CN213677217U - High-adaptability stacked satellite platform structure with one arrow and two or more satellites - Google Patents
High-adaptability stacked satellite platform structure with one arrow and two or more satellites Download PDFInfo
- Publication number
- CN213677217U CN213677217U CN202022889767.8U CN202022889767U CN213677217U CN 213677217 U CN213677217 U CN 213677217U CN 202022889767 U CN202022889767 U CN 202022889767U CN 213677217 U CN213677217 U CN 213677217U
- Authority
- CN
- China
- Prior art keywords
- satellite
- inter
- butt joint
- rocket
- carrying
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 210000001503 joint Anatomy 0.000 claims abstract description 113
- 238000000926 separation method Methods 0.000 claims abstract description 105
- 230000007246 mechanism Effects 0.000 claims abstract description 31
- 238000003032 molecular docking Methods 0.000 claims description 110
- 238000004880 explosion Methods 0.000 claims description 39
- 239000002360 explosive Substances 0.000 claims description 26
- 238000003825 pressing Methods 0.000 claims description 25
- 230000007274 generation of a signal involved in cell-cell signaling Effects 0.000 claims 1
- 230000005540 biological transmission Effects 0.000 abstract description 7
- 238000010276 construction Methods 0.000 abstract description 4
- 238000010008 shearing Methods 0.000 description 6
- 238000010586 diagram Methods 0.000 description 4
- 230000009471 action Effects 0.000 description 3
- 238000009434 installation Methods 0.000 description 3
- 238000005381 potential energy Methods 0.000 description 3
- 230000004044 response Effects 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000001960 triggered effect Effects 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 238000010923 batch production Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000003139 buffering effect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000006855 networking Effects 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000001737 promoting effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 230000009469 supplementation Effects 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
Images
Abstract
The utility model provides a high-adaptability stacked satellite platform structure with one arrow and two or more satellites, which comprises a carrying butt joint base and two or more satellites overlapped on the carrying butt joint base; the carrying butt joint base is provided with a carrying butt joint structure, the satellite at the bottommost part is provided with a satellite and arrow butt joint structure, and the carrying butt joint structure is connected with the satellite and arrow butt joint structure through a satellite and arrow connection and separation mechanism; two adjacent satellites are in butt joint through a first inter-satellite butt joint structure and a second inter-satellite butt joint structure, and the first inter-satellite butt joint structure is connected with the second inter-satellite butt joint structure through an inter-satellite connection and separation mechanism. The utility model discloses overlap on the delivery butt joint base and set up two and above satellites, to launching demand and the reasonable satellite transmission quantity of confirming of delivery restraint, have the advantage that scalability is strong, high adaptability, can realize the group of small batch satellite in addition and criticize the transmission, improve emission efficiency, establish the basis for the construction of satellite constellation.
Description
Technical Field
The utility model belongs to the technical field of space satellite, concretely relates to heap a arrow two stars or multi-star satellite platform configuration of high adaptability.
Background
With the rapid development of low-orbit satellite internet, single-satellite transmission can not meet the requirement of constellation construction, and the satellite batch transmission technology becomes a trend. The launching of large-batch satellites is difficult to technically realize due to the limitation of carrying and production capacity, and the launching of small-batch satellites has the advantages of good adaptability, simplicity, high efficiency, flexibility, maneuverability and the like, and is widely applied to the field of aerospace.
At present, small-batch satellite launching mainly uses a distributor to carry out satellite launching and in-orbit separation, the space and weight utilization rate of carrying caused by the distributor is reduced, and under different quantity launching modes and different carrying conditions, the distributor needs to be redeveloped, the expandability is poor, the waste of time and production cost is caused, and particularly, the launching progress is seriously influenced on a quick response task.
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 heap of high adaptability arrow two stars or multi-star satellite platform configuration to improve emission efficiency, establish the basis for the construction of satellite constellation.
In order to achieve the above purpose, the utility model adopts the following technical scheme: a high-adaptability stacked satellite platform structure with one rocket and two or more satellites comprises a carrying butt joint base and two or more satellites overlapped on the carrying butt joint base; the carrying butt joint base is provided with a carrying butt joint structure, the satellite at the bottommost part is provided with a satellite and arrow butt joint structure matched with the carrying butt joint structure, and the carrying butt joint structure is connected with the satellite and arrow butt joint structure through a satellite and arrow connection and separation mechanism; between two adjacent satellites, one satellite has a first inter-satellite docking structure, the other satellite has a second inter-satellite docking structure matched with the first inter-satellite docking structure, and the first inter-satellite docking structure is connected with the second inter-satellite docking structure through an inter-satellite connection and separation mechanism.
