CN114963892A - Connecting and unlocking device suitable for multi-satellite separation - Google Patents
Connecting and unlocking device suitable for multi-satellite separation Download PDFInfo
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- CN114963892A CN114963892A CN202110195551.8A CN202110195551A CN114963892A CN 114963892 A CN114963892 A CN 114963892A CN 202110195551 A CN202110195551 A CN 202110195551A CN 114963892 A CN114963892 A CN 114963892A
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- 238000000926 separation method Methods 0.000 title claims abstract description 57
- 239000000835 fiber Substances 0.000 claims abstract description 72
- 230000000149 penetrating effect Effects 0.000 claims abstract description 6
- 230000006835 compression Effects 0.000 claims description 8
- 238000007906 compression Methods 0.000 claims description 8
- 230000003139 buffering effect Effects 0.000 claims description 7
- 229920006231 aramid fiber Polymers 0.000 claims description 4
- 230000000452 restraining effect Effects 0.000 claims 1
- 230000005540 biological transmission Effects 0.000 abstract description 8
- 238000010586 diagram Methods 0.000 description 3
- 230000001360 synchronised effect Effects 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
- F42B15/36—Means for interconnecting rocket-motor and body section; Multi-stage connectors; Disconnecting means
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Aviation & Aerospace Engineering (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Ropes Or Cables (AREA)
Abstract
The application belongs to the technical field of satellite-rocket connection and separation, and discloses a connection unlocking device suitable for multi-satellite separation, which comprises a base and a locking mechanism, wherein the base is fixed on a rocket; the fiber rope is provided with a first end and a second end, the first end is fixed on the base, and the second end can be sequentially arranged in the stacked satellites in a penetrating mode; the pressing component is connected to the second end of the fiber rope to press and fix the stacked satellites on the base; a plurality of stacked satellites can be unlocked when the fiber rope is cut. The satellite is penetrated through the fiber rope, the two ends of the fiber rope are respectively connected with the top pressing device and the base, a plurality of stacked satellites can be fixedly connected in series, the occupied space is small, and more satellites can be fixed in the limited fairing space; decide the fiber rope during the transmission, realize the batch transmission of a plurality of heap satellites, improve rocket carrying efficiency and satellite emission efficiency.
Description
Technical Field
The application relates to the technical field of satellite and rocket connection and separation, in particular to a connection unlocking device suitable for multi-satellite separation.
Background
In recent years, as satellite internet is brought into the new infrastructure of the country, low-orbit internet satellite constellations will be deployed rapidly in the coming years. The rapid establishment of the satellite constellation network requires that the satellite gradually develops towards integration, flattening and low cost, and the traditional trapezoidal satellite structure and the rectangular structure limit the development of satellite batch launching under the condition of limited rocket fairing space.
In the traditional one-rocket multi-satellite launching process, the separation technology mainly faces to the satellite and rocket separation process, and each satellite is sequentially separated from the adapter in the fairing. With the gradual increase of rocket carrying capacity, the inner space of the fairing is gradually increased, but the number of satellites capable of being accommodated by the distributor is limited, and the space utilization rate is low. With the appearance of the 'flat-plate' and 'stackable' satellites, the space utilization rate of the fairing can be fully improved, and the connecting and unlocking device for separating the satellites and the arrows in the prior art has great limitation on batch launching of the stacked satellites, occupies larger rocket carrying space, and influences the rocket carrying efficiency or the satellite launching efficiency.
Disclosure of Invention
The application aims to provide a connecting and unlocking device suitable for separating multiple satellites, so that the problem that satellites are stacked in batch launching is solved, and rocket carrying efficiency and satellite launching efficiency are improved.
To achieve the purpose, the following technical scheme is adopted in the application:
a connection unlocking device suitable for multi-satellite separation comprises:
the base is fixed on the rocket;
the fiber rope is provided with a first end and a second end, the first end is fixed on the base, and the second end can be sequentially arranged in a plurality of stacked satellites in a penetrating mode;
a hold-down element connected to a second end of the fiber rope to hold down the plurality of stacked satellites on the base; a plurality of the stacked satellites can be unlocked when the fiber rope is cut.
Optionally, the fiber rope is an aramid fiber rope.
Optionally, a thermal cutter is disposed within the base, the thermal cutter configured to sever the fiber rope.
Optionally, the number of the thermal cutters is two, and the two thermal cutters are arranged at intervals in the length direction of the fiber rope.
