CN118018111A - Laser communication load and satellite with same - Google Patents
Laser communication load and satellite with same Download PDFInfo
- Publication number
- CN118018111A CN118018111A CN202410418191.7A CN202410418191A CN118018111A CN 118018111 A CN118018111 A CN 118018111A CN 202410418191 A CN202410418191 A CN 202410418191A CN 118018111 A CN118018111 A CN 118018111A
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- optical module
- locking rope
- satellite
- laser communication
- rope
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- 238000004891 communication Methods 0.000 title claims abstract description 38
- 230000003287 optical effect Effects 0.000 claims abstract description 67
- 230000001737 promoting effect Effects 0.000 claims abstract description 4
- 239000004677 Nylon Substances 0.000 claims description 12
- 229920001778 nylon Polymers 0.000 claims description 12
- WABPQHHGFIMREM-UHFFFAOYSA-N lead(0) Chemical compound [Pb] WABPQHHGFIMREM-UHFFFAOYSA-N 0.000 claims description 5
- 238000004146 energy storage Methods 0.000 claims description 3
- 230000005540 biological transmission Effects 0.000 description 14
- 238000000034 method Methods 0.000 description 11
- 238000011161 development Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012546 transfer Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
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Abstract
The application discloses a laser communication load and a satellite with the same, wherein the laser communication load comprises a bottom plate, a plurality of laser communication modules and a plurality of laser communication modules, wherein the bottom plate is suitable for being fixed on the satellite; the optical module is rotationally connected with the bottom plate and is suitable for emitting and/or receiving laser; the driving piece is arranged on the bottom plate and connected with the optical module, and is suitable for driving the optical module to rotate after the satellite enters the orbit; the two ends of the locking rope are respectively connected with the bottom plate and the optical module, and are suitable for limiting the rotation of the optical module; and the release assembly is connected with the locking rope and is suitable for promoting the locking rope to be broken, so that the driving piece can drive the optical module to rotate. Compared with the prior art, the application is mainly embodied in the aspects of small volume, light weight, high reliability and the like, and meets the general requirements of the load on the satellite.
Description
Technical Field
The application relates to the technical field of satellite communication, in particular to a laser communication load and a satellite with the same.
Background
With the development of technology, the requirements on the transmission rate of communication equipment are higher and higher, and satellites are used as information transfer equipment, so that the improvement of the communication transmission rate is particularly important. At present, the transmission rate of microwave communication is approaching the limit, and if the communication rate is to be continuously improved, the use of laser as an information carrier becomes a necessary choice. The laser communication is characterized by high directivity requirement and is generally provided with a mechanism for driving the optical module to rotate.
Because of the current technical limitations, satellite transmission costs are high, and thus the load on the satellite generally requires: on the premise of realizing the established function, the device has small volume, light weight and high reliability, and can bear vibration and impact in the transportation and emission processes. The moving parts in the load are usually constrained in their degree of freedom by some means before the satellite is launched into orbit and then restored after orbit.
A common method of limiting the degrees of freedom is to use a motor or electromagnet to drive a pin or a stop to lock or release a moving part in the load. The disadvantage of this method is the complex mechanism, large volume, high weight and easy seizing.
Disclosure of Invention
In view of the above, it is necessary to provide a laser communication load and a satellite having the same.
In one aspect of the application, a laser communication load is presented comprising:
A base plate adapted to be secured to a satellite;
The optical module is rotationally connected with the bottom plate and is suitable for emitting laser and/or receiving laser;
the driving piece is arranged on the bottom plate, connected with the optical module and used for driving the optical module to rotate after the satellite enters the orbit;
The two ends of the locking rope are respectively connected with the bottom plate and the optical module, and are suitable for limiting the rotation of the optical module;
And the release assembly is connected with the locking rope and is suitable for promoting the locking rope to be broken, so that the driving piece can drive the optical module to rotate.
In some embodiments, the release assembly comprises:
A power supply;
A wire connected to the power supply;
And the resistance wire is connected with the lead, is bound and fixed on the locking rope and can generate heat when being electrified, so that the locking rope is promoted to break.
In some embodiments, further comprising:
The safe spring-off assembly is arranged on the bottom plate and can move out the lead wire, the resistance wire and the broken locking rope away from the optical module.