According to the technical scheme, the two or more satellites are overlapped on the delivery butt joint base, the satellite emission quantity is reasonably determined according to the emission requirements and the delivery constraints, the advantages of high expandability and high adaptability are achieved, batch emission of small-batch satellites can be achieved, the emission efficiency is improved, and a foundation is laid for satellite constellation construction.
In a preferred embodiment of the present invention, the satellite-rocket connecting and separating mechanism includes a satellite-rocket explosive bolt assembly and a satellite-rocket separating spring, the satellite-rocket explosive bolt assembly connects the carrying butt-joint structure with the satellite-rocket butt-joint structure, the explosion of the satellite-rocket explosive bolt assembly can separate the whole satellite from the rocket, the satellite-rocket separating spring is pressed between the carrying butt-joint structure and the satellite-rocket butt-joint structure, and the satellite-rocket separating spring provides power for the separation of the satellite and the rocket during the separation of the satellite and the rocket;
the inter-satellite connection and separation mechanism comprises an inter-satellite explosion bolt assembly and an inter-satellite separation spring, the inter-satellite explosion bolt assembly connects the first inter-satellite butt joint structure with the second inter-satellite butt joint structure, the inter-satellite explosion bolt assembly explodes to enable the satellites to be separated, the inter-satellite separation spring is arranged between the first inter-satellite butt joint structure and the second inter-satellite butt joint structure in a pressing mode, and during inter-satellite separation, the inter-satellite separation spring provides power for separation between the satellites.
In the technical scheme, when the satellite and the arrow are in butt joint, the carrying butt joint base and the bottommost satellite are fastened by using the satellite and the arrow explosion bolt assembly, and the satellite and the arrow separation spring are in a compressed state; when the star and the arrow are separated, the star and the arrow explosion bolt assemblies explode to unlock, and the star and the arrow separation springs release elastic potential energy to provide power for the separation of the star and the arrow. When the satellites are in butt joint, the two adjacent satellites are fastened by using the inter-satellite explosive bolt assembly, and the inter-satellite separation spring is in a compressed state; when the satellites are separated, the inter-satellite explosion bolt assembly explodes to unlock, and the inter-satellite separation spring releases elastic potential energy to provide power for inter-satellite separation.
In a preferred embodiment of the present invention, the satellite-rocket explosive bolt assembly comprises paired explosive bolts and nuts, and the carrying butt-joint structure and the satellite-rocket butt-joint structure are connected by the explosive bolts and fastened by the nuts; the structure of the inter-satellite explosive bolt assembly is the same as that of the satellite-rocket explosive bolt assembly.
In a preferred embodiment of the present invention, the head of the explosion bolt of the satellite and rocket explosion bolt assembly is clamped in the satellite and rocket docking structure, the nut thereof is located inside the carrying docking structure, and the inside of the carrying docking structure is provided with the buffer member wrapped outside the nut;
the head of the explosion bolt of the inter-satellite explosion bolt assembly is clamped in the first inter-satellite butt joint structure, the nut of the explosion bolt assembly is located inside the second inter-satellite butt joint structure, and the buffer piece wrapped outside the nut is arranged inside the first inter-satellite butt joint structure.
Among the above-mentioned technical scheme, when separation between star arrow/star, explosion bolt disconnection, explosion bolt head stop on carrying butt joint structure/second inter-star butt joint structure, and the nut part collides with the bolster under the impact force effect, and the bolster plays the effect of accomodating the nut when reducing the impact force.
In a preferred embodiment of the present invention, the carrying butt joint structure/the first inter-satellite butt joint structure has a lower pressing plate, the satellite-rocket butt joint structure/the second inter-satellite butt joint structure has an upper pressing plate disposed opposite to the lower pressing plate, and the satellite-rocket separation spring/the inter-satellite separation spring sleeve is disposed between the upper pressing plate and the lower pressing plate; the carrying butt joint structure/the first inter-satellite butt joint structure is fixedly connected with a guide rod, the upper portion of the guide rod penetrates through the lower pressing plate and extends upwards, the lower pressing plate is in threaded connection with the guide rod, the upper end of the guide rod is a free end, and the satellite-rocket separation spring/the inter-satellite separation spring is sleeved on the guide rod.
Among the above-mentioned technical scheme, through setting up the guide bar, and holding down plate and guide bar threaded connection, before the satellite launch, through the position of vertical regulation holding down plate on the guide bar to adjust the pretightning force of satellite-rocket separation spring and separation spring between the star, make satellite-rocket separation spring and separation spring between the star's elasticity adjustable.
