Booms solar wing lifting mechanism

Abstract

The application provides a telescopic solar wing lifting mechanism, which comprises a base and a telescopic mechanism; the base is fixed to a star body; the telescopic mechanism is arranged in opposite telescopic modes at two ends; the telescopic mechanism is arranged in at least three circumferential modes and is hinged to the base; the telescopic mechanism rotates along the hinge towards the side away from the star body; and the end of the telescopic mechanism away from the base is hinged to a solar wing module; the telescopic mechanism comprises at least a first working state and a second working state; in the first working state, the telescopic mechanism is contracted, and the connecting end of the telescopic mechanism and the solar wing module is close to the star body; in the second working state, the telescopic mechanism is elongated, and the connecting end of the telescopic mechanism and the solar wing module is away from the star body. The application has the effect that the solar wing maintains a certain distance from the star body after being unfolded, the increased solar wing does not block the antenna, and the transmission of signals is ensured.

Description

Technical Field

[0001] This invention belongs to the field of aerospace technology, specifically relating to a telescopic solar wing lifting mechanism. Background Technology

[0002] As spacecraft become larger and their missions more complex, their demand for power systems is increasing. A powerful energy system is the most important foundation for spacecraft to perform its functions, which places higher demands on the deployment area of ​​solar panels.

[0003] Patent document CN120423071A discloses a two-dimensional flexible solar array with a single deployment of up to 100 square meters, comprising a flexible array based on an origami configuration that can be infinitely expanded laterally and / or longitudinally, an auxiliary deployment mechanism to assist in the deployment of the flexible array, and a deployment drive mechanism to drive the entire wing to deploy. The flexible array is composed of a first type of folding and unfolding unit located at both ends and a second type of folding and unfolding unit in the middle, connected by a piano hinge, so that the entire wing can be deployed from a folded state to achieve lateral and longitudinal directions in a single deployment. Both types of folding and unfolding units are double-vertex seven-fold origami units, and the flexible array has a single degree of freedom. The auxiliary deployment mechanism is connected to the first type of folding and unfolding unit and is connected to the deployment drive mechanism.

[0004] Although the configuration in patent document CN120423071A can increase the solar array's deployment area, this increase will inevitably obstruct the antenna on the satellite and reduce its fundamental frequency. If it is to increase the solar array's area while ensuring signal transmission, the solar array deployment mechanism needs to have the function of lifting the solar array to a certain distance away from the satellite to avoid antenna obstruction.

[0005] To ensure the solar array maintains a certain distance from the celestial body after deployment, preventing the enlarged solar array from obstructing the antenna and guaranteeing signal transmission, this invention designs a telescopic solar array lifting mechanism, thus solving the aforementioned problems. Summary of the Invention

[0006] In view of the deficiencies in the prior art, the purpose of this invention is to provide a telescopic solar panel lifting mechanism.

[0007] According to the present invention, a telescopic solar panel lifting mechanism includes: a base and a telescopic mechanism; The base is fixed to the star, and the two ends of the extension rod mechanism are relatively telescopic. The extension rod mechanism has at least three circumferentially arranged and hinged to the base. The extension rod mechanism rotates along the hinge point toward the side away from the star. The end of the extension rod mechanism away from the base is hinged to the solar panel module. The extension mechanism includes at least a first working state and a second working state. In the first working state, the extension mechanism is retracted and the connection end of the extension mechanism with the solar array module is close to the star. In the second working state, the extension mechanism is extended and the connection end of the extension mechanism with the solar array module is away from the star.

[0008] Preferably, the extension mechanism includes a sleeve, an extension rod, a bushing, and a drive device; The sleeve is arranged in at least three circumferential directions and hinged to the base; the bushing is received and fixed to the end of the sleeve away from the base; the extension rod is received and slidably connected to the bushing, and the end of the extension rod near the base can pass through the inside of the sleeve; The drive unit is located inside the sleeve and connected to the extension rod. The drive unit drives the extension rod away from the base.

[0009] Preferably, the driving device includes a passive driving structure, which includes a spring housed inside a sleeve. One end of the spring abuts against the inner wall of the sleeve near the base, and the other end abuts against the extension rod, driving the extension rod away from the base.

[0010] Preferably, the driving device includes an active driving structure, which includes a linear motor, a lead screw, a threaded sleeve, and a slider. The linear motor is fixed to the sleeve; the lead screw is rotatably connected to the sleeve and coaxially fixed to the output shaft of the linear motor; the slider is fixed to the extension rod and slides linearly along the axial direction of the sleeve; the threaded sleeve is coaxially fixed to the extension rod and screwed to the lead screw; the linear motor rotates to drive the threaded sleeve to move the extension rod away from the base.