In some embodiments, the safety pop-off assembly includes:
The fixing piece is fixedly connected with the bottom plate;
One end of the elastic piece is fixedly connected with the fixing piece;
The connecting piece is connected with one end, far away from the fixing piece, of the elastic piece and is used for connecting the locking rope, the conducting wire and the resistance wire.
In some embodiments, before the locking rope breaks, the elastic element is in an elastic energy storage state, after the locking rope breaks, the elastic element can rebound, and the conducting wire, the resistance wire and the broken locking rope are removed in a direction away from the optical module.
In some embodiments, the base plate and the optical module are respectively provided with a first connecting ring and a second connecting ring, and two ends of the locking rope are respectively bound and fixed on the first connecting ring and the second connecting ring.
In some embodiments, the locking cord is any one of a single strand nylon cord, a multi-strand nylon cord, a reinforced nylon cord, and a blended nylon cord.
In a second aspect of the application, a satellite is also presented that includes the laser communication payload described above.
Compared with the prior art, the application has the beneficial effects that:
Firstly, the application is helpful to realize higher communication transmission rate by providing a laser communication load with a bottom plate, an optical module and a driving piece, thereby meeting the increasing transmission rate requirement of communication equipment. Secondly, through setting up locking rope and release subassembly, before the satellite goes into orbit, the rotation of optical module can be restricted to the locking rope to reduce the harm to optical module because vibration and impact at satellite transmission process, after the satellite goes into orbit, release subassembly can promote the fracture of locking rope, thereby make the driving piece can normally drive optical module and rotate, make optical module can normally transmit laser and/or receive laser, this kind of method of restriction degree of freedom compares in prior art, mainly embody in aspects such as small, light in weight and reliability height, accord with the general requirement of load on the satellite.
Drawings
FIG. 1 is a schematic diagram showing a state of a locking rope before a satellite enters an orbit according to an exemplary embodiment of the present application;
FIG. 2 is a schematic diagram showing a state of a locking rope after a satellite enters an orbit according to an exemplary embodiment of the present application;
FIG. 3 is an exploded view of an exemplary embodiment of the present application;
FIG. 4 is an enlarged schematic view of portion A of FIG. 1;
fig. 5 is an enlarged schematic view of a portion B in fig. 2.
In the figure: 1. a bottom plate; 11. a first connection ring; 2. an optical module; 21. a light shield; 22. a second connecting ring; 3. a driving member; 4. a locking rope; 5. a release assembly; 51. a wire; 52. a resistance wire; 6. a safety bouncing component; 61. a fixing member; 62. an elastic member; 63. a connecting piece; 631. and a third connecting ring.
Detailed Description
The following description of the embodiments of the present application will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present application, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application.
In the description of the present application, it should be noted that the directions or positional relationships indicated by the terms "upper", "lower", "inner", "outer", "front", "rear", "both ends", "one end", "the other end", etc. are based on the directions or positional relationships shown in the drawings, are merely for convenience of describing the present application and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific direction, be configured and operated in the specific direction, and thus should not be construed as limiting the present application. Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present application, it should be noted that, unless explicitly specified and limited otherwise, the terms "mounted," "provided," "connected," and the like are to be construed broadly, and may be fixedly connected, detachably connected, or integrally connected, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art according to the specific circumstances.
As described in the background art, with the development of the technology, the requirements on the transmission rate of the communication device are higher and higher, and the satellite is used as the information transfer device, so that the improvement of the communication transmission rate is particularly important. At present, the transmission rate of microwave communication is approaching the limit, and if the communication rate is to be continuously improved, the use of laser as an information carrier becomes a necessary choice. The laser communication is characterized by high directivity requirement and is generally provided with a mechanism for driving the optical module to rotate. Because of the current technical limitations, satellite transmission costs are high, and thus the load on the satellite generally requires: on the premise of realizing the established function, the device has small volume, light weight and high reliability, and can bear vibration and impact in the transportation and emission processes. The moving parts in the load are usually constrained in their degree of freedom by some means before the satellite is launched into orbit and then restored after orbit. A common method of limiting the degrees of freedom is to use a motor or electromagnet to drive a pin or a stop to lock or release a moving part in the load. The disadvantage of this method is the complex mechanism, large volume, high weight and easy seizing.