In another preferred embodiment of the present invention, a separation travel switch is disposed between the carrying docking structure and the satellite-rocket docking structure, and between the first inter-satellite docking structure and the second inter-satellite docking structure, and when the satellite-rocket/satellite is separated, the separation travel switch is used for generating a signal for separating between the satellite-rocket/satellite to complete the start-up of the satellite.
According to the technical scheme, when the satellite is launched, the separation travel switch is closed, the satellite is in a power-off state, when the satellite and the rocket/the satellite are separated, the separation travel switch is activated along with the separation of the satellite, the rocket/the satellite and the satellite, the satellite whole satellite corresponding to the separation travel switch is started, the step-by-step separation is realized, and the satellites cannot collide with one another.
In another preferred embodiment of the present invention, the carrying docking structure is a lower column disposed on the carrying docking base, and the satellite-rocket docking structure is an upper column disposed on the bottommost satellite; between two adjacent satellites, the first inter-satellite docking structure is a lower upright column arranged on the satellite below, and the second inter-satellite docking structure is an upper upright column arranged on the satellite above.
Among the above-mentioned technical scheme, go up the stand and pair the setting down, for the frame that supports the satellite, be convenient for the satellite with carry the butt joint base, the satellite is connected with the satellite.
In another preferred embodiment of the present invention, one of the paired lower and upper columns is provided with a shear-resistant boss which is nested and matched with the other column.
The utility model discloses an in another preferred embodiment, the quantity of carrying butt joint structure and star arrow butt joint structure equals and the one-to-one setting with the quantity of butt joint structure between first star and second star. Therefore, the connection positions of the satellite, the carrying support and the two adjacent satellites are the same, the installation is convenient, and the stress is balanced.
In another preferred embodiment of the present invention, the number of the carrying butt joint structures and the satellite-rocket butt joint structures is four, and the four carrying butt joint structures and the four satellite-rocket butt joint structures are distributed at four corners of the satellite at the bottommost in pairs; the number of the first inter-satellite butt joint structures and the number of the second inter-satellite butt joint structures are four, and four first inter-satellite butt joint structures and four second inter-satellite butt joint structures are distributed at four corners between two adjacent satellites in pairs. All the butt joint structures are arranged at the corners, so that the installation is convenient.
Compared with the prior art, the beneficial effects of the utility model are as follows:
1) the utility model discloses an emission mode has high mobility, responds advantages such as quick, the superstrong delivery adaptability of response, and the specially adapted emergency response satellite, the constellation mend the transmission of net satellite fast, have the significance to promoting the development of little satellite scale.
2) The design of the satellite meets the requirement of satellite batch production, can adapt to different delivery according to the requirement of the satellite size, and has good delivery adaptability to rapid networking of small constellations and network supplementation of the existing constellations.
3) The expandability of a stacked transmitting mode is met, and the satellite transmitting quantity is reasonably determined according to the transmitting requirement and the carrying constraint.
4) The utility model discloses the atress characteristic of satellite-borne arrow before the satellite transmission, emission in-process is fully considered to and the buffering of separating between on-orbit unblock, surplus thing collection, impact force between on-orbit satellite-borne arrow and star.
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 high-adaptability stacked rocket-two-star satellite platform configuration according to an embodiment of the present application.
Fig. 2 is a schematic structural diagram of the connection between the satellite-arrow connection and disconnection mechanism and the carrying docking structure and the satellite-arrow docking structure in the first embodiment of the present application.
Fig. 3 is a schematic structural diagram of a connection between the inter-satellite connection separation mechanism and the first inter-satellite docking structure and the second inter-satellite docking structure in the first embodiment of the present application.
Fig. 4 is a schematic structural diagram of a high-adaptability stacked samsung satellite platform configuration according to the second embodiment of the present application.
Reference numerals in the drawings of the specification include: the device comprises a carrying butt joint base 10, a satellite 20, a carrying butt joint structure 31, a satellite and arrow butt joint structure 32, a first inter-satellite butt joint structure 33, a second inter-satellite butt joint structure 34, an anti-shearing boss 35, a satellite and arrow butt joint surface 41, an inter-satellite butt joint surface 42, a satellite and arrow connection and separation mechanism 50, a satellite and arrow explosion bolt assembly 51, an explosion bolt 511, a nut 512, a satellite and arrow separation spring 52, an upper pressing plate 521, a lower pressing plate 522, a guide rod 523, a buffer 54, an inter-satellite connection and separation mechanism 60, an inter-satellite explosion bolt assembly 61, an inter-satellite separation spring 62 and a separation travel switch 70.
