CN115675928A - Scissors type extension mechanism for extension of solar wing based on spring pin locking - Google Patents
Scissors type extension mechanism for extension of solar wing based on spring pin locking Download PDFInfo
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- CN115675928A CN115675928A CN202211106446.3A CN202211106446A CN115675928A CN 115675928 A CN115675928 A CN 115675928A CN 202211106446 A CN202211106446 A CN 202211106446A CN 115675928 A CN115675928 A CN 115675928A
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
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- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
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Abstract
The present invention provides a scissor-type extension mechanism for extension of solar wings based on spring pin locking, the left synchronizing assembly is arranged on the left bracket base, and the right synchronizing assembly is arranged on the right bracket base; one end of the extension mechanism is connected with the left synchronous component, the other end of the extension mechanism is connected with the right synchronous component, and the left synchronous component and the right synchronous component are used for ensuring that the extension mechanism can extend so as to enable the solar wing to extend synchronously; the locking mechanism is arranged in the extension mechanism and used for limiting the extension mechanism not to extend any more after reaching a limited position in the unfolding process. The left synchronizing assembly is matched with the right synchronizing assembly to enable the stretching mechanism to stretch so that the solar wing stretches, and when the stretching mechanism stretches to a set position, the locking mechanism limits the continuous movement of the stretching mechanism; the locking mechanism is driven passively, so that the stretching mechanism is guaranteed to be kept in a stretched stable state, and the solar wing locking mechanism is different from the existing active drive, and reduces the mass of the solar wing.
Description
Technical Field
The invention relates to the field of sun wing extension mechanisms, in particular to a scissor type extension mechanism based on spring pin locking and used for sun wing extension.
Background
For a spacecraft, a solar wing is a main energy supply device, the reliability of a deployable mechanism of the solar wing in the process of unlocking the solar wing directly determines the success or failure of a task, and internationally, the locking mode of a solar wing extension mechanism often needs to be locked and limited by designing a locking device.
The solar wing is locked in the prior art by an active drive locking device, the active drive needs to be provided with an active device, the weight of the solar wing is increased, and the increased weight in the field of outer space can generate larger cost.
To solve the above problems, the present invention provides a scissor type extension mechanism based on spring pin locking for extension of solar wings
Disclosure of Invention
Aiming at solving the problem of the solar wing extending mechanism in the prior art
Unmanned aerial vehicle is carrying out data acquisition's in-process, and control center needs the direction and the angle of regulation and control mount device in carrying out data acquisition for acquire required data, mount device has the condition that the adjustment is malfunctioning in carrying out the adjustment process, influences the collection of data. Therefore, the invention provides a test tool for an unmanned aerial vehicle mounting device.
A scissor-type extension mechanism for extension of solar wings based on spring pin locking, comprising: the device comprises a left bracket seat, a right bracket seat, an extension mechanism, a synchronization mechanism and a locking mechanism;
the synchronizing mechanism comprises a left synchronizing component and a right synchronizing component, the left synchronizing component is mounted on the left support seat, and the right synchronizing component is mounted on the right support seat;
one end of the extending mechanism is connected with the left synchronous component, the other end of the extending mechanism is connected with the right synchronous component, and the left synchronous component and the right synchronous component are used for ensuring that the extending mechanism can extend to enable the solar wing to extend synchronously;
the locking mechanism is arranged in the extension mechanism and used for limiting the extension mechanism not to extend any more after reaching a limited position in the unfolding process.
On the basis of the above scheme and as a preferable scheme of the scheme: the extension mechanism comprises a long rod component and a short rod component;
the long rod assembly comprises a first long rod and a second long rod, the centers of the first long rod and the second long rod are rotatably connected through a first hinge piece, the first long rod is provided with a first left end and a first right end, and the second long rod is provided with a second left end and a second right end;
the short rod assembly comprises a first left short rod, a second left short rod, a first right short rod and a second right short rod, one end of the first short rod is hinged to the first left end, the other end of the first short rod is connected with the left synchronizing assembly, one end of the second left short rod is hinged to the second left end, the other end of the second left short rod is connected with the left synchronizing assembly, one end of the first right short rod is hinged to the first right end, the other end of the first right short rod is connected with the right synchronizing assembly, and the second right short rod is hinged to the second right end, the other end of the second right short rod is connected with the right synchronizing assembly.
On the basis of the above scheme and as a preferred scheme of the scheme: the locking mechanism is arranged at the joint of the first left short rod and the first long rod, the joint of the first right short rod and the second long rod, the joint of the second left short rod and the first long rod or the joint of the second right short rod and the second long rod.