To improve the above problem, in a first aspect of the present application, a laser communication load is proposed, referring to fig. 1 and 3, which mainly includes: the device comprises a base plate 1, an optical module 2, a driving piece 3, a locking rope 4, a release assembly 5, a safety ejection assembly 6 and a control module. Wherein the base plate 1 is adapted to be fixed to a satellite; the optical module 2 is suitable for emitting and/or receiving laser light; the driving piece 3 is suitable for driving the optical module 2 to rotate after the satellite enters orbit so that the optical module 2 emits laser light in different directions or receives laser light from different directions; the locking rope 4 is used for limiting the rotation of the optical module 2 before the satellite enters the orbit, namely limiting the freedom degree of the optical module 2, so that the vibration and impact of the optical module 2 in the satellite transmitting process are reduced; the release assembly 5 is suitable for promoting the locking rope 4 to break after the satellite enters the orbit, so that the driving piece 3 can normally drive the optical module 2 to rotate; the safety pop-off assembly 6 is adapted to move the locking cord 4 and other parts out in a direction away from the optical module 2 after the locking cord 4 breaks, thereby avoiding interference with the normal operation of the optical module 2.
Specifically, in the exemplary embodiment, referring to fig. 1 and 2, the base plate 1 is formed in a square plate-like structure, and is adapted to be fixed to a satellite by welding or bolting, or the like.
Specifically, in the exemplary embodiment, referring to fig. 1 and 2, the optical module 2 is rotatably connected to the base plate 1 so that it emits laser light in different directions or receives laser light from different directions.
Further, in the exemplary embodiment, referring to fig. 1 and 3, a light shielding cover 21 is disposed on the optical module 2, the light shielding cover 21 is integrally covered on the optical module 2, and a relief opening is formed at a position corresponding to the transmitting end and the receiving end of the optical module 2.
Specifically, in the exemplary embodiment, referring to fig. 1 and 3, the driving member 3 is disposed on the base plate 1 and connected to the optical module 2, so as to drive the optical module 2 to rotate after the satellite is in orbit.
Further, in the exemplary embodiment, referring to fig. 1 and 3, the driving member 3 is specifically a motor, wherein a stator of the motor is fixedly connected to the base plate 1, and a rotor of the motor is fixedly connected to the bottom of the optical module 2. The optical module2 can be rotated to a preset direction by the motor.
Specifically, in the exemplary embodiment, referring to fig. 1 and 2, the locking rope 4 is any one of a single-strand nylon rope, a multi-strand nylon rope, a reinforced nylon rope, and a blended nylon rope. Both ends of the locking rope 4 are respectively connected with the bottom plate 1 and the optical module 2, and are suitable for limiting the rotation of the optical module 2.
Further, in the exemplary embodiment, referring to fig. 4 and 5, the first and second connection rings 11 and 22 are welded and fixed to the sides of the base plate 1 and the optical module 2, respectively, and both ends of the locking string 4 are bound and fixed to the first and second connection rings 11 and 22, respectively.
Further, in the exemplary embodiment, referring to fig. 4 and 5, the first connecting rings 11 are provided with two, and are disposed on two sides of the second connecting ring 22 oppositely, and the corresponding locking ropes 4 are provided with two, one ends of the two locking ropes 4 are bound and fixed on the second connecting ring 22, and the other ends of the two locking ropes 4 are bound and fixed on the two first connecting rings 11 respectively. By the arrangement, the rotation of the optical module 2 can be further limited, and the stability of the optical module in the satellite transmitting and orbit entering process is improved.
Specifically, in the exemplary embodiment, referring to fig. 4 and 5, the release assembly 5 is connected to the locking rope 4, and is adapted to cause the locking rope 4 to break after the satellite is in orbit, so that the driving member 3 can normally drive the optical module 2 to rotate.
Further, in the exemplary embodiment, referring to fig. 4 and 5, release assembly 5 includes a power source (not shown), a wire 51, and a resistance wire 52. Wherein the power is supplied by a satellite; the wire 51 is connected with a power supply and a resistance wire 52; the resistance wire 52 is specifically a tungsten wire, is bound and fixed on the locking rope 4, and is connected with a power supply through a lead wire 51, and the resistance wire 52 can generate heat when being electrified, so that the locking rope 4 is promoted to break.
Still further, in the exemplary embodiment, referring to fig. 4 and 5, corresponding to the two locking ropes 4, two ends of the resistance wire 52 are respectively bound to the two locking ropes 4, the wire 51 includes a positive wire and a negative wire, two ends of the positive wire are respectively connected with a positive electrode of the power supply and one end of the resistance wire 52, two ends of the negative wire are respectively connected with a negative electrode of the power supply and the other end of the resistance wire 52, and when the power supply is electrified, current flows through the wire 51 and the resistance wire 52, and the resistance wire 52 heats up, so that the two locking ropes 4 are blown.