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 high-adaptability stacked rocket-two-satellite platform configuration, as shown in fig. 1, in a preferred embodiment, the high-adaptability stacked rocket-two-satellite platform configuration comprises a carrying docking base 10 and two satellites 20 overlapped on the carrying docking base 10, wherein the first satellite and the second satellite are respectively arranged from bottom to top, the two satellites 20 have the same shape and size, and the two satellites 20 are divided into an upper layer and a lower layer.
The carrying docking structure 31 is arranged on the carrying docking base 10, the satellite and arrow docking structure 32 matched with the carrying docking structure 31 is arranged on the first satellite 20, the docking surface of the carrying docking structure 31 and the satellite and arrow docking structure 32 is a satellite and arrow docking surface 41, and the carrying docking structure 31 and the satellite and arrow docking structure 32 are connected through the satellite and arrow connecting and separating mechanism 50, so that the first satellite 20 and the carrying docking base 10 are fastened and connected.
One of the satellites 20 has a first inter-satellite docking structure 33, the other satellite 20 has a second inter-satellite docking structure 34 that is matched with the first inter-satellite docking structure 33, for example, the first inter-satellite docking structure 33 is on the first satellite 20, the second inter-satellite docking structure 34 is on the second satellite 20, the interface where the first inter-satellite docking structure 33 and the second inter-satellite docking structure 34 are docked is an inter-satellite docking interface 42, and the first inter-satellite docking structure 33 and the second inter-satellite docking structure 34 are connected by an inter-satellite connection and separation mechanism 60, so as to realize a tight connection between the first satellite 20 and the second satellite 20.
In the present embodiment, the number of the carrying butt joint structures 31 and the satellite-rocket butt joint structures 32 is equal to the number of the first inter-satellite butt joint structures 33 and the second inter-satellite butt joint structures 34, and the carrying butt joint structures and the satellite-rocket butt joint structures are arranged in one-to-one correspondence. Preferably, the number of the carrying butt joint structures 31 and the satellite and arrow butt joint structures 32 is four, the front ends are two, the rear ends are two, and the four carrying butt joint structures 31 and the four satellite and arrow butt joint structures 32 are distributed on four corners of the first satellite 20 in pairs; the number of the first inter-satellite docking structures 33 and the number of the second inter-satellite docking structures 34 are four, the number of the first inter-satellite docking structures 33 is two at the front end, the number of the second inter-satellite docking structures 34 is two at the rear end, and the four first inter-satellite docking structures 33 and the four second inter-satellite docking structures 34 are distributed at four corners between the first satellite 20 and the second satellite 20 in pairs.
During installation, the carrying docking base 10 is connected with the four satellite-rocket docking structures 32 on the first satellite 20 through the four carrying docking structures 31, and then is fixed by the four satellite-rocket connecting and separating mechanisms 50; the first satellite 20 is connected to four second inter-satellite docking structures 34 of the second satellite 20 by four first inter-satellite docking structures 33, and then fixed by four inter-satellite connection and separation mechanisms 60. After the launch vehicle docking station 10 is integrated with all satellites 20, the launch vehicle docking station 10 is mounted on an external rocket vehicle.
When the satellite and the rocket are separated, the satellite and rocket connecting and separating mechanism 50 is unlocked, the whole satellite is separated from the carrying butt joint base 10, and the separation of the whole satellite and the rocket is realized; when the satellites are separated, the inter-satellite connection and separation mechanism 60 is unlocked, and the first satellite 20 is separated from the second satellite 20. In the present embodiment, the satellite-rocket connection and separation mechanism 50 and the inter-satellite connection and separation mechanism 60 may both adopt a connection and separation mechanism in the related art, such as a belted unlocking and separation device driven by an explosive bolt 511 disclosed in CN201510143772.5 or an explosive bolt 511 buffer device disclosed in CN 201711335636.1.
As shown in fig. 1-3, the carrying docking structure 31 is a lower column disposed on the carrying docking base 10, the satellite docking structure 32 is an upper column disposed on the first satellite 20, and a docking surface of the upper column and the lower column is a satellite docking surface 41. Between the first satellite 20 and the second satellite 20, the first inter-satellite docking structure 33 is a lower upright disposed on the first satellite 20, the second inter-satellite docking structure 34 is an upper upright disposed on the second satellite 20, and a docking surface between the upper upright and the lower upright is an inter-satellite docking surface 42. Preferably, one of the lower and upper matching columns is provided with an anti-shearing boss 35 which is in nesting fit with the other column, for example, the anti-shearing boss 35 is provided at the top of the lower column, the upper column is provided with a groove which is in clamping fit with the anti-shearing boss 35, and the anti-shearing boss 35 plays a role in positioning and resisting a transverse load when the satellite 20 is launched.