On the basis of the above scheme and as a preferable scheme of the scheme: the locking mechanism comprises a pin, a micro spring and a pin groove; the first short rod is provided with a pin hole for the pin to stretch, and the first short rod is provided with a limiting seat; the pin is arranged in the pin hole, and the bottom of the pin is provided with a telescopic groove; one end of the micro spring is fixed on the limiting seat, and the other end of the micro spring is arranged in the telescopic groove; the pin slot is positioned on the lower surface of the first long rod; when the first short rod is in limit fit with the first long rod, the pin is positioned in the pin groove to limit the relative rotation of the first short rod and the first long rod.
On the basis of the above scheme and as a preferable scheme of the scheme: the lower surface of the first long rod is provided with an inclined surface which is used for being matched with the pin to rotate;
the top of the pin is of an arc-shaped structure.
On the basis of the above scheme and as a preferred scheme of the scheme: the left synchronizing assembly comprises a first left rotating tooth and a second left rotating tooth, the first left rotating tooth and the second left rotating tooth are rotatably mounted on the left support base, the first left rotating tooth and the second left rotating tooth are in a meshed state, the first left rotating tooth is fixedly connected with a first left short rod, and the second left rotating tooth is fixedly connected with a second left short rod.
On the basis of the above scheme and as a preferable scheme of the scheme: the right synchronizing assembly comprises a first right rotating tooth and a second right rotating tooth, the first right rotating tooth and the second right rotating tooth are rotatably mounted on the right bracket base, the first right rotating tooth and the second right rotating tooth are in a meshed state, the first right rotating tooth is fixedly connected with a first right short rod, and the second right rotating tooth is fixedly connected with a second right short rod.
On the basis of the above scheme and as a preferable scheme of the scheme: the left bracket base is provided with a left connecting lug, and the connecting lug is used for mounting the first left rotating tooth and the second left rotating tooth;
and a right connecting lug is arranged on the right bracket seat and used for installing the first right rotating tooth and the second right rotating tooth.
On the basis of the above scheme and as a preferable scheme of the scheme: the first left short rod, the second left short rod, the first right short rod and the second right short rod keep a parallelogram structure in the motion process.
Compared with the prior art, the technical scheme provided by the application has the following beneficial effects:
the left support seat or the right support seat is fixedly arranged on the spacecraft, the corresponding right support seat or the left support seat is a movable support, the left synchronizing assembly is matched with the right synchronizing assembly to enable the stretching mechanism to stretch so that the solar wing can stretch, and when the stretching mechanism stretches to a set position, the locking mechanism limits the continuous movement of the stretching mechanism; the locking mechanism is driven passively, so that the stretching mechanism is guaranteed to be kept in a stretched stable state, the solar wing is different from the existing active drive, and the mass of the solar wing is reduced.
The parallelogram structure that first left quarter butt, second left quarter butt, first right quarter butt and second right quarter butt are constituteed can make left synchronizing assembly and right synchronizing assembly when acting on, and extension mechanism can be steady extend.
First stock carries out the pivoted in-process with first left quarter butt, and the top of pintle groove removal to the pintle on the first stock, and the pintle top enters into the pintle inslot, prescribes a limit to the rotation of first stock and first left quarter butt, and then prescribes a limit to the rotation of extending the mechanism. The lower surface of the first long rod is pressed on the pin, the first long rod and the first left short rod are matched and rotated in the process, the inclined surface can be convenient for downwards pressing the pin to move downwards, and the arc-shaped structure at the top of the pin can help the first long rod to rotate in the matching mode with the first left short rod.
Drawings
The present invention will be described in further detail with reference to the accompanying drawings and specific embodiments.
FIG. 1 is a perspective view of the overall structure of the present invention;
FIG. 2 is a schematic cross-sectional view of the locking mechanism of the present invention;
FIG. 3 is an enlarged view of the junction between the first left short rod and the first long rod according to the present invention;
FIG. 4 is an enlarged view of the left synchronizing assembly and the left bracket base according to the present invention.
In the figure: 11. a left support base; 111. a left engaging lug; 12. a right support base; 21. a first left short bar; 211. a limiting seat; 22. a first right short bar; 31. a second left short bar; 32. a second right short bar; 41. a first long rod; 411. an inclined surface; 42. a second long rod; 51. a left synchronization component; 511. a first left rotating tooth; 512. a second left rotating tooth; 52. a right synchronization component; 61. a pin; 611. a telescopic groove; 62. a pin slot; 63. a micro-spring; 7. a first hinge member.