Specifically, in the exemplary embodiment, referring to fig. 4 and 5, the safety pop-off assembly 6 is disposed on the base plate 1, and is capable of moving out the conductive wire 51, the resistance wire 52, and the broken locking rope 4 in a direction away from the optical module 2, so as to avoid interference with subsequent operation of the optical module 2.
Further, in the exemplary embodiment, referring to fig. 4 and 5, safety pop-off assembly 6 includes a securing member 61, an elastic member 62, and a connecting member 63. Wherein the fixing member 61 is formed in a circular plate shape and is fixed to the base plate 1 by bolts; the elastic member 62 is specifically a spring, one end of which is welded and fixed to the fixing member 61, and the other end of which is welded and fixed to the connecting member 63; the connection piece 63 is formed in a rod shape for connecting the locking rope 4, the lead wire 51, and the resistance wire 52.
Still further, in the exemplary embodiment, referring to fig. 4 and 5, before the locking rope 4 is broken, the elastic member 62 is in an elastic energy storage state, after the locking rope 4 is broken, the elastic member 62 can rebound, and the wire 51, the resistance wire 52, and the broken locking rope 4 are removed away from the optical module 2.
Further, in the exemplary embodiment, referring to fig. 4 and 5, the middle portion of the connecting member 63 is welded to the elastic member 62, the positive electrode wire and the negative electrode wire are bound and fixed to the connecting member 63 and are respectively located at two sides of the elastic member 62, and a third connecting ring 631 is welded to two ends of the connecting member 63, so that the positive electrode wire and the negative electrode wire can be prevented from sliding off the connecting member 63. Meanwhile, the two locking ropes 4 are respectively bound and fixed with the two third connecting rings 631, so that the stability of the binding ropes is improved. Further, for one locking rope 4, the binding position of the resistance wire 52 and the locking rope 4 is located between the second connecting ring 22 and the third connecting ring 631, so that the breaking point of the locking rope 4 is located between the second connecting ring 22 and the third connecting ring 631, after the locking rope 4 breaks, the elastic piece 62 rebounds, and the connecting piece 63 can carry the lead wire 51, the resistance wire 52 and the broken locking rope 4 to move out in a direction away from the optical module 2.
Specifically, in the exemplary embodiment, the control module is connected to the satellite, the optical module 2, the driving member 3 and the release assembly 5, and is capable of receiving information sent by the satellite, and after the satellite enters the orbit, it is capable of controlling the release assembly 5 to operate, specifically, controlling the power supply to supply current to the wire 51 and the resistance wire 52, so as to blow the locking rope 4, and in the subsequent process, the control module is also capable of controlling the operation of the driving member 3 and the optical module 2, so as to complete information transmission between the satellites.
In summary, the present application is helpful to achieve a higher communication transmission rate by providing a laser communication load with a base plate 1, an optical module 2 and a driving element 3, so as to meet the increasing transmission rate requirements of communication devices. By arranging the locking rope 4 and the release assembly 5, the locking rope 4 can limit the rotation of the optical module 2 before the satellite enters the orbit, so that the damage to the optical module 2 caused by vibration and impact in the satellite launching process is reduced, and after the satellite enters the orbit, the release assembly 5 can cause the locking rope 4 to be broken, so that the driving piece 3 can normally drive the optical module 2 to rotate, and the optical module 2 can normally launch laser and/or receive laser.
In a second aspect of the application, a satellite is also presented that includes the laser communication payload described above. Finally, it should be noted that: the foregoing description is only a preferred embodiment of the present application, and the present application is not limited thereto, but it is to be understood that modifications and equivalents of some of the technical features described in the foregoing embodiments may be made by those skilled in the art, although the present application has been described in detail with reference to the foregoing embodiments. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application should be included in the protection scope of the present application.
Claims (8)
1. A laser communication load, comprising:
A base plate adapted to be secured to a satellite;
The optical module is rotationally connected with the bottom plate and is suitable for emitting laser and/or receiving laser;
the driving piece is arranged on the bottom plate, connected with the optical module and used for driving the optical module to rotate after the satellite enters the orbit;
The two ends of the locking rope are respectively connected with the bottom plate and the optical module, and are suitable for limiting the rotation of the optical module;
And the release assembly is connected with the locking rope and is suitable for promoting the locking rope to be broken, so that the driving piece can drive the optical module to rotate.