In another preferred embodiment, as shown in FIG. 2, the satellite-to-rocket connecting and disconnecting mechanism 50 comprises a satellite-to-rocket explosive bolt assembly 51 and a satellite-to-rocket disconnecting spring 52.
The satellite and rocket explosion bolt assembly 51 connects the carrying butt joint structure 31 and the satellite and rocket butt joint structure 32 together, and the satellite and rocket explosion bolt assembly 51 can separate the whole satellite from the rocket. Specifically, the satellite-rocket explosive bolt assembly 51 comprises a pair of explosive bolts 511 and nuts 512, and the carrying butt joint structure 31 and the satellite-rocket butt joint structure 32 are connected through the explosive bolts 511 and fastened through the nuts 512. Preferably, the head of the explosion bolt 511 of the satellite-rocket connection and separation mechanism 50 is clamped in the satellite-rocket docking structure 32, the nut 512 of the bolt is located inside the carrying docking structure 31, the inside of the carrying docking structure 31 is provided with the buffer 54 wrapped outside the nut 512, when the satellite and the rocket are separated, the explosion bolt 511 is disconnected, the head of the explosion bolt 511 stays in the second inter-satellite docking structure 34 of the second satellite 20, the nut 512 collides with the buffer 54 under the action of the explosion impact force, and the buffer 54 plays a role in accommodating the nut 512 while reducing the impact force.
The satellite-arrow separation spring 52 is pressed between the carrying butt joint structure 31 and the satellite-arrow butt joint structure 32, before separation of the satellite and the arrow, the satellite-arrow separation spring 52 is in a compressed state, and when the satellite and the arrow are separated, the satellite-arrow separation spring 52 releases elastic potential energy to provide power for separation of the satellite and the arrow. Specifically, the carrying docking structure 31 has a lower pressing plate 522, the satellite and rocket docking structure 32 has an upper pressing plate 521 disposed opposite to the lower pressing plate 522, and the satellite and rocket separating spring 52 is pressed between the upper pressing plate 521 and the lower pressing plate 522; preferably, the carrying and docking structure 31 is fixedly connected with a guide rod, the upper part of the guide rod penetrates through the lower pressing plate 522 and extends upwards, the upper end of the guide rod is a free end, and the satellite-rocket separation spring 52 is sleeved on the guide rod; further preferably, the lower pressing plate 522 is in threaded connection with the guide rod, and the position of the lower pressing plate 522 is vertically adjusted on the guide rod, so as to adjust the pretightening force (elastic force) of the satellite-rocket separation spring 52.
As shown in fig. 3, the inter-satellite connection and separation mechanism 60 includes an inter-satellite explosive bolt assembly 61 and an inter-satellite separation spring 62, the inter-satellite explosive bolt assembly 61 connects the first inter-satellite docking structure 33 and the second inter-satellite docking structure 34 together, the inter-satellite explosive bolt assembly 61 explodes to separate the first satellite 20 from the second satellite 20, the inter-satellite separation spring 62 is pressed between the first inter-satellite docking structure 33 and the second inter-satellite docking structure 34, and the inter-satellite separation spring 62 provides power for separating the first satellite 20 from the second satellite 20 during inter-satellite separation.
In the present embodiment, the head of the explosion bolt 511 of the inter-satellite explosion bolt assembly 61 is engaged with the first inter-satellite docking structure 33, the nut 512 thereof is located inside the second inter-satellite docking structure 34, and the buffer 54 wrapped around the nut 512 is provided inside the first inter-satellite docking structure 33. The structure of the inter-satellite connection and separation mechanism 60 is the same as that of the satellite-rocket connection and separation mechanism 50, and the structure and the connection mode of the inter-satellite explosive bolt assembly 61 are the same as those of the explosive bolt 511 assembly, so that the details are not repeated herein; the inter-satellite separation spring 62 is mounted in the same manner as the satellite-rocket separation spring 52, and will not be described herein again.
As shown in fig. 2 and 3, a separation travel switch 70 is disposed between the carrying docking structure 31 and the satellite-satellite docking structure 32, a separation travel switch 70 is also disposed between the first inter-satellite docking structure 33 and the second inter-satellite docking structure 34, the separation travel switch 70 is a main switch of the satellite 20, and when the satellite-satellite is separated from the satellite, the separation travel switch 70 is used for generating a signal for separating the satellite from the satellite so as to complete the start-up of the satellite 20.
