Inter-satellite laser communication terminal

Abstract

The invention discloses an inter-satellite laser communication terminal, and relates to the technical field of laser communication, the inter-satellite laser communication terminal comprises a laser communication assembly, the front surface of the laser communication assembly is detachably provided with a lifting assembly, the top of the lifting assembly is in transmission connection with a fixing assembly in the vertical direction, and the fixing assembly is internally provided with an opening and closing assembly. A locking assembly is fixedly arranged at the top of the fixing assembly; the laser communication assembly comprises a square locking ring fixedly arranged at the top of the front surface of the rotating bracket and the bottom of the front surface of the reflecting telescope; the lifting assembly comprises an L-shaped mounting plate detachably arranged on the front face of the base. According to the invention, the locking operation of the rotating bracket and the reflecting telescope can be completed only by using a single driving piece, and meanwhile, the piezoelectric ceramics are used for locking, so that the structure is simple, and the device can be lighter and lower in cost.

Description

Technical Field

[0001] This invention relates to the field of laser communication technology, and in particular to an inter-satellite laser communication terminal. Background Technology

[0002] A laser communication terminal is a device that uses a space laser beam as an information carrier to transmit information. Compared with traditional microwave communication, it has advantages such as high communication capacity, strong confidentiality, strong anti-interference ability, and small size and weight. For inter-satellite laser communication terminals, it is necessary to restrict the relative rotation of its sub-components before the satellite is launched into orbit.

[0003] Based on the above background, the invention patent with authorization announcement number CN119154948B discloses an inter-satellite laser communication terminal. After entering orbit, the rigid locking component moves downward to disengage from the first and second limiting cylinders, thereby releasing the restrictions on the pitch and azimuth turntables. Compared with the traditional method of restricting the relative rotation of sub-components of the inter-satellite laser communication terminal by using ropes to pull, this improves the fixed frequency of the inter-satellite laser communication terminal and avoids resonance during transmission.

[0004] However, in order to lock the azimuth and pitch turntables, the aforementioned inter-satellite laser communication terminal requires multiple drive components, including a rotary driver and two linear drivers, as well as supporting control circuits. In addition, to facilitate insertion into the limiting cylinder and locking after insertion into the limiting cylinder, a relatively complex umbrella rib assembly is also required, making the device structure relatively complex and unable to move towards lightweight and low-cost design.

[0005] Therefore, it is necessary to invent an inter-satellite laser communication terminal to solve the above problems. Summary of the Invention

[0006] The purpose of this invention is to provide an inter-satellite laser communication terminal that can complete the locking operation of the rotating bracket and the reflecting telescope using only a single driving component. Furthermore, it utilizes piezoelectric ceramics for locking, resulting in a simple structure that makes the device lighter and less expensive. This addresses the problem mentioned in the background art, where locking the azimuth and pitch turntables requires multiple driving components, including a rotary driver and two linear drivers, as well as corresponding control circuits. Additionally, to facilitate insertion into the limiting cylinder and locking after insertion, a relatively complex umbrella-shaped assembly is also needed, leading to a more complex device structure and hindering lightweight and low-cost design.

[0007] To achieve the above objectives, the present invention provides the following technical solution: an inter-satellite laser communication terminal, comprising a laser communication component, a lifting component detachably disposed on the front of the laser communication component, a fixing component being driven to the top of the lifting component along the vertical direction, a switching component being disposed inside the fixing component, and a locking component being fixedly disposed on the top of the fixing component;

[0008] The laser communication component includes a square locking ring fixedly disposed on the top front of the rotating bracket and the bottom front of the reflecting telescope.

[0009] The lifting assembly includes an L-shaped mounting plate that can be detachably mounted on the front of the base. A lead screw is rotatably nested on the top left side of the L-shaped mounting plate via a bearing. A micro motor that is connected to the lead screw is fixedly mounted on the bottom left side of the L-shaped mounting plate. A T-shaped lifting seat is driven and sleeved on the outside of the lead screw.

[0010] The fixing components include four sets of elastic support mechanisms that are slidably installed at the four corners of the top of the T-shaped lifting seat, and a fixing plate that is fixedly installed on the top of the four sets of elastic support mechanisms.

