CN213769017U - Satellite stacking structure for low-earth-orbit satellite group transmission - Google Patents
Satellite stacking structure for low-earth-orbit satellite group transmission Download PDFInfo
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Abstract
The utility model provides a low orbit satellite is criticized satellite of transmission and is piled up framework in group, including interface and satellite and arrow coupling mechanism between the star, a plurality of satellites overlap and set up and divide into about two staggered arrangement, and adjacent satellite connects through the interface between the star, and satellite and arrow coupling mechanism has the elastic mechanism that can provide power for the separation of star and arrow. The utility model discloses a satellite stacking framework can realize the pile up and the transmission of big satellite in batches simultaneously, and emission efficiency is high, and greatly reduced the emission cost, provides the guarantee for satellite mass transmission and constellation construction; and the expandability of one-rocket multi-satellite transmission is met, the stacking of satellites in batches is realized on the premise of meeting the envelope, the transmission of any number of satellites can be realized, and more possible choices are provided for networking.
Description
Technical Field
The utility model belongs to the technical field of space satellite, concretely relates to satellite that low earth orbit satellite group criticized transmission piles up framework.
Background
The satellite stacking mode is one of key technologies for low-orbit satellite group launching, provides effective structural support for launching of group satellites, and meets the requirements of safety and high efficiency of satellite launching in carrying while realizing batch satellite launching. The current satellite transmission is mainly single-satellite transmission, and when multiple satellites are transmitted, each satellite and the distributor are provided with independent interfaces, so that the connection and separation method is simple, the application is wide, and the technology is mature. With the rapid development of satellites and constellations, particularly with the development of space internet technology, the trend of developing space internet by utilizing a large number of satellite networks is that the quantity demand of satellites is increased rapidly, so that the original independent transmitting mode cannot meet the market demand.
In the conventional multi-satellite transmission, the used satellite stacking method has the following defects: (1) in order to meet the requirement of multi-satellite launching, a distributor needs to be additionally designed in a connection and separation structure aiming at a plurality of stacked satellites, and the satellite launching space utilization rate is low; (2) each stacked satellite needs to be provided with an independent connecting and separating structure and initiating explosive devices, and the structure is complex and is not beneficial to batch production; (3) the separation process between the stacked satellites is complex, which is not beneficial to the constellation control of the satellites in orbit.
SUMMERY OF THE UTILITY MODEL
The utility model discloses aim at solving the technical problem who exists among the prior art, the utility model aims at providing a low orbit satellite is organized satellite of criticizing transmission and is piled up framework.
In order to achieve the above purpose, the utility model adopts the following technical scheme: a satellite stacking framework for low-earth satellite group launching comprises an inter-satellite interface and a satellite and arrow connecting mechanism, wherein a plurality of satellites are overlapped and divided into a left column and a right column which are staggered, adjacent satellites are connected through the inter-satellite interface, and the satellite and arrow connecting mechanism is provided with an elastic mechanism capable of providing power for satellite and arrow separation.
The utility model discloses a satellite stacking framework can realize the pile up and the transmission of big satellite in batches simultaneously, and emission efficiency is high, and greatly reduced the emission cost, provides the guarantee for satellite mass transmission and constellation construction; and the expandability of one-rocket multi-satellite transmission is met, the stacking of satellites in batches is realized on the premise of meeting the envelope, the transmission of any number of satellites can be realized, and more possible choices are provided for networking.
In a preferred embodiment of the present invention, the inter-satellite interfaces are connected by nesting of a cylindrical structure. The cylindrical body has a simple structure, and the nesting mode provides limiting and transverse shearing force to ensure the stability of the transverse position of the satellite.
The utility model discloses an among the preferred embodiment, the interface all including the spacing draw-in groove that is located columnar body one end between the star and be located the columnar body other end with spacing boss of spacing draw-in groove matched with, when piling up the setting, the interface realizes transversely spacing through spacing boss and spacing draw-in groove between two adjacent stars.