The separation travel switch 70 is a whole satellite switch of one satellite 20, when the satellite launches, the separation travel switch 70 is closed, the satellite 20 is in a power-off state, when the satellite and the rocket are separated, the separation travel switch 70 between the first satellite 20 and the rocket is activated along with the separation of the satellite 20 and the rocket, and the whole satellite of the first satellite 20 is started; when the two satellites are separated, the separation travel switch 70 between the first satellite 20 and the second satellite 20 is activated, and the second satellite 20 is started up.
The specific implementation process is as follows:
before satellite transmission: the carrying butt joint base 10, the first satellite 20 and the second satellite 20 are assembled according to the mode of figure 1 through the carrying butt joint structure 31, the satellite-rocket butt joint structure 32, the first inter-satellite butt joint structure 33 and the second inter-satellite butt joint structure 34, the anti-shearing boss 35 is used for positioning, then the satellite-rocket connecting and separating mechanism 50 and the inter-satellite connecting and separating mechanism 60 are installed, the space between the first satellite 20 and the carrying butt joint base 10 and the space between the first satellite 20 and the second satellite 20 are fastened through the explosion bolt 511, then the pre-tightening force of the satellite-rocket separating spring 52 and the inter-satellite separating spring 62 is adjusted, the stroke of the two separating stroke switches 70 is adjusted, and the preparation work before launching is completed.
Satellite on-orbit unlocking: the satellite and arrow separation movement is controlled by outer wall carrying, after a satellite and arrow separation instruction is sent, the four explosion bolts 511 between the carrying butt joint base 10 and the first satellite 20 are detonated simultaneously, the whole satellite is separated from the carrying butt joint structure 31 under the action of the satellite and arrow separation springs 52 between the satellite and the arrow, the separation travel switch 70 of the first satellite 20 is triggered, and the first satellite 20 is started. After the whole satellite keeps a safe distance with the carrying butt joint structure 31, the first satellite 20 sends a double-satellite separation signal, the four explosive bolts 511 between the first satellite 20 and the second satellite 20 are detonated simultaneously, the second satellite 20 is separated from the first satellite 20 under the action of the double-satellite inter-satellite separation spring 62, the separation travel switch 70 of the second satellite 20 is triggered, and the second satellite 20 completes starting, so that the double-satellite on-orbit unlocking is completed.
Example two
The structural principle of the present embodiment is substantially the same as that of the first embodiment, and the difference is that the present embodiment is a satellite platform configuration of one arrow and three stars, as shown in fig. 4, the present embodiment is extended to the satellite platform configuration of one arrow and three stars on the basis of the satellite platform configuration of one arrow and two stars of the first embodiment, specifically, a third satellite 20 may be added on the second satellite 20, four sets of the first inter-satellite docking structures 33, four sets of the second inter-satellite docking structures 34, and four sets of the inter-satellite connecting and separating mechanisms 60 are added, so that launching of one arrow and three stars may be achieved. The connection between the added third satellite 20 and the second satellite 20 is the same as the connection between the second satellite 20 and the first satellite 20, and the separation between the third satellite 20 and the second satellite 20 is the same as the separation between the second satellite 20 and the first satellite 20, which is not described herein again.
When the satellite and the rocket are separated, the three satellites 20 are integrated, the satellite is separated from the rocket as a whole, when the satellites are separated, the first satellite 20 is separated from the second satellite 20 and the third satellite 20 firstly (the second satellite 20 and the third satellite 20 are integrated), then the second satellite 20 is separated from the third satellite 20, and in-orbit unlocking of the three satellites 20 is completed for step-by-step separation.
It should be noted that, according to the requirement of the number of the actual launching satellites, launching satellites of an arrow with four stars or more can be set, which is the same as launching satellites of an arrow with two stars and an arrow with three stars, and is not described in detail here.
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 (10)
1. A high-adaptability stacked satellite platform structure with one arrow, two stars or multiple stars is characterized by comprising a carrying butt joint base and two or more than two satellites overlapped on the carrying butt joint base;
the carrying butt joint base is provided with a carrying butt joint structure, the satellite at the bottommost part is provided with a satellite and arrow butt joint structure matched with the carrying butt joint structure, and the carrying butt joint structure is connected with the satellite and arrow butt joint structure through a satellite and arrow connection and separation mechanism;
between two adjacent satellites, one satellite has a first inter-satellite docking structure, the other satellite has a second inter-satellite docking structure matched with the first inter-satellite docking structure, and the first inter-satellite docking structure is connected with the second inter-satellite docking structure through an inter-satellite connection and separation mechanism.