[0011] Preferably, the laser communication component further includes a base, with multiple fixing holes at the top edge of the base, and multiple reinforcing plates evenly fixed on the outer side of the base.

[0012] Preferably, a rotating bracket that can rotate around its own axis is installed on the top of the base, and a reflecting telescope that can rotate around its own axis is installed on the inner side of the rotating bracket.

[0013] Preferably, the lifting assembly further includes mounting bolts for detachably mounting the L-shaped mounting plate to the bottom front of the base and a guide rod for guiding the T-shaped lifting seat. The guide rod is fixedly mounted on the top of the L-shaped mounting plate and the T-shaped lifting seat is slidably sleeved on the outside of the guide rod.

[0014] Preferably, any of the elastic support mechanisms includes a sliding shaft that slides vertically through the T-shaped lifting seat and a return spring sleeved on the outside of the sliding shaft. The sliding shaft is fixedly mounted on the bottom of the fixed plate, and the return spring is located between the fixed plate and the T-shaped lifting seat.

[0015] Preferably, the fixing assembly further includes an outer housing that is fixedly sleeved on the outside of the fixing plate and a wiring hole opened on the top of the fixing plate.

[0016] Preferably, the opening and closing assembly includes a first L-shaped bracket fixedly disposed on the top of the T-shaped lifting seat and a second L-shaped bracket fixedly disposed on the bottom of the fixed plate. A first guide block is fixedly disposed on the bottom of the first L-shaped bracket and is connected to the power supply through a wire. A second guide block that fits against the first guide block is fixedly disposed on the top of the second L-shaped bracket.

[0017] Preferably, the locking assembly includes a locking rod fixedly disposed on the top of the fixing plate. The locking rod and the inner holes of the two square locking rings are coaxially disposed in the vertical direction. Multiple piezoelectric ceramics are fixedly disposed on the top and bottom of the outer side of the locking rod. Each piezoelectric ceramic is connected to the second guide block and the power supply through a wire. The piezoelectric ceramic undergoes mechanical deformation and shortens due to the inverse piezoelectric effect.

[0018] Preferably, the locking assembly further includes a wiring channel that extends through the top of the locking rod and to the bottom of the locking rod, the wiring channel communicating with the wiring hole.

[0019] This invention also discloses a locking method for an inter-satellite laser communication terminal, the method specifically including the following steps:

[0020] S1. Before the satellite is launched into orbit, the output shaft of the micro motor drives the lead screw to rotate, causing the T-shaped lifting seat guided by the guide rod to move upward. When the T-shaped lifting seat moves upward, it drives the first guide block to move upward through the first L-shaped bracket. At the same time, it drives the fixed plate to move upward through the elastic support mechanism. Then, the fixed plate drives the second guide block to move upward through the second L-shaped bracket. The second guide block drives the locking rod to move upward continuously, so that the locking rod is inserted into the inside of the two square locking rings. During this process, the first guide block and the second guide block always remain in contact.

[0021] S2. When the top of the fixed plate is in contact with the bottom of the square locking ring below, the locking rod drives multiple piezoelectric ceramics to the locking position located inside the two square locking rings. At the same time, due to the obstruction of the square locking ring below, the locking rod cannot continue to move upward.

[0022] S3. The T-shaped lifting seat continues to move upward under the drive of the lead screw. During this process, the return spring is continuously compressed. At the same time, the T-shaped lifting seat drives the first guide block to disengage from the top of the second guide block through the first L-shaped bracket. At this time, multiple piezoelectric ceramics are de-energized. Subsequently, the piezoelectric ceramics that are no longer affected by the inverse piezoelectric effect recover and press against the inner wall of the adjacent square locking ring to achieve locking. Then, the micro motor is de-energized and stopped.

[0023] S4. After the satellite is launched into orbit, the micro motor is restarted and the micro motor drives the lead screw to rotate in the opposite direction, thereby causing the T-shaped lifting seat to move down and reset. When the T-shaped lifting seat moves down, it drives the first guide block to move down through the first L-shaped bracket until the first guide block and the second guide block are in contact. At this time, multiple piezoelectric ceramics shorten again under the action of the inverse piezoelectric effect to release the lock.