Among the above-mentioned technical scheme, realize location and horizontal spacing through spacing boss and spacing draw-in groove, interface simple structure between the star, and the interface between the star of the satellite of group transmission keeps unanimous, makes the batch production of satellite more high-efficient convenient.
The utility model discloses an in a preferred embodiment, elastic mechanism includes the spring, the one end of spring and the spacing draw-in groove bottom butt of bottommost intersatellite interface, the other end of spring and the base butt on the rocket delivery.
Among the above-mentioned technical scheme, when not unblock the separation, the spring is in compression state with the energy storage, and during the unblock separation, the spring provides power for the satellite in orbit unblock on the one hand, and on the other hand plays the effect of buffering.
The utility model discloses an in the preferred embodiment, the middle part of the columnar body has the through-hole, and spacing draw-in groove is the through-hole at columnar body middle part, and spacing boss inserts in the through-hole. The through hole in the middle of the cylindrical body can reduce the weight, and compared with the clamping groove formed in the cylindrical body, the structure of the inter-satellite interface can be further simplified.
The utility model discloses an in another kind of preferred embodiment, the inboard and the outside of every satellite all are equipped with the interface between the star, are the interface between first star and second star respectively, connect through the interface between first star between two adjacent satellites that two crisscross settings of satellite were listed as, connect through the interface between the second star between two adjacent satellites of every satellite.
In another preferred embodiment of the present invention, the inner side of each satellite is provided with two first inter-satellite interfaces, and the outer side of each satellite is provided with one second inter-satellite interface. The number of the inter-satellite interfaces of each satellite is reasonably set.
In another preferred embodiment of the present invention, the two first inter-satellite interfaces of each satellite are respectively located at two ends of the satellite, and the second inter-satellite interface of each satellite is located at the middle part of the satellite outside. The position of the inter-satellite interface of each satellite is reasonably set, so that the stress is more uniform, and the connection is more stable.
In another preferred embodiment of the present invention, the number of the satellite-rocket connecting mechanisms is four, and the four satellite-rocket connecting mechanisms are respectively located between the bottommost two first inter-satellite interfaces and two second inter-satellite interfaces and the rocket carrier. And a satellite and arrow connecting mechanism is correspondingly arranged at each row of inter-satellite interfaces, and the satellite and arrow connecting mechanisms and the inter-satellite interfaces are also overlapped into a row, so that the installation is more convenient.
Compared with the prior art, the utility model, following beneficial effect has:
1) the satellite mass transmitting device can simultaneously realize the stacking and transmitting of a large number of satellites, has high transmitting efficiency, greatly reduces the transmitting cost, and provides guarantee for the satellite mass transmitting and the constellation construction.
2) The expandability of one-rocket multi-satellite launching can be realized, the stacking of satellites in batches can be realized on the premise of meeting the envelope, the launching of any number of satellites can be realized, and more possible choices are provided for networking.
3) The interfaces among the satellites transmitted in batches are kept consistent, so that the design and manufacture of the satellites are unified, and the batch production of the satellites is more efficient and convenient.
4) The assembly of each satellite before launching is simple, and it is convenient to pile up the arrangement, and the requirement is loose, satisfies the security requirement in the launch process, and the on-orbit unblock is safe convenient.
Additional aspects and advantages of the invention will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the invention.
Drawings
The above and/or additional aspects and advantages of the present invention will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings of which:
fig. 1 is a schematic structural diagram of a satellite stacking architecture for low earth orbit satellite group transmission according to a first embodiment.
Fig. 2 is a schematic cross-sectional structural diagram of connection between first inter-satellite interfaces in the first embodiment.
Fig. 3 is a schematic cross-sectional structural diagram of connection between second inter-satellite interfaces in the first embodiment.
Fig. 4 is a schematic structural diagram of a low earth orbit satellite group transmission satellite-rocket separation unlocking module according to the second embodiment.