[0011] Preferably, a torsion spring is provided at the hinge point between the base and the sleeve, and a shaft is formed on the base through which the torsion spring passes and positions. One end of the torsion spring abuts against the base, and the other end abuts against the sleeve, driving the sleeve to rotate toward the side away from the star.

[0012] Preferably, a first locking mechanism is provided between the bushing and the extension rod. When the extension rod is located at the end of the sleeve away from the base, the first locking mechanism is used to fix the bushing and the extension rod. A second locking mechanism is provided between the base and the sleeve. When the sleeve is rotated to the side away from the star, the second locking mechanism is used to fix the base and the sleeve.

[0013] Preferably, the first locking mechanism includes a first pin, a first insertion hole, and a first spring. The first pin is axially perpendicular to the extension rod and is slidably connected to one side of the bushing along the axial direction. The first insertion hole is opened at one end of the extension rod near the base. The first spring is connected between the first pin and the bushing and drives the first pin to insert into the first insertion hole.

[0014] Preferably, the second locking mechanism includes a second insert plate, a second slot, and a second spring. The second insert plate extends radially along the hinge axis between the sleeve and the base, and is slidably connected to one end of the sleeve near the base along its own extension direction. The second slot is opened in the base, and the opening direction is radially toward the hinge axis between the sleeve and the base. The second spring is connected between the sleeve and the second insert plate, and the second spring drives the second insert plate to be inserted into the second slot.

[0015] Preferably, a clamping structure is fitted around the extension rod mechanism and the outer side of the solar wing module. The clamping structure abuts against the extension rod mechanism and the solar wing module near the surface of the star, and the clamping structure is movably connected to the surface of the star.

[0016] Preferably, the base is fixed to the surface of the star by bolts, and four sleeves are arranged around the base. The solar panel module is rectangular, and the four corners of the rectangle are connected to four extension rods. Among the four sleeves, two sleeves are arranged in opposite directions around the base, and the other two are located on the same side of the sleeves arranged in opposite directions. The four sleeves are symmetrically arranged along the two sleeves arranged in opposite directions.

[0017] Compared with the prior art, the present invention has the following beneficial effects: 1. At least three circumferentially hinged extension rod mechanisms work together to extend and rotate, enabling the solar array module to switch from a retracted state close to the star to a working state far away from the star, reserving sufficient space for signal transmission of the star antenna.

[0018] 2. The dual locking mechanism and multi-strut distribution design make the structure extremely stable after deployment, and can maintain its working state for a long time.

[0019] 3. The drive method is optional, combining passive and active modes to adapt to different working conditions and provide high flexibility; the torsion spring assists in rotation and the clamping structure assists in storage, further improving the smoothness of unfolding and storage, and the overall adaptability and reliability are excellent. Attached Figure Description

[0020] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings: Figure 1 This is a front view of the retracted state of the present invention.

[0021] Figure 2 This is a top view of the retracted state of the present invention.

[0022] Figure 3 This is a structural diagram of the extension rod mechanism in this invention.

[0023] Figure 4 This is a schematic diagram of the unfolded state of the present invention.

[0024] Figure 5 Show Figure 4 A magnified view of part A in the middle.

[0025] The figure shows: 1. Base; 2. Extension rod mechanism; 21. Sleeve; 22. Extension rod; 23. Bushing; 24. Spring; 3. First locking mechanism; 4. Solar panel module; 5. Second locking mechanism; 6. Torsion spring; 9. First insertion hole; 10. Second insertion plate. Detailed Implementation

[0026] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0027] like Figures 1-5 As shown, a telescopic solar wing lifting mechanism includes a base 1 and a telescopic mechanism 2. The base 1 is fixed to the celestial body. The telescopic mechanism 2 is telescopically arranged at both ends, and at least three circumferentially arranged and hinged to the base 1. The telescopic mechanism 2 rotates along the hinge points toward the side away from the celestial body. The end of the telescopic mechanism 2 away from the base 1 is hinged to the solar wing module 4. The telescopic mechanism 2 includes at least a first working state and a second working state. In the first working state, the telescopic mechanism 2 is retracted, and the connection end of the telescopic mechanism 2 and the solar wing module 4 is close to the celestial body. In the second working state, the telescopic mechanism 2 is extended, and the connection end of the telescopic mechanism 2 and the solar wing module 4 is away from the celestial body.

[0028] The working principle of this application is as follows: the base 1 is fixed to the star as the installation basis. Through the coordinated telescopic and rotational movements of the extension rod mechanism 2, combined with the positioning and fixing function of the locking mechanism, the solar wing module 4 can switch between a retracted state close to the star and an deployed working state far away from the star. Moreover, this structure has a very strong stability. Once deployed, it tends to maintain its deployed state, thereby achieving the goal of the solar wing module 4 being deployed away from the star while providing favorable signal transmission space for the star antenna.