Optionally, a plurality of bearing rings are arranged on the stacked satellite, the plurality of bearing rings are distributed at intervals in the circumferential direction of the stacked satellite, and the fiber rope is inserted into the bearing rings.
Optionally, a plurality of the connection and unlocking devices suitable for multi-satellite separation are circumferentially arranged on the stacked satellite, and the connection and unlocking devices suitable for multi-satellite separation are respectively arranged corresponding to the positions of the bearing rings.
Optionally, a buffer assembly is further disposed in the base, the buffer assembly includes a buffer spring, a limiting member and a fixed end cover, the limiting member is fixedly connected to the base, the first end of the fiber rope is fixedly connected to the fixed end cover, when the fiber rope is in a connection state, the fixed end cover is abutted to the limiting member, and the buffer spring is compressed between the fixed end cover and the limiting member.
Optionally, the buffer assembly further comprises a limiting chuck fixedly connected to the base, and the thermal cutter is connected to the limiting chuck.
Optionally, the pressing assembly includes a pressing ring, a separation spring, and a limiting post, the limiting post and the pressing ring are slidably connected, the second end of the fiber rope is fixedly connected to one end of the limiting post away from the stacked satellites, two ends of the separation spring are respectively connected to one end of the limiting post facing the stacked satellites and the pressing ring, when the fiber rope is in a connected state, the pressing ring abuts against the surfaces of a plurality of the stacked satellites, and the limiting post can slide towards the stacked satellites and stretch the separation spring to tension the fiber rope.
Optionally, the compressing assembly further comprises a compressing member, the compressing member is fixedly connected with the compressing ring, and the limit column is slidably connected with the compressing member.
According to the connecting and unlocking device suitable for multi-satellite separation, the fiber rope penetrates through the satellites, the two ends of the fiber rope are respectively connected with the pressing component and the base, a plurality of stacked satellites can be connected on the fiber rope in series to be pressed and fixed together, the occupied space position is small, and more satellites can be fixed in the limited fairing space; the fiber ropes are cut during launching, batch launching of a plurality of stacked satellites is achieved, satellite-rocket separation and inter-satellite separation are completed, and rocket carrying efficiency and satellite launching efficiency are improved.
Drawings
Fig. 1 is a schematic overall structural diagram of a connection unlocking device suitable for multi-star separation according to an embodiment of the present application;
fig. 2 is a schematic diagram illustrating a positional relationship between a connection unlocking device and a satellite suitable for multi-satellite separation according to an embodiment of the present application;
FIG. 3 is a schematic structural diagram of a pressing assembly in a connection unlocking device suitable for multi-star separation according to an embodiment of the present application;
fig. 4 is a schematic cross-sectional view of a base of a connection unlocking device suitable for multi-star separation according to an embodiment of the present disclosure.
In the figure:
100. a stacked satellite; 200. a force bearing ring; 300. a rocket;
1. a base; 2. a fiber rope; 3. a compression assembly; 31. a compression ring; 32. a separation spring; 33. a limiting column; 34. a compression member; 4. a thermal cutter; 5. a compression spring; 6. a stopper; 7. fixing the end cover; 8. and a limiting chuck.
Detailed Description
The present application will be described in further detail with reference to the following drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the application and are not limiting of the application. It should be further noted that, for the convenience of description, only some of the structures related to the present application are shown in the drawings, not all of the structures.
In the description of the present application, unless expressly stated or limited otherwise, the terms "connected," "connected," and "fixed" are to be construed broadly, e.g., as meaning permanently connected, removably connected, or integral to one another; can be mechanically or electrically connected; they may be directly connected or indirectly connected through intervening media, or may be connected through the use of two elements or the interaction of two elements. The specific meaning of the above terms in the present application can be understood in a specific case by those of ordinary skill in the art.
In this application, unless expressly stated or limited otherwise, the first feature "on" or "under" the second feature may comprise direct contact of the first and second features, or may comprise contact of the first and second features not directly but through another feature in between. Also, the first feature being "on," "above" and "over" the second feature includes the first feature being directly on and obliquely above the second feature, or merely indicating that the first feature is at a higher level than the second feature. "beneath," "under" and "beneath" a first feature includes the first feature being directly beneath and obliquely beneath the second feature, or simply indicating that the first feature is at a lesser elevation than the second feature.