[0024] S5. The T-shaped lifting seat moves the fixed plate down via the return spring. The fixed plate then moves the locking rod out from the inside of the square locking ring, thereby releasing the lock between the rotating bracket and the reflecting telescope. After the T-shaped lifting seat is reset, the micro motor is powered off and stops.

[0025] The technical effects and advantages of this invention are as follows:

[0026] This invention incorporates a lifting component and a locking component. The lifting component, via a fixing component, drives the locking component to the locking position. Subsequently, under the obstruction of a square locking ring, the lifting component drives the opening and closing component to separate, allowing the piezoelectric ceramic, which has shortened due to the inverse piezoelectric effect, to recover and achieve locking. Compared to existing technologies, this invention uses only a single driving component to complete the locking operation of the rotating bracket and the reflecting telescope. Simultaneously, it utilizes piezoelectric ceramic for locking, resulting in a simple structure that makes the device lighter and lower in cost. Attached Figure Description

[0027] Figure 1 This is a schematic diagram of the overall structure of the present invention;

[0028] Figure 2 This is a schematic diagram of the laser communication component structure of the present invention;

[0029] Figure 3 This is a schematic diagram of the lifting component, fixing component, and locking component of the present invention;

[0030] Figure 4 This is a partial structural diagram of the lifting component and the opening / closing component of the present invention;

[0031] Figure 5 This is a partial structural diagram of the fixing component and the opening / closing component of the present invention;

[0032] Figure 6 This is a schematic diagram of the locking component structure of the present invention.

[0033] In the diagram: 1. Laser communication component; 11. Base; 12. Fixing hole; 13. Reinforcing plate; 14. Rotating bracket; 15. Reflecting telescope; 16. Square locking ring; 2. Lifting component; 21. L-shaped mounting plate; 22. Lead screw; 23. Micro motor; 24. T-shaped lifting seat; 25. Mounting bolt; 26. Guide rod; 3. Fixing component; 31. Fixing plate; 32. Sliding shaft; 33. Return spring; 34. Housing; 35. Wiring hole; 4. Opening and closing component; 41. First L-shaped bracket; 42. First guide block; 43. Second L-shaped bracket; 44. Second guide block; 5. Locking component; 51. Locking rod; 52. Piezoelectric ceramic; 53. Wiring channel. Detailed Implementation

[0034] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0035] This invention provides, for example Figures 1-6 An inter-satellite laser communication terminal is shown, including a laser communication component 1. A lifting component 2 is detachably provided on the front of the laser communication component 1. A fixing component 3 is connected to the top of the lifting component 2 in a vertical direction. A switching component 4 is provided inside the fixing component 3. A locking component 5 is fixedly provided on the top of the fixing component 3.

[0036] like Figure 2 As shown, the laser communication component 1 includes a square locking ring 16 fixedly disposed on the top front of the rotating bracket 14 and the bottom front of the reflecting telescope 15;

[0037] The laser communication component 1 also includes a base 11, with multiple fixing holes 12 at the top edge of the base 11, multiple reinforcing plates 13 evenly fixed on the outer side of the base 11, and a rotating bracket 14 that can rotate around its own axis installed on the top of the base 11. A reflecting telescope 15 that can rotate around its own axis is installed on the inner side of the rotating bracket 14.

[0038] It should be noted that the laser communication component 1 is a publicly available technology and a necessary technical feature for solving the technical problem of this application. Therefore, this application will not elaborate on the specific structure and connection method of the rotating bracket 14 and the reflecting telescope 15.

[0039] like Figure 4As shown, the lifting component 2 includes an L-shaped mounting plate 21 that can be detachably mounted on the front of the base 11. A lead screw 22 is rotatably nested on the top left side of the L-shaped mounting plate 21 via a bearing. A micro motor 23 that is connected to the lead screw 22 is fixedly mounted on the bottom left side of the L-shaped mounting plate 21. A T-shaped lifting seat 24 is connected to the outside of the lead screw 22.

[0040] The lifting assembly 2 also includes mounting bolts 25 for detachably mounting the L-shaped mounting plate 21 to the bottom front of the base 11 and guide rods 26 for guiding the T-shaped lifting seat 24. The guide rods 26 are fixedly mounted on the top of the L-shaped mounting plate 21 and the T-shaped lifting seat 24 is slidably sleeved on the outside of the guide rods 26.