[0029] Specifically, the extension rod mechanism 2 includes a sleeve 21, an extension rod 22, a bushing 23, and a drive device. The sleeve 21 is arranged in at least three circumferential directions and hinged to the base 1. The bushing 23 is accommodated and fixed to the end of the sleeve 21 away from the base 1. The extension rod 22 is accommodated and slidably connected to the bushing 23, and the end of the extension rod 22 near the base 1 can pass through the inside of the sleeve 21. The drive device is disposed inside the sleeve 21 and connected to the extension rod 22, and the drive device drives the extension rod 22 away from the base 1.

[0030] In one embodiment, the drive device includes a passive drive structure, which includes a spring 24 housed inside a sleeve 21. One end of the spring 24 abuts against the inner wall of the sleeve 21 near the base 1, and the other end abuts against the extension rod 22, driving the extension rod 22 away from the base 1.

[0031] In one variation, the drive unit includes an active drive structure comprising a linear motor, a lead screw, a threaded sleeve, and a slider. The linear motor is fixed to the sleeve 21. The lead screw is rotatably connected to the sleeve 21 and coaxially fixed to the output shaft of the linear motor. The slider is fixed to the extension rod 22 and slides linearly along the axial direction of the sleeve 21. The threaded sleeve is coaxially fixed to the extension rod 22 and screwed to the lead screw. The rotation of the linear motor drives the threaded sleeve to move the extension rod 22 away from the base 1.

[0032] In one embodiment, the extension rod 22 extends radially near the end of the base 1 to form a stop against the end of the bushing 23.

[0033] Specifically, a torsion spring 6 is provided at the hinge point between the base 1 and the sleeve 21. A shaft is formed on the base 1 to pass through and position the torsion spring 6. One end of the torsion spring 6 abuts against the base 1, and the other end abuts against the sleeve 21, driving the sleeve 21 to rotate toward the side away from the star, thus assisting the extension rod mechanism 2 to rotate.

[0034] A first locking mechanism 3 is provided between the bushing 23 and the extension rod 22. When the extension rod 22 is located at the end of the sleeve 21 away from the base 1, the first locking mechanism 3 is used to fix the bushing 23 and the extension rod 22. A second locking mechanism 5 is provided between the base 1 and the sleeve 21. When the sleeve 21 is rotated to the side away from the star, the second locking mechanism 5 is used to fix the base 1 and the sleeve 21.

[0035] Specifically, the first locking mechanism 3 includes a first pin, a first insertion hole 9, and a first spring. The first pin is axially perpendicular to the axis of the extension rod 22 and is slidably connected to one side of the bushing 23 along the axis. The first insertion hole 9 is located at the end of the extension rod 22 near the base 1. The first spring connects the first pin and the bushing 23, and drives the first pin to insert into the first insertion hole 9.

[0036] The second locking mechanism 5 includes a second insert plate 10, a second slot, and a second spring. The second insert plate 10 extends radially along the hinge axis between the sleeve 21 and the base 1, and is slidably connected to the end of the sleeve 21 near the base 1 along its own extending direction. The second slot is formed in the base 1, with its opening facing radially toward the hinge axis between the sleeve 21 and the base 1. The second spring connects the sleeve 21 and the second insert plate 10, and drives the second insert plate 10 to insert into the second slot.

[0037] Preferably, a clamping structure is fitted on the outer side of the extension rod mechanism 2 and the solar wing module 4. The clamping structure abuts against and clamps the extension rod mechanism 2 and the solar wing module 4 close to the surface of the star. The clamping structure is movably connected to the surface of the star. When the clamping structure is released, the extension rod mechanism 2 extends outward and the solar wing module 4 is lifted and unfolded toward the side away from the star.

[0038] In one embodiment, the base 1 is bolted to the surface of the satellite. Four sleeves 21 are arranged circumferentially around the base 1. The solar array module 4 is rectangular, and the four corners of the rectangle are connected to four extension rods 22. Two of the four sleeves 21 are arranged in opposite directions along the circumference of the base 1, and the other two are located on the same side of the two oppositely arranged sleeves 21. The four sleeves 21 are symmetrically arranged along the two oppositely arranged sleeves 21.