2. The laser communication load of claim 1, wherein the release assembly comprises:
A power supply;
A wire connected to the power supply;
And the resistance wire is connected with the lead, is bound and fixed on the locking rope and can generate heat when being electrified, so that the locking rope is promoted to break.
3. The laser communication load of claim 2, further comprising:
The safe spring-off assembly is arranged on the bottom plate and can move out the lead wire, the resistance wire and the broken locking rope away from the optical module.
4. The laser communication load of claim 3, wherein the safety pop-off assembly comprises:
The fixing piece is fixedly connected with the bottom plate;
One end of the elastic piece is fixedly connected with the fixing piece;
The connecting piece is connected with one end, far away from the fixing piece, of the elastic piece and is used for connecting the locking rope, the conducting wire and the resistance wire.
5. The laser communication load of claim 4, wherein the elastic member is in an elastic energy storage state before the locking rope breaks, and wherein the elastic member is capable of springback after the locking rope breaks and moving the wire, the resistance wire, and the broken locking rope away from the optical module.
6. The laser communication load according to claim 1, wherein the base plate and the optical module are respectively provided with a first connecting ring and a second connecting ring, and both ends of the locking rope are respectively bound and fixed on the first connecting ring and the second connecting ring.
7. The laser communication load of claim 1, wherein the locking rope is any one of a single strand nylon rope, a multi-strand nylon rope, a reinforced nylon rope, and a blended nylon rope.
8. A satellite, comprising:
The laser communication load of any of claims 1-7.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410418191.7A CN118018111A (en) | 2024-04-09 | 2024-04-09 | Laser communication load and satellite with same |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410418191.7A CN118018111A (en) | 2024-04-09 | 2024-04-09 | Laser communication load and satellite with same |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN118018111A true CN118018111A (en) | 2024-05-10 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202410418191.7A Pending CN118018111A (en) | 2024-04-09 | 2024-04-09 | Laser communication load and satellite with same |
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| CN (1) | CN118018111A (en) |
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| CN103895879A (en) * | 2014-02-26 | 2014-07-02 | 郑钢铁 | Low-impact locking and unlocking device |
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| CN111038737A (en) * | 2019-12-31 | 2020-04-21 | 中国科学院空间应用工程与技术中心 | Driving device for optical inspection outside material cabin and exposure platform |
| WO2023040257A1 (en) * | 2021-09-17 | 2023-03-23 | 椭圆时空(北京)科技有限公司 | Communication and remote sensing integrated satellite system |
| CN116238719A (en) * | 2023-04-26 | 2023-06-09 | 长光卫星技术股份有限公司 | Terminal locking device of satellite-borne periscope type two-dimensional turntable |
| CN117657473A (en) * | 2023-12-20 | 2024-03-08 | 上海卫星工程研究所 | Swing arm mechanism for compressing and releasing satellite payload |
-
2024
- 2024-04-09 CN CN202410418191.7A patent/CN118018111A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103895879A (en) * | 2014-02-26 | 2014-07-02 | 郑钢铁 | Low-impact locking and unlocking device |
| CN108583942A (en) * | 2018-06-19 | 2018-09-28 | 哈尔滨工业大学 | A kind of spatial flexible arm compression relieving mechanism of fuse unlock |
| CN111038737A (en) * | 2019-12-31 | 2020-04-21 | 中国科学院空间应用工程与技术中心 | Driving device for optical inspection outside material cabin and exposure platform |
| WO2023040257A1 (en) * | 2021-09-17 | 2023-03-23 | 椭圆时空(北京)科技有限公司 | Communication and remote sensing integrated satellite system |
| CN116238719A (en) * | 2023-04-26 | 2023-06-09 | 长光卫星技术股份有限公司 | Terminal locking device of satellite-borne periscope type two-dimensional turntable |
| CN117657473A (en) * | 2023-12-20 | 2024-03-08 | 上海卫星工程研究所 | Swing arm mechanism for compressing and releasing satellite payload |
Non-Patent Citations (1)
| Title |
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| 宣明;张道威;谷松;杨林;程龙;: "微小卫星太阳帆板压紧释放机构的设计", 光学精密工程, no. 04, 15 April 2017 (2017-04-15) * |
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