Detailed Description
To make the objects, technical solutions and advantages of the present invention more apparent, embodiments of the present invention will be described in detail below with reference to the accompanying drawings. However, it will be appreciated by those of ordinary skill in the art that numerous technical details are set forth in the embodiments of the present invention in order to provide a better understanding of the present application. However, the technical solutions claimed in the present application can be implemented without these technical details and various changes and modifications based on the following embodiments.
For a better illustration of the invention, the invention is described in detail below with reference to the accompanying figures 1-4.
Referring to fig. 1, a scissor-type extension mechanism for extension of solar wings based on locking of a spring pin 61 comprises: a left bracket base 11, a right bracket base 12, an extension mechanism, a synchronization mechanism and a locking mechanism; the synchronizing mechanism comprises a left synchronizing component 51 and a right synchronizing component 52, wherein the left synchronizing component 51 is installed on the left support base 11, and the right synchronizing component 52 is installed on the right support base 12; one end of the extending mechanism is connected with the left synchronizing component 51, the other end of the extending mechanism is connected with the right synchronizing component 52, and the left synchronizing component 51 and the right synchronizing component 52 are used for ensuring that the extending mechanism can extend so as to enable the solar wing to extend synchronously; the locking mechanism is arranged in the extension mechanism and used for limiting the extension mechanism not to extend any more after reaching a limited position in the unfolding process. In the actual use process, according to the installation mode of the technical scheme, the left support base 11 is fixedly installed on the spacecraft, the right support base 12 is a movable support, the left synchronizing assembly 51 is matched with the right synchronizing assembly 52 to enable the extending mechanism to extend so as to enable the solar wing to extend, and when the extending mechanism extends to a set position, the locking mechanism limits the continuous movement of the extending mechanism; the locking mechanism is driven passively, so that the stretching mechanism is kept in a stable unfolding state, and the solar wing is different from the existing active drive, and the mass of the solar wing is reduced; in another installation mode of the technical scheme, the right support base 12 is fixedly installed on the spacecraft, the left support base 11 is a movable support, the left synchronizing assembly 51 is matched with the right synchronizing assembly 52 to enable the stretching mechanism to stretch so that the solar wing can stretch, and when the stretching mechanism stretches to a set position, the locking mechanism limits the continuous movement of the stretching mechanism; from this, this technical scheme does not restrict left branch frame seat 11 and right branch frame seat 12 and spacecraft's fixed, installs according to actual demand, improves this technical scheme's application range.
Referring to fig. 1, a specific example of the present embodiment, the extension mechanism includes a long rod assembly and a short rod assembly; wherein, the long rod assembly comprises a first long rod 41 and a second long rod 42, the centers of the first long rod 41 and the second long rod 42 are rotatably connected through a first hinge member 7, the first long rod 41 has a first left end and a first right end, and the second long rod 42 has a second left end and a second right end; wherein, the quarter butt subassembly includes first left quarter butt 21, second left quarter butt 31, first right quarter butt 22 and second right quarter butt 32, and first quarter butt one end articulates in first left end, and left synchronizing assembly 51 is connected to the other end, and second left quarter butt 31 one end articulates in the second left end, and left synchronizing assembly 51 is connected to the other end, and first right quarter butt 22 one end articulates in first right-hand member, and right synchronizing assembly 52 is connected to the other end, and second right quarter butt 32 articulates in the second right-hand member, and right synchronizing assembly 52 is connected to the other end. In this technical scheme, first articulated elements 7 makes the center of first stock 41 and second stock 42 rotate for first stock 41 and second stock 42 form scissors formula structure. Specifically, the first hinge member 7 in this embodiment is a first rotating shaft, and the first rotating shaft penetrates through the first long rod 41 and the second long rod 42, and the first rotating shaft enables the first long rod 41 and the second long rod 42 to rotate. It should be noted that, in other embodiments of the present technical solution, the number of the long poles of the long pole assembly is a multiple of two, each two long poles are a cross unit, adjacent cross units are hinged together, and the structure in each cross unit is hinged together in a cross manner. It should be noted that, in the present embodiment, the first left short bar 21, the second left short bar 31, the first right short bar 22 and the second right short bar 32 maintain the parallelogram structure during the movement. The parallelogram structure that first left quarter butt 21, second left quarter butt 31, first right quarter butt 22 and second right quarter butt 32 in this embodiment constitute can make left synchronizing assembly 51 and right synchronizing assembly 52 when acting on, and the extension mechanism can be steady extend.