2. The high-adaptability stacked one-arrow two-star or multi-star satellite platform configuration is characterized in that the satellite-arrow connection and separation mechanism comprises a satellite-arrow explosion bolt assembly and a satellite-arrow separation spring, the satellite-arrow explosion bolt assembly connects the carrying butt joint structure and the satellite-arrow butt joint structure together, the satellite-arrow explosion bolt assembly explodes to separate the whole satellite from the rocket, the satellite-arrow separation spring is pressed between the carrying butt joint structure and the satellite-arrow butt joint structure, and the satellite-arrow separation spring provides power for satellite-arrow separation when the satellite and the arrow are separated;
the inter-satellite connection and separation mechanism comprises an inter-satellite explosion bolt assembly and an inter-satellite separation spring, the inter-satellite explosion bolt assembly is used for connecting the first inter-satellite butt joint structure and the second inter-satellite butt joint structure together, the inter-satellite explosion bolt assembly explodes to enable the satellites to be separated, the inter-satellite separation spring is arranged between the first inter-satellite butt joint structure and the second inter-satellite butt joint structure in a pressing mode, and during inter-satellite separation, the inter-satellite separation spring provides power for separation between the satellites.
3. A highly adaptable stacked one-rocket two-or multi-satellite platform configuration as claimed in claim 2, wherein said rocket explosive bolt assembly comprises paired explosive bolts and nuts, said carrying docking structure and rocket docking structure are connected by explosive bolts and fastened with nuts;
the structure of the inter-satellite explosive bolt assembly is the same as that of the satellite explosive bolt assembly.
4. The high-adaptability stacked one-rocket two-satellite or multi-satellite platform configuration is characterized in that the head of the explosion bolt of the satellite-rocket explosion bolt assembly is clamped in a satellite-rocket docking structure, the nut of the explosion bolt is positioned in a carrying docking structure, and a buffer piece wrapped outside the nut is arranged in the carrying docking structure;
the head of the explosion bolt of the inter-satellite explosion bolt assembly is clamped in a first inter-satellite butt joint structure, the nut of the explosion bolt assembly is located inside a second inter-satellite butt joint structure, and a buffer piece wrapped outside the nut is arranged inside the first inter-satellite butt joint structure.
5. A highly adaptable stacked one-rocket two-satellite or multi-satellite platform configuration as claimed in claim 2, wherein said carrying docking structure/first inter-satellite docking structure has a lower pressing plate, the satellite-rocket docking structure/second inter-satellite docking structure has an upper pressing plate disposed opposite to the lower pressing plate, the satellite-rocket separation spring/inter-satellite separation spring sleeve is pressed between the upper pressing plate and the lower pressing plate; the carrying butt joint structure/the first inter-satellite butt joint structure is fixedly connected with a guide rod, the upper portion of the guide rod penetrates through the lower pressing plate and extends upwards, the upper end of the guide rod is a free end, and the satellite-rocket separation spring/the inter-satellite separation spring is sleeved on the guide rod.
6. A highly adaptable stacked one-rocket two-satellite or multi-satellite platform configuration as claimed in any one of claims 2-5, wherein there are separation travel switches between said carrying docking structure and the satellite-rocket docking structure, and between the first inter-satellite docking structure and the second inter-satellite docking structure, and when the satellite-rocket/inter-satellite is separated, the separation travel switches are used for the signal generation of the satellite-rocket/inter-satellite separation to complete the start-up of the satellite.
7. A highly adaptable stacked one-rocket-two-satellite or multi-satellite platform configuration as claimed in any one of claims 1-5, wherein said carrying docking structure is a lower column provided on a carrying docking base, said satellite-rocket docking structure is an upper column provided on a bottommost satellite; between two adjacent satellites, first inter-satellite butt joint structure is the lower stand of establishing on the satellite of below, second inter-satellite butt joint structure is the last stand of establishing on the satellite of top.
8. The high adaptability stacked one-rocket-two-star or multi-star satellite platform configuration according to claim 7, wherein one of said paired lower and upper uprights is provided with anti-shear bosses which are in nesting fit with the other upright.
9. A highly adaptable stacked one-rocket-two-satellite or multi-satellite platform configuration according to any one of claims 1-5, wherein the number of said carrying and rocket docking structures is equal to the number of said first inter-satellite docking structures and said second inter-satellite docking structures and is arranged in a one-to-one correspondence.
