connecting rod is positioned in the tripping groove; when in the release position, the connecting rod is positioned at the opening of the tripping slot.
7. The satellite deployment mechanism for reducing solar wing shadows according to claim 2, wherein: the elastic piece is a spring sleeved on the inner slide rod, one end of the spring is fixed on the side wall of the rotating end of the wing body unfolding mechanism, and the other end of the spring is abutted to the end part of the outer slide rail, which faces the star body.
8. The satellite deployment mechanism for reducing solar wing shadows according to claim 2, wherein: the inner slide rod is provided with at least one positioning pin at the end part deviating from the rotating end of the wing body unfolding mechanism, and the inner wall of the outer slide rail is provided with a positioning hole corresponding to the positioning pin and used for locking the solar wing body to a preset sliding position.
9. The satellite deployment mechanism for reducing solar wing shadows according to claim 6, wherein: the number of the fixing blocks in each wing body unfolding mechanism is two, and when the solar wing body is in a contracted position, the fixing blocks are positioned on two sides of the solar wing body;
the number of the release blocks in each second locking/releasing unit is two, the release blocks are respectively positioned between the fixed blocks and the solar wing main body, and the end parts of the connecting rods are respectively positioned in the corresponding tripping grooves.
10. The satellite deployment mechanism for reducing solar wing shadows according to claim 5, wherein: the outer slide rail is fixed on the solar wing main body and connected to the side wall of the compression release mechanism.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321719760.9U CN220010090U (en) | 2023-07-03 | 2023-07-03 | Satellite unfolding mechanism for reducing sun wing shadows |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321719760.9U CN220010090U (en) | 2023-07-03 | 2023-07-03 | Satellite unfolding mechanism for reducing sun wing shadows |
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| Publication Number | Publication Date |
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| CN220010090U true CN220010090U (en) | 2023-11-14 |
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| CN202321719760.9U Active CN220010090U (en) | 2023-07-03 | 2023-07-03 | Satellite unfolding mechanism for reducing sun wing shadows |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117775317A (en) * | 2024-01-05 | 2024-03-29 | 银河航天(北京)网络技术有限公司 | Solar wing driving device, solar wing unfolding equipment and satellite |
-
2023
- 2023-07-03 CN CN202321719760.9U patent/CN220010090U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117775317A (en) * | 2024-01-05 | 2024-03-29 | 银河航天(北京)网络技术有限公司 | Solar wing driving device, solar wing unfolding equipment and satellite |
| CN117775317B (en) * | 2024-01-05 | 2024-10-22 | 银河航天(北京)网络技术有限公司 | Solar wing driving device, solar wing unfolding equipment and satellite |
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