Reference numerals in the drawings of the specification include: the rocket carrier comprises a rocket carrier 10, a satellite 20, an inter-satellite interface 30, a first inter-satellite interface 301, a second inter-satellite interface 302, a cylindrical body 31, a limiting clamping groove 311, a limiting boss 312, a satellite and rocket connecting mechanism 40, an elastic mechanism 41, a connecting and separating device 50, a pull rod 51, a pressure bearing body 52 and a pressing plate 53.
Detailed Description
Reference will now be made in detail to the embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like reference numerals refer to the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the drawings are exemplary only for the purpose of explaining the present invention, and should not be construed as limiting the present invention.
In the description of the present invention, it is to be understood that the terms "longitudinal", "lateral", "vertical", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be construed as limiting the present invention.
In the description of the present invention, unless otherwise specified and limited, it is to be noted that the terms "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, mechanically or electrically connected, or may be connected between two elements through an intermediate medium, or may be directly connected or indirectly connected, and specific meanings of the terms may be understood by those skilled in the art according to specific situations.
Example one
The embodiment provides a satellite stacking structure for low-earth-orbit satellite group launching, as shown in fig. 1, in a preferred embodiment, the satellite stacking structure comprises an inter-satellite interface 30 and a satellite-rocket connecting mechanism 40, a plurality of satellites 20 are arranged on a rocket carrier 10 in an overlapping manner and are arranged in a left-right two-column staggered manner, the shape and the size of each satellite 20 are the same, the rocket carrier 10 is connected with the satellites 20 at the bottom through the satellite-rocket connecting mechanism 40, two adjacent satellites 20 are connected through the inter-satellite interface 30, the satellite-rocket connecting mechanism 40 is provided with an elastic mechanism 41 capable of providing power for satellite-rocket separation, and the elastic mechanism 41 provides power for in-orbit unlocking of the satellites 20 and plays a role in buffering.
In another preferred embodiment, the inter-satellite interfaces 30 are connected in a nested manner by the columns 31 and are overlapped into a column. As shown in fig. 2 and 3, the first inter-satellite interface 301 and the second inter-satellite interface 302 have the same structure, each inter-satellite interface 30 includes a limiting slot 311 located at one end of the cylindrical body 31 and a limiting boss 312 located at the other end of the cylindrical body 31 and engaged with the limiting slot 311, for example, the limiting boss 312 is disposed above the limiting slot 311, the limiting boss 312 on the lower satellite 20 is inserted into the limiting slot 311 of the upper satellite 20, and when the inter-satellite interfaces 30 are stacked, the adjacent two inter-satellite interfaces 30 realize transverse limiting through the limiting boss 312 and the limiting slot 311.
Preferably, the middle of the cylindrical body 31 has a through hole, the limiting slot 311 is the through hole in the middle of the cylindrical body 31, the limiting boss 312 is an annular boss that is arranged at the top of the cylindrical body 31 and extends radially inward and then upward, an outer step is arranged between the top end of the cylindrical body 31 and the limiting boss 312, the limiting boss 312 is inserted into the through hole, the outer step of the limiting boss 312 abuts against the bottom end of the cylindrical body 31, and the limiting boss 312 is used for positioning and transverse limiting.
In another preferred embodiment, the satellite-rocket connecting mechanism 40 is mounted in the same way as the inter-satellite connecting mechanism, and provides limiting and transverse shearing force for the manner of utilizing columnar body nesting, so that the stability of the transverse position is ensured.
In another preferred embodiment, as shown in fig. 1, the inter-satellite interface 30 is disposed inside and outside each satellite 20, the first inter-satellite interface 301 is disposed inside, the second inter-satellite interface 302 is disposed outside, preferably, two first inter-satellite interfaces 301 respectively located at two ends inside each satellite 20 are disposed inside each satellite 20, and one second inter-satellite interface 302 is disposed in the middle of the outside of each satellite 20. Two adjacent columns of satellites 20 (one satellite in the left column and one satellite in the right column) which are arranged in a staggered manner by the satellites 20 are connected through a first inter-satellite interface 301, two adjacent satellites 20 in each column of satellites 20 are connected through a second inter-satellite interface 302, and four columns of inter-satellite interfaces 30, two columns of the first inter-satellite interfaces 301 and two columns of the second inter-satellite interfaces 302 are arranged in an overlapped manner.