[0039] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0040] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A telescopic solar panel lifting mechanism, characterized in that, include: Base (1) and extension rod mechanism (2); The base (1) is fixed to the star, the extension rod mechanism (2) is telescopically set at both ends, the extension rod mechanism (2) is set in at least three circumferential directions and hinged to the base (1), the extension rod mechanism (2) rotates along the hinge towards the side away from the star, and the end of the extension rod mechanism (2) away from the base (1) is hinged to the solar wing module (4). The extension rod mechanism (2) includes at least a first working state and a second working state. In the first working state, the extension rod mechanism (2) is retracted and the connection end of the extension rod mechanism (2) and the solar wing module (4) is close to the star. In the second working state, the extension rod mechanism (2) is extended and the connection end of the extension rod mechanism (2) and the solar wing module (4) is far away from the star. The extension mechanism (2) includes a sleeve (21), an extension rod (22), a bushing (23), and a drive device; The sleeve (21) is provided in at least three circumferential directions and hinged to the base (1); the bushing (23) is received and fixed to the end of the sleeve (21) away from the base (1); the extension rod (22) is received and slidably connected to the bushing (23), and the end of the extension rod (22) near the base (1) can be inserted into the sleeve (21); The drive device is located inside the sleeve (21) and connected to the extension rod (22). The drive device drives the extension rod (22) away from the base (1). A first locking mechanism (3) is provided between the bushing (23) and the extension rod (22). When the extension rod (22) is located at the end of the sleeve (21) away from the base (1), the first locking mechanism (3) is used to fix the bushing (23) and the extension rod (22). A second locking mechanism (5) is provided between the base (1) and the sleeve (21). When the sleeve (21) is rotated to the side away from the star, the second locking mechanism (5) is used to fix the base (1) and the sleeve (21).

2. The telescopic solar panel lifting mechanism according to claim 1, characterized in that, The drive device includes a passive drive structure, which includes a spring (24). The spring (24) is housed inside the sleeve (21), with one end abutting against the inner wall of the sleeve (21) near the base (1) and the other end abutting against the extension rod (22), and driving the extension rod (22) away from the base (1).

3. The telescopic solar panel lifting mechanism according to claim 1, characterized in that, The driving device includes an active driving structure, which includes a linear motor, a lead screw, a threaded sleeve, and a slider. The linear motor is fixed to the sleeve (21); the lead screw is rotatably connected to the sleeve (21) and coaxially fixed to the output shaft of the linear motor; the slider is fixed to the extension rod (22) and slides linearly along the axial direction of the sleeve (21); the threaded sleeve is coaxially fixed to the extension rod (22) and the threaded sleeve is screwed to the lead screw; the linear motor rotates to drive the threaded sleeve to move the extension rod (22) away from the base (1).

4. The telescopic solar panel lifting mechanism according to claim 1, characterized in that, A torsion spring (6) is provided at the hinge point between the base (1) and the sleeve (21). A shaft is formed on the base (1) through which the torsion spring (6) passes and positions. One end of the torsion spring (6) abuts against the base (1) and the other end abuts against the sleeve (21), driving the sleeve (21) to rotate toward the side away from the star.

5. The telescopic solar panel lifting mechanism according to claim 1, characterized in that, The first locking mechanism (3) includes a first pin, a first insertion hole (9) and a first spring. The first pin is axially perpendicular to the extension rod (22) and is slidably connected to one side of the bushing (23) along the axis. The first insertion hole (9) is opened at one end of the extension rod (22) near the base (1). The first spring is connected between the first pin and the bushing (23) and drives the first pin to insert into the first insertion hole (9).

6. The telescopic solar panel lifting mechanism according to claim 1, characterized in that, The second locking mechanism (5) includes a second insert plate (10), a second slot and a second spring. The second insert plate (10) extends radially along the hinge axis between the sleeve (21) and the base (1), and the second insert plate (10) is slidably connected to the end of the sleeve (21) near the base (1) along its own extension direction. The second slot is opened in the base (1) and the opening direction is towards the radial direction of the hinge axis between the sleeve (21) and the base (1). The second spring is connected between the sleeve (21) and the second insert plate (10) and drives the second insert plate (10) to be inserted into the second slot.

7. The telescopic solar panel lifting mechanism according to claim 1, characterized in that, The extension rod mechanism (2) and the solar wing module (4) are fitted with a clamping structure on their outer sides. The clamping structure abuts against the extension rod mechanism (2) and the solar wing module (4) close to the surface of the star. The clamping structure is movably connected to the surface of the star.

8. The telescopic solar panel lifting mechanism according to claim 1, characterized in that, The base (1) is fixed to the surface of the star by bolts. The base (1) is provided with four sleeves (21) around its circumference. The solar wing module (4) is rectangular, and the four corners of the rectangle are connected to four extension rods (22). Among the four sleeves (21), two sleeves (21) are arranged in opposite directions around the base (1), and the other two are located on the same side of the sleeves (21) arranged in opposite directions. The four sleeves (21) are arranged symmetrically along the two sleeves (21) arranged in opposite directions.

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