In the practical use process, when left support seat 11 fixed mounting on the spacecraft, right support seat 12 is the movable support, left synchronizing assembly 51 is initiative runner assembly, left synchronizing assembly 51 drives first left quarter butt 21 and second left quarter butt 31 and rotates, first left quarter butt 21 and second left quarter butt 31 drive first stock 41 and second stock 42 and carry out the extension motion, first stock 41 and second stock 42 make first right quarter butt 22 and second right quarter butt 32 carry out the extension motion, right synchronizing assembly 52 makes above-mentioned extension mechanism can keep stable extension.
In a specific example of the present embodiment, the locking mechanism is disposed at the connection between the first left short rod 21 and the first long rod 41, the connection between the first right short rod 22 and the second long rod 42, the connection between the second left short rod 31 and the first long rod 41, or the connection between the second right short rod 32 and the second long rod 42. It should be noted that in other embodiments, the locking mechanism is disposed at the rotational connection between the first long rod 41 and the second long rod 42. Therefore, the locking mechanism in the technical scheme is used for limiting the rotation of the stretching mechanism, so that when the stretching mechanism is stretched to a proper position, the rotation is stopped, and the stretching mechanism is kept stable.
Referring to fig. 2 and 3, a specific example of the present embodiment, the locking mechanism includes a pin 61, a micro spring 63, and a pin groove 62; the first left short rod 21 is provided with a pin 61 hole for the pin 61 to stretch, and the first left short rod 21 is provided with a limit seat 211; the pin 61 is arranged in the hole of the pin 61, and the bottom of the pin 61 is provided with a telescopic groove 611; one end of the micro spring 63 is fixed on the limiting seat 211, and the other end is arranged in the telescopic groove 611; the pin slot 62 is located on the lower surface of the first long rod 41; when the first left short rod 21 is in limit fit with the first long rod 41, the pin 61 is positioned in the pin groove 62 to limit the relative rotation of the first left short rod 21 and the first long rod 41. In practical use, during the rotation of the first long rod 41 and the first left short rod 21, the pin slot 62 on the first long rod 41 moves above the pin 61, the top of the pin 61 enters the pin slot 62, and the rotation of the first long rod 41 and the first left short rod 21, and further the rotation of the extension mechanism, is limited.
Referring to fig. 3, in the specific example of the present embodiment, the lower surface of the first long rod 41 is provided with an inclined surface 411, and the inclined surface 411 is used for matching with the pin 61 to rotate; the top of the pin 61 is of an arc-shaped structure. In the actual use, the lower surface of the first long rod 41 is pressed on the pin 61, and in the process of the cooperation rotation of the first long rod 41 and the first left short rod 21, the inclined surface 411 can facilitate the downward pressing of the pin 61 to move downward, and the arc-shaped structure at the top of the pin 61 can help the cooperation rotation of the first long rod 41 and the first left short rod 21. It should be noted that in other embodiments, the inclined surface 411 is provided on the contact surface that engages with the pin 61, depending on the position where the lock mechanism is installed.
Referring to fig. 4, in an example of the present invention, the left synchronizing assembly 51 includes a first left rotating tooth 511 and a second left rotating tooth 512, the first left rotating tooth 511 and the second left rotating tooth 512 are both rotatably mounted on the left bracket base 11, the first left rotating tooth 511 and the second left rotating tooth 512 are in a meshed state, the first left rotating tooth 511 is fixedly connected to the first left short rod 21, and the second left rotating tooth is fixedly connected to the second left short rod 31. The right synchronizing assembly 52 includes a first right-turning tooth and a second right-turning tooth, both of which are rotatably mounted on the right frame base 12, and the first right-turning tooth and the second right-turning tooth are in a meshed state, the first right-turning tooth is fixedly connected to the first right short rod 22, and the second right-turning tooth is fixedly connected to the second right short rod 32. It should be noted that, the structural diagram between the right synchronizing assembly and the right support base is not shown, and those skilled in the art can understand the structure between the right synchronizing assembly and the right support base by referring to the structural drawings of the left synchronizing assembly and the left support base.
Referring to fig. 4, in a specific example of the present embodiment, a left connecting lug 111 is disposed on the left bracket base 11, and the connecting lug is used for mounting the first left rotating tooth 511 and the second left rotating tooth 512; the right bracket base 12 is provided with a right connecting lug, and the right connecting lug is used for installing the first right rotating tooth and the second right rotating tooth.
The foregoing describes specific embodiments of the present invention. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes, modifications, or combinations may be made by those skilled in the art within the scope of the claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (9)
1. A scissor-type extension mechanism for extension of solar wings based on spring pin locking, comprising: the device comprises a left bracket base, a right bracket base, an extension mechanism, a synchronization mechanism and a locking mechanism;
the synchronizing mechanism comprises a left synchronizing component and a right synchronizing component, the left synchronizing component is mounted on the left support seat, and the right synchronizing component is mounted on the right support seat;
one end of the extending mechanism is connected with the left synchronizing assembly, the other end of the extending mechanism is connected with the right synchronizing assembly, and the left synchronizing assembly and the right synchronizing assembly are used for ensuring that the extending mechanism can extend so as to enable the solar wing to extend synchronously;
the locking mechanism is arranged in the extension mechanism and used for limiting the extension mechanism not to extend any more after reaching a limited position in the unfolding process.