[0041] By setting the above structure, when the output shaft of the micro motor 23 drives the lead screw 22 to rotate, the T-shaped lifting seat 24 guided by the guide rod 26 can continuously move upward along the guide rod 26. Conversely, if the micro motor 23 drives the lead screw 22 to rotate in the opposite direction, the T-shaped lifting seat 24 guided by the guide rod 26 can continuously move downward and reset along the guide rod 26.

[0042] like Figure 5 As shown, the fixing component 3 includes four sets of elastic support mechanisms that are slidably installed at the four corners of the top of the T-shaped lifting seat 24, and a fixing plate 31 that is fixedly installed on the top of the four sets of elastic support mechanisms.

[0043] Any elastic support mechanism includes a sliding shaft 32 that slides vertically through the T-shaped lifting seat 24 and a return spring 33 sleeved on the outside of the sliding shaft 32. The sliding shaft 32 is fixedly installed at the bottom of the fixed plate 31, and the return spring 33 is located between the fixed plate 31 and the T-shaped lifting seat 24.

[0044] The fixing component 3 also includes an outer housing 34 fixedly sleeved on the outside of the fixing plate 31 and a wiring hole 35 opened on the top of the fixing plate 31.

[0045] By setting the above structure, when the T-shaped lifting seat 24 moves upward, the return spring 33 in the elastic support mechanism drives the fixed plate 31 to move upward, and then the fixed plate 31 drives the second guide block 44 to move upward through the second L-shaped bracket 43. When the fixed plate 31 cannot move upward due to obstruction, the T-shaped lifting seat 24 can also compress the return spring 33 during the upward movement, so that the T-shaped lifting seat 24 can continue to move upward when the fixed plate 31 cannot move upward.

[0046] like Figure 4 and Figure 5As shown, the opening and closing assembly 4 includes a first L-shaped bracket 41 fixedly installed on the top of the T-shaped lifting seat 24 and a second L-shaped bracket 43 fixedly installed on the bottom of the fixing plate 31. A first guide block 42 is fixedly installed at the bottom of the first L-shaped bracket 41 and is connected to the power supply through a wire. A second guide block 44 that fits against the first guide block 42 is fixedly installed at the top of the second L-shaped bracket 43.

[0047] like Figure 6 As shown, the locking assembly 5 includes a locking rod 51 fixedly mounted on the top of the fixing plate 31. The locking rod 51 and the inner holes of the two square locking rings 16 are coaxially arranged in the vertical direction. Multiple piezoelectric ceramics 52 are fixedly mounted on the top and bottom of the outer side of the locking rod 51. Each piezoelectric ceramic 52 is connected to the second guide block 44 and the power supply through a wire. The piezoelectric ceramic 52 undergoes mechanical deformation and shortens due to the inverse piezoelectric effect. The locking assembly 5 also includes a wiring channel 53 that passes through the top of the locking rod 51 and extends to the bottom of the locking rod 51. The wiring channel 53 is connected to the wiring hole 35.

[0048] By setting up the above-mentioned opening and closing assembly 4 and locking assembly 5, when the locking rod 51 moves vertically, it can be inserted into the inside of the square locking ring 16, and in the process, it drives multiple piezoelectric ceramics 52 to the locking position located inside the two square locking rings 16. Since the piezoelectric ceramics 52 undergo mechanical deformation and shortening due to the inverse piezoelectric effect at this time, the square locking rings 16 will not block the piezoelectric ceramics 52 during the upward movement of the piezoelectric ceramics 52. When the piezoelectric ceramics 52 are de-energized, the piezoelectric ceramics 52, which are no longer affected by the inverse piezoelectric effect, recover and press against the inner wall of the adjacent square locking rings 16 to achieve locking. The structure is simple and the device is lighter and lower in cost.