In the present embodiment, as shown in fig. 1, the number of the satellite-rocket connecting mechanisms 40 is four, and four satellite-rocket connecting mechanisms 40 are respectively located between the bottommost two first inter-satellite interfaces 301 and two second inter-satellite interfaces 302 and the rocket carrier 10, that is, one satellite-rocket connecting mechanism 40 is respectively arranged at the bottommost inter-satellite interface of each row of inter-satellite interfaces.
In the present embodiment, the elastic mechanism 41 included in the satellite-rocket coupling mechanism 40 includes a spring, an upper end of the spring abuts against the bottom of the limit slot 311 of the bottommost inter-satellite interface 30, and a lower end of the spring abuts against the base on the rocket carrier 10. When the separation is not unlocked, the spring is in a compressed state, and when the separation is unlocked, the compressed spring releases elastic potential energy to provide power for the separation of the star and the arrow.
By adopting the technical scheme, the stacked satellites 20 are divided into two left columns and two right columns, and the two columns of satellites 20 are staggered to form a whole. Three inter-satellite interfaces 30 are distributed on each satellite 20 to bear load during launching, the single second inter-satellite interface 302 on the outer side is connected with the second inter-satellite interfaces 302 of the satellites 20 above and below the single second inter-satellite interface 302, the two first inter-satellite interfaces 301 on the inner side are connected with the first inter-satellite interfaces 301 of the satellites 20 above and below the inner side in parallel, a mutually staggered overlapping mode is formed, and a plurality of satellites 20 stacked by means of axial overload during launching form a whole.
Example two
The embodiment provides a low-earth-orbit satellite batch transmitting satellite-arrow separating and unlocking module, which can be applied to the satellite stacking architecture of the low-earth-orbit satellite batch transmitting of the first embodiment. As shown in fig. 4, in a preferred embodiment, the satellite-rocket separation unlocking module includes several groups of connection and separation devices 50 fixed on the rocket carrier 10, each group of connection and separation devices 50 includes two pull rods 51 connected with the rocket carrier 10 and extending along the stacking direction of the satellites 20, the joints (i.e., the pull rod roots) between the pull rods 51 and the rocket carrier 10 are provided with first initiating explosive devices (not shown in the drawings), the tail ends (the upper ends in fig. 4) of the two pull rods 51 are connected with a pressing plate 53 located outside the terminal satellite 20, a pressure-bearing body 52 is pressed between the pressing plate 53 and the terminal satellite 20, and the pressure-bearing body 52 is pressed between the pressing plate 53 and the inter-satellite interface 30 of the terminal satellite. In fig. 4, four sets of connection and separation devices 50 are provided, one set of connection and separation device 50 is provided at each row of inter-satellite interfaces 30, and two pull rods 51 of the connection and separation device 50 are respectively located at two sides of each row of inter-satellite interfaces 30.
When the two rows of satellites 20 are not unlocked and separated, the pull rod 51 of the connecting and separating device 50 bears the pulling force, the pressure bearing body 52 bears the pressure, and the connecting and separating device 50 carries out vertical limiting on the two rows of satellites 20.
In the present embodiment, a second initiating explosive device (not shown in the figure) is disposed inside the pressure-bearing body 52, for example, the pressure-bearing body 52 is a circular ring composed of two semicircular rings, and the second initiating explosive device is disposed inside the circular ring.