2. A scissor extension mechanism based on spring pin locking for extension of solar wings according to claim 1, wherein the extension mechanism includes a long rod assembly and a short rod assembly;
the long rod assembly comprises a first long rod and a second long rod, the centers of the first long rod and the second long rod are rotatably connected through a first hinge piece, the first long rod is provided with a first left end and a first right end, and the second long rod is provided with a second left end and a second right end;
the short rod assembly comprises a first left short rod, a second left short rod, a first right short rod and a second right short rod, one end of the first short rod is hinged to the first left end, the other end of the first short rod is connected with the left synchronizing assembly, one end of the second left short rod is hinged to the second left end, the other end of the second left short rod is connected with the left synchronizing assembly, one end of the first right short rod is hinged to the first right end, the other end of the first right short rod is connected with the right synchronizing assembly, and the second right short rod is hinged to the second right end, the other end of the second right short rod is connected with the right synchronizing assembly.
3. A scissor extension mechanism based on spring pin locking for extension of solar wings according to claim 2, wherein the locking mechanism is provided at the junction of the first left short bar and the first long bar, at the junction of the first right short bar and the second long bar, at the junction of the second left short bar and the first long bar or at the junction of the second right short bar and the second long bar.
4. A scissor extension mechanism based on spring pin locking for extension of solar wings as claimed in claim 2, characterized in that the locking mechanism comprises a pin, a micro spring and a pin slot; the first short rod is provided with a pin hole for the pin to stretch, and the first short rod is provided with a limiting seat; the pin is arranged in the pin hole, and the bottom of the pin is provided with a telescopic groove; one end of the micro spring is fixed on the limiting seat, and the other end of the micro spring is arranged in the telescopic groove; the pin slot is positioned on the lower surface of the first long rod; when the first short rod is in limit fit with the first long rod, the pin is positioned in the pin groove to limit the relative rotation of the first short rod and the first long rod.
5. The scissor extension mechanism based on spring pin locking for extension of solar wings of claim 4, wherein the lower surface of the first long rod is provided with an inclined surface for cooperating with the pin to rotate;
the top of the pin is of an arc-shaped structure.
6. A scissor extension mechanism for solar wing extension based on spring pin locking according to claim 2, wherein the left synchronization assembly comprises a first left rotation tooth and a second left rotation tooth, the first left rotation tooth and the second left rotation tooth are both rotatably mounted on the left bracket base and are in a meshed state, the first left rotation tooth is fixedly connected with a first left short bar, and the second rotation tooth is fixedly connected with a second left short bar.
7. A scissor extension mechanism based on spring pin locking for solar wing extension according to claim 6, wherein the right synchronization assembly comprises a first right turning tooth and a second right turning tooth, the first right turning tooth and the second right turning tooth are both rotatably mounted on the right frame base, and the first right turning tooth and the second right turning tooth are in a meshed state, the first right turning tooth is fixedly connected with a first right short bar, and the second right turning tooth is fixedly connected with a second right short bar.
8. A scissor extension mechanism based on spring pin locking for extension of solar wings according to claim 7, wherein the left bracket base is provided with a left engaging lug for mounting of the first left turning tooth and the second left turning tooth;
and a right connecting lug is arranged on the right bracket base and used for mounting the first right rotating tooth and the second right rotating tooth.
9. A scissor extension mechanism based on spring pin locking for extension of solar wings according to claim 2, wherein the first left short bar, the second left short bar, the first right short bar and the second right short bar maintain a parallelogram structure during motion.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211106446.3A CN115675928A (en) | 2022-09-12 | 2022-09-12 | Scissors type extension mechanism for extension of solar wing based on spring pin locking |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211106446.3A CN115675928A (en) | 2022-09-12 | 2022-09-12 | Scissors type extension mechanism for extension of solar wing based on spring pin locking |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115675928A true CN115675928A (en) | 2023-02-03 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211106446.3A Pending CN115675928A (en) | 2022-09-12 | 2022-09-12 | Scissors type extension mechanism for extension of solar wing based on spring pin locking |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115675928A (en) |
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2022
- 2022-09-12 CN CN202211106446.3A patent/CN115675928A/en active Pending
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