[0049] This invention also discloses a locking method for an inter-satellite laser communication terminal, the method specifically including the following steps:

[0050] S1. Before the satellite is launched into orbit, the output shaft of the micro motor 23 drives the lead screw 22 to rotate, causing the T-shaped lifting seat 24, which is guided by the guide rod 26, to move upward. When the T-shaped lifting seat 24 moves upward, it drives the first guide block 42 to move upward through the first L-shaped bracket 41, and at the same time, it drives the fixed plate 31 to move upward through the elastic support mechanism. Then, the fixed plate 31 drives the second guide block 44 to move upward through the second L-shaped bracket 43. The second guide block 44 then drives the locking rod 51 to move upward continuously, so that the locking rod 51 is inserted into the inside of the two square locking rings 16. During this process, the first guide block 42 and the second guide block 44 always remain in contact.

[0051] S2. When the top of the fixed plate 31 is in contact with the bottom of the lower square locking ring 16, the locking rod 51 drives multiple piezoelectric ceramics 52 to the locking position located inside the two square locking rings 16. At the same time, due to the obstruction of the lower square locking ring 16, the locking rod 51 cannot continue to move upward.

[0052] S3, the T-shaped lifting seat 24 continues to move upward under the drive of the lead screw 22. During this process, the return spring 33 is continuously compressed. At the same time, the T-shaped lifting seat 24 drives the first guide block 42 to disengage from the top of the second guide block 44 through the first L-shaped bracket 41. At this time, multiple piezoelectric ceramics 52 are de-energized. Subsequently, the piezoelectric ceramics 52, which are no longer affected by the inverse piezoelectric effect, recover and press against the inner wall of the adjacent square locking ring 16 to achieve locking. Then, the micro motor 23 is de-energized and stopped.

[0053] S4. After the satellite is launched into orbit, the micro motor 23 is restarted and the micro motor 23 drives the lead screw 22 to rotate in the opposite direction, thereby causing the T-shaped lifting seat 24 to move down and reset. When the T-shaped lifting seat 24 moves down, it drives the first guide block 42 to move down through the first L-shaped bracket 41 until the first guide block 42 and the second guide block 44 are in contact. At this time, multiple piezoelectric ceramics 52 shorten again under the action of the inverse piezoelectric effect to release the lock.

[0054] S5, the T-shaped lifting seat 24 drives the fixed plate 31 to move down through the return spring 33, and the fixed plate 31 drives the locking rod 51 to disengage from the inside of the square locking ring 16, thereby releasing the lock between the rotating bracket 14 and the reflecting telescope 15. After the T-shaped lifting seat 24 is reset, the micro motor 23 is powered off and stopped.

[0055] Finally, it should be noted that the above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or make equivalent substitutions for some of the technical features. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. An inter-satellite laser communication terminal, characterized by: The utility model provides a laser communication assembly, the laser communication assembly is detachable with the lifting assembly in the front, the lifting assembly top direction transmission connection has the fixed component along the vertical, the fixed component inside is provided with the opening and closing component, the fixed component top fixedly installed with locking assembly, The laser communication assembly includes a square locking ring fixedly arranged on the top of the front surface of the rotating support and the bottom of the front surface of the reflecting telescope. The lifting assembly includes an L-shaped mounting plate detachably arranged on the front surface of the base, a lead screw rotatably nested on the left side of the top of the L-shaped mounting plate through a bearing, a micro motor fixedly arranged on the left side of the bottom of the L-shaped mounting plate and transmissionally connected with the lead screw, and a T-shaped lifting seat transmissionally and sleevably arranged on the outer side of the lead screw. The fixed component includes four groups of elastic support mechanisms slidingly installed on the top of the four corners of the T-shaped lifting seat and four fixed plates fixedly arranged on the top of the four groups of elastic support mechanisms.

2. The inter-satellite laser communication terminal according to claim 1, characterized in that: The laser communication assembly further includes a base, a plurality of fixing holes are formed at the top edge of the base, and a plurality of reinforcing plates are fixedly arranged on the outer side of the base.

3. The inter-satellite laser communication terminal according to claim 2, characterized in that: The base is provided with a rotating support rotatable about its own axis at the top thereof, and the rotating support is provided with a reflecting telescope rotatable about its own axis at the inner side thereof.