In the present embodiment, the inside of the satellite-rocket connecting mechanism 40 for connecting the rocket vehicle 10 and the satellite 20 is provided with an explosive bolt, and the explosive bolt is an explosive separating bolt which plays a role in connecting and fastening and has initiating explosive devices in the prior art and can break the bolt body, such as the explosive bolts disclosed in CN201810581584.4, CN201710430885.2, CN201510466049.0 or CN 202020002414.9. Of course, the satellite-rocket connecting mechanism 40 may also adopt the structure of the satellite-rocket point-type connecting and disconnecting module disclosed in CN201610538456.2 to realize the connection and disconnection between the rocket carrier 10 and the satellite 20.
The specific separation process comprises the following steps:
the method comprises the following steps: all the connecting and separating devices 50 are unlocked simultaneously, specifically, all the pull rods 51 and the first initiating explosive devices connected with the carrier and all the second initiating explosive devices in the pressure bearing bodies 52 explode simultaneously, the pressure bearing bodies 52 are divided into two halves, the roots of the pull rods 51 are burst, and the pull rods 51 and the pressure bearing bodies 52 of the connecting and separating devices 50 do not bear force any more.
Step two: all the connecting and disconnecting devices 50 are disconnected from the satellite and rocket and leave the satellite and rocket assembly (when the satellite and the rocket are not disconnected, the satellite and the rocket are taken as a whole and are called the satellite and rocket assembly).
Step three: the satellite and arrow fly in a designated manner, and the satellite and arrow generally start to rotate slowly around the Z axis (forming an angle of 45 degrees with each satellite). The fact that the rocket flies in a designated manner means that the rocket and the satellite firstly enter a parking orbit (the orbit and a working orbit are in the same plane and have different heights) and automatically fly according to a preset flying program, wherein the flying program is set from launching to entering, and is not an innovative point of the invention and is not described in detail herein.
Step four: after the satellite and the arrow are totally and slowly rotated and stabilized, the satellite and the arrow connecting mechanism 40 is unlocked to release energy, specifically, the explosion bolt explodes, and the compressed spring releases elastic potential energy to provide power for the separation of the satellite and the arrow.
Step five: the satellites 20 are separated from the carrier under the action of energy released by unlocking the satellite-rocket connecting mechanism 40 and centrifugal force generated by slow rotation, and separation is completed. Because the two rows of satellites 20 are subjected to different centrifugal force directions, the two rows of satellites 20 are slowly separated, the centrifugal force applied to each satellite 20 in the same row is different, the satellite 20 at the outer end farther away from the Z axis is subjected to large centrifugal force and high speed, and the satellites cannot collide.
In the description herein, reference to the description of the terms "preferred embodiment," "one embodiment," "some embodiments," "an example," "a specific example" or "some examples" or the like means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.
While embodiments of the present invention have been shown and described, it will be understood by those of ordinary skill in the art that: various changes, modifications, substitutions and alterations can be made to the embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the claims and their equivalents.
Claims (8)
1. A satellite stacking framework for low-earth-orbit satellite group launching is characterized by comprising an inter-satellite interface and a satellite and arrow connecting mechanism, wherein a plurality of satellites are overlapped and divided into a left row and a right row which are staggered, adjacent satellites are connected through the inter-satellite interface, and the satellite and arrow connecting mechanism is provided with an elastic mechanism capable of providing power for separating the satellites and the arrows;
the inner side and the outer side of each satellite are respectively provided with an inter-satellite interface which is a first inter-satellite interface and a second inter-satellite interface, two adjacent rows of satellites which are arranged in a staggered mode are connected through the first inter-satellite interface, and two adjacent satellites of each row of satellites are connected through the second inter-satellite interface.
2. The stacked architecture as claimed in claim 1, wherein the inter-satellite interfaces are connected in a nested manner by using a cylindrical structure.
3. The stacked architecture as claimed in claim 2, wherein each inter-satellite interface comprises a limiting slot at one end of the cylindrical body and a limiting boss at the other end of the cylindrical body, the limiting boss being engaged with the limiting slot, and when the stacked architecture is configured, two adjacent inter-satellite interfaces are laterally limited by the limiting boss and the limiting slot.