10. A highly adaptable stacked one-rocket two-satellite or multi-satellite platform configuration as claimed in any one of claims 1-5, wherein the number of said carrying butt-joint structures and said satellite-rocket butt-joint structures is four, and four carrying butt-joint structures and four satellite-rocket butt-joint structures are distributed at four corners of the bottommost satellite in pairs;
the number of the first inter-satellite butt joint structures and the number of the second inter-satellite butt joint structures are four, and four first inter-satellite butt joint structures and four second inter-satellite butt joint structures are distributed on four corners between two adjacent satellites in pairs.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022889767.8U CN213677217U (en) | 2020-12-04 | 2020-12-04 | High-adaptability stacked satellite platform structure with one arrow and two or more satellites |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022889767.8U CN213677217U (en) | 2020-12-04 | 2020-12-04 | High-adaptability stacked satellite platform structure with one arrow and two or more satellites |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN213677217U true CN213677217U (en) | 2021-07-13 |
Family
ID=76738123
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202022889767.8U Active CN213677217U (en) | 2020-12-04 | 2020-12-04 | High-adaptability stacked satellite platform structure with one arrow and two or more satellites |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN213677217U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113581499A (en) * | 2021-08-06 | 2021-11-02 | 长光卫星技术有限公司 | Heap satellite linkage unblock separator |
| CN113955156A (en) * | 2021-11-26 | 2022-01-21 | 长光卫星技术有限公司 | Satellite and rocket connecting device of stacked satellite |
-
2020
- 2020-12-04 CN CN202022889767.8U patent/CN213677217U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113581499A (en) * | 2021-08-06 | 2021-11-02 | 长光卫星技术有限公司 | Heap satellite linkage unblock separator |
| CN113581499B (en) * | 2021-08-06 | 2023-02-17 | 长光卫星技术股份有限公司 | Heap satellite linkage unblock separator |
| CN113955156A (en) * | 2021-11-26 | 2022-01-21 | 长光卫星技术有限公司 | Satellite and rocket connecting device of stacked satellite |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN213677217U (en) | High-adaptability stacked satellite platform structure with one arrow and two or more satellites | |
| CN111954625B (en) | Satellite configuration and method of separation thereof | |
| CN104260903A (en) | Propelling module structure with independent high-rail satellite platform function | |
| US20220127022A1 (en) | Multiple space vehicle launch system | |
| CN102009746B (en) | Octagonal battery-equipped array upright post micro satellite configuration | |
| CN109050992B (en) | Docking type multi-module cooperative flexible taper rod type docking mechanism and working method thereof | |
| RU2451631C1 (en) | Method of accumulating spaceship power supply | |
| CN112373734B (en) | Low-orbit satellite group emission satellite-arrow separation unlocking module and satellite-arrow separation method | |
| CN110182388A (en) | Based on pre-integrated truss can in-orbit assembling spacecraft | |
| WO2010133684A1 (en) | Transportable electricity generation unit and method for generating electricity using said unit | |
| CN111703592B (en) | Large commercial remote sensing satellite platform configuration and assembly method | |
| CN109229422A (en) | A kind of deck board formula satellite configuration and its assembly method | |
| CN110104222A (en) | A kind of modularization propulsion service system promoted based on mixed mode | |
| CN100483292C (en) | Mini-sized low-load SMA space in-phase unlocking mechanism | |
| CN206691377U (en) | A kind of in-orbit assembly system of space truss using robot for space | |
| CN112298618A (en) | Two-dimensional secondary expansion solar wing | |
| CN111891404A (en) | Layout method and system for electrified dual-mode thruster of high-orbit maneuvering satellite platform | |
| CN106363667A (en) | Fixing and releasing device of space manipulator | |
| CN107128514A (en) | The in-orbit assembly system of space truss and method of a kind of use robot for space | |
| CN102358438A (en) | Increased resistance type device applicable to low-orbit post-task spacecraft deorbit | |
| CN105217057A (en) | A kind of based on rope system docking star between energy transform device | |
| CN112777001B (en) | Micro-nano satellite accompanied with orbit entering | |
| CN206394910U (en) | A kind of manned Mars mission based on MW class nuclear reactor power supply | |
| CN109510028B (en) | Automatic separation system and method for electric connector | |
| RU2310768C2 (en) | Impulse-action rocket solar oxygen-hydrogen propulsion plant |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address |
Address after: 401123 39-1, Building 1, No. 64, Middle Huangshan Avenue, Yubei District, Chongqing Patentee after: China Star Network Application Co.,Ltd. Address before: 618 Liangjiang Avenue, Longxing Town, Yubei District, Chongqing Patentee before: Dongfanghong Satellite Mobile Communication Co.,Ltd. |
|
| CP03 | Change of name, title or address |