4. The inter-satellite laser communication terminal according to claim 3, characterized in that: The lifting assembly further includes mounting bolts for detachably arranging the L-shaped mounting plate on the front surface of the base and guide rods for guiding the T-shaped lifting seat, the guide rods being fixedly arranged on the top of the L-shaped mounting plate and the T-shaped lifting seat being slidingly and sleevably arranged on the outer side of the guide rods.

5. The inter-satellite laser communication terminal according to claim 4, characterized in that: Each of the elastic support mechanisms includes a sliding shaft slidingly penetrating the T-shaped lifting seat in the vertical direction and a return spring sleeved on the outer side of the sliding shaft, the sliding shaft being fixedly arranged on the bottom of the fixed plate, and the return spring being located between the fixed plate and the T-shaped lifting seat.

6. The inter-satellite laser communication terminal of claim 5, wherein: The fixed component further includes an outer shell fixedly sleeved on the outer side of the fixed plate and a wiring hole formed in the top of the fixed plate.

7. The inter-satellite laser communication terminal according to claim 6, characterized in that: The opening and closing component includes a first L-shaped bracket fixedly arranged on the top of the T-shaped lifting seat and a second L-shaped bracket fixedly arranged on the bottom of the fixed plate, the bottom of the first L-shaped bracket being fixedly provided with a first guide block, the first guide block being connected with the power supply through a wire, and the top of the second L-shaped bracket being fixedly provided with a second guide block abutting against the first guide block.

8. The inter-satellite laser communication terminal according to claim 7, characterized in that: The locking assembly includes a locking rod fixedly arranged on the top of the fixed plate, the locking rod and the inner holes of the two square locking rings being coaxially arranged in the vertical direction, a plurality of piezoelectric ceramics being fixedly arranged on the top outer side and the bottom outer side of the locking rod, each of the piezoelectric ceramics being connected with the second guide block and the power supply through a wire, and the piezoelectric ceramics being mechanically deformed and shortened due to the inverse piezoelectric effect.

9. The inter-satellite laser communication terminal of claim 8, wherein: The locking assembly further includes a wiring channel penetratingly arranged on the top end of the locking rod and extending to the bottom end of the locking rod, the wiring channel being in communication with the wiring hole.

10. The inter-satellite laser communication terminal of claim 9, wherein: The utility model further relates to a locking method of an intersatellite laser communication terminal, the method specifically comprising the following steps: S1, before the satellite is launched into orbit, the output shaft of the micro motor drives the screw to rotate, so that the T-shaped lifting seat guided by the guide rod moves up, and when the T-shaped lifting seat moves up, the first guide block is driven to move up through the first L-shaped support, and the fixed plate is driven to move up through the elastic support mechanism, so that the second guide block is driven to move up through the second L-shaped support, and the second guide block is driven to move up continuously, so that the locking rod is inserted into the inside of the two square locking rings; in this process, the first guide block and the second guide block always remain in close contact; S2, when the top of the fixed plate is in close contact with the bottom of the lower square locking ring, the locking rod drives the plurality of piezoelectric ceramics to reach the locking station inside the two square locking rings, and due to the blockage of the lower square locking ring, the locking rod cannot continue to move up; S3, the T-shaped lifting seat continues to move up under the drive of the screw, in this process, the reset spring is continuously compressed, and at the same time, the first guide block is driven by the first L-shaped support to move away from the top of the second guide block, at this time, the plurality of piezoelectric ceramics are de-energized, and then the piezoelectric ceramics which are no longer affected by the inverse piezoelectric effect are restored and tightly abut against the inner wall of the adjacent square locking ring, so as to realize locking, and then the micro motor is de-energized and stopped; S4, after the satellite is launched into orbit, the micro motor is started again and the screw is driven to rotate in reverse, so that the T-shaped lifting seat moves down and resets, and when the T-shaped lifting seat moves down, the first guide block is driven to move down through the first L-shaped support, until the first guide block and the second guide block are in close contact, at this time, the plurality of piezoelectric ceramics are shortened again under the action of the inverse piezoelectric effect, so as to release the locking; S5, the T-shaped lifting seat drives the fixed plate to move down through the reset spring, and the fixed plate drives the locking rod to move out of the inside of the square locking ring, so as to release the locking of the rotating support and the reflecting telescope, and after the T-shaped lifting seat resets, the micro motor is de-energized and stopped.

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