4. The stacked architecture of low earth orbit satellite group launching as claimed in claim 3, wherein the elastic mechanism comprises a spring, one end of the spring is abutted with the bottom of the limiting slot of the bottommost inter-satellite interface, and the other end of the spring is abutted with the base on the rocket carrier.
5. The stacked architecture for satellites in low earth orbit as set forth in claim 3, wherein the middle of the cylindrical body has a through hole, the limiting slot is a through hole in the middle of the cylindrical body, and the limiting boss is inserted into the through hole.
6. The stacked architecture of satellites as claimed in any one of claims 1-5 wherein each satellite has two first inter-satellite interfaces on the inside and one second inter-satellite interface on the outside.
7. The stacked architecture as claimed in claim 6, wherein the two first inter-satellite interfaces of each satellite are respectively located at two ends of the inner side of the satellite, and the second inter-satellite interface of each satellite is located at the middle of the outer side of the satellite.
8. The satellite stacking architecture for low earth orbit satellite group launching as claimed in claim 6, wherein the number of the satellite-rocket connecting mechanisms is four, and four satellite-rocket connecting mechanisms are respectively located between the two first inter-satellite interfaces and the two second inter-satellite interfaces at the bottommost and the rocket carrier.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202022742901.1U CN213769017U (en) | 2020-11-24 | 2020-11-24 | Satellite stacking structure for low-earth-orbit satellite group transmission |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202022742901.1U CN213769017U (en) | 2020-11-24 | 2020-11-24 | Satellite stacking structure for low-earth-orbit satellite group transmission |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113619812A (en) * | 2021-09-10 | 2021-11-09 | 赛德雷特(珠海)航天科技有限公司 | Standard modular microsatellite system |
| CN113753263A (en) * | 2021-09-14 | 2021-12-07 | 上海卫星工程研究所 | Stacked satellite launching structure |
| CN113998156A (en) * | 2021-12-15 | 2022-02-01 | 北华航天工业学院 | Pneumatic satellite-rocket separation system |
| CN114084381A (en) * | 2021-11-11 | 2022-02-25 | 长光卫星技术有限公司 | Satellite and arrow separation system suitable for one-arrow-multiple-star launching and separation method thereof |
| CN115675938A (en) * | 2022-11-21 | 2023-02-03 | 北京中科宇航技术有限公司 | Low-orbit mobile stack constellation satellite unlocking distributor |
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2020
- 2020-11-24 CN CN202022742901.1U patent/CN213769017U/en active Active
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113619812A (en) * | 2021-09-10 | 2021-11-09 | 赛德雷特(珠海)航天科技有限公司 | Standard modular microsatellite system |
| CN113753263A (en) * | 2021-09-14 | 2021-12-07 | 上海卫星工程研究所 | Stacked satellite launching structure |
| CN114084381A (en) * | 2021-11-11 | 2022-02-25 | 长光卫星技术有限公司 | Satellite and arrow separation system suitable for one-arrow-multiple-star launching and separation method thereof |
| CN114084381B (en) * | 2021-11-11 | 2024-03-19 | 长光卫星技术股份有限公司 | Satellite-rocket separation system suitable for launching one rocket with multiple satellites and separation method thereof |
| CN113998156A (en) * | 2021-12-15 | 2022-02-01 | 北华航天工业学院 | Pneumatic satellite-rocket separation system |
| CN113998156B (en) * | 2021-12-15 | 2023-11-14 | 北华航天工业学院 | Pneumatic type satellite and rocket separation system |
| CN115675938A (en) * | 2022-11-21 | 2023-02-03 | 北京中科宇航技术有限公司 | Low-orbit mobile stack constellation satellite unlocking distributor |
| CN115675938B (en) * | 2022-11-21 | 2024-04-26 | 北京中科宇航技术有限公司 | Low-orbit mobile stack constellation satellite unlocking distributor |
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