In the description of the present embodiment, the terms "upper", "lower", "right", etc. are used in an orientation or positional relationship based on that shown in the drawings only for convenience of description and simplicity of operation, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus should not be construed as limiting the present application. Furthermore, the terms "first" and "second" are used only for descriptive purposes and are not intended to have a special meaning.
The application provides a connect unlocking device suitable for separation of many stars solves the problem that the satellite was piled up in the transmission in batches, improves rocket delivery efficiency and satellite emission efficiency.
As shown in fig. 1 and 2, the connecting and unlocking device suitable for multi-satellite separation of the embodiment includes a base 1, a fiber rope 2 and a pressing assembly 3, wherein the base 1 is fixed on a rocket 300; the fiber rope 2 is provided with a first end and a second end, the first end is fixed on the base 1, and the second end can be sequentially arranged in the stacked satellites 100 in a penetrating way; the pressing component 3 is connected to the second end of the fiber rope 2 to press and fix a plurality of stacked satellites 100 on the base 1; the plurality of stacked satellites 100 can be unlocked when the fiber ropes 2 are cut to complete the separation of the satellites and the arrows.
The connection unlocking device suitable for separation of many stars of this embodiment, when using, at first be fixed in the last stage of rocket 300 with base 1, then be fixed in base 1 with the first end of fibre rope 2 on, the second end wears to establish a plurality of heap satellites 100 in proper order, and be fixed in on compressing tightly subassembly 2 with the second end of fibre rope 2, make the both ends of heap satellite 100 stop respectively in base 1 and compressing tightly subassembly 3, the realization is fixed with a plurality of heap satellites 100, the both ends of fibre rope 2 are connected respectively and are compressed tightly subassembly 3 and base 1, can concatenate a plurality of heap satellites 100 fixedly, the occupation space position is little, can be at the fixed more heap satellite 100 of radome space internal fixation of limited rocket 300. Only need decide the cordage 2 during satellite transmission, a plurality of heap satellites 100 unblock constraint simultaneously, and the transmission in batches improves rocket carrying efficiency and satellite transmission efficiency.
Optionally, the fiber rope 2 is an aramid fiber rope, and the aramid fiber has excellent properties such as high strength, high modulus, high temperature resistance, corrosion resistance, low density, and easy processing and forming, and can ensure the compression strength of the stacked satellite, and the stacked satellite 100 can be compressed and fixed under the tension thereof. When the fiber rope is released or launched, the fiber rope 2 is easy to fuse or cut, and separation between stars and arrows is achieved.
Optionally, a thermal cutter 4 is provided within the base 1, the thermal cutter 4 being configured to sever the fiber rope 2. Adopt hot cutterbar 4, the circular telegram heats in the twinkling of an eye and can fuses the fiber rope 2, guarantees that a plurality of fiber ropes 2 who connect unlocking device decide or fuse in step, guarantees the synchronous release or the transmission of a plurality of heap satellites 100.
Alternatively, two thermal cutters 4 are provided, and the two thermal cutters 4 are arranged at intervals in the length direction of the fiber rope 3.
As shown in fig. 4, the thermal cutters 4 are disposed inside the base 1, two thermal cutters 4 are disposed at intervals on both sides of the fiber rope 2, and the cutters of the two thermal cutters 4 are disposed at intervals in the longitudinal direction of the fiber rope 2, respectively, so that when the fiber rope 2 needs to be cut, the two thermal cutters 4 are simultaneously energized in synchronization to ensure timely cutting of the fiber rope 2.
Optionally, a bearing ring 200 is arranged on the stacked satellite 100, the bearing ring 200 is provided in plurality, the bearing rings 200 are distributed at intervals in the circumferential direction of the stacked satellite 100, and the fiber rope 2 is inserted into the bearing rings 200. As shown in fig. 2, at least three bearing rings 200 are provided in the circumferential direction of the stacked satellite 100, and the bearing rings 200 of a plurality of stacked satellites 100 that need to be fixed and launched at the same time are arranged at the same position, so as to ensure that in the stacked state of a plurality of stacked satellites 100, the bearing rings 200 correspond to each other in position, the fiber ropes 2 can be inserted into the bearing rings 200 of a plurality of stacked satellites 100 corresponding to each other in position, each bearing ring 200 is inserted with at least one fiber rope 2, and the number of bearing rings 200 of each stacked satellite 100 is equal to the number of fiber ropes 2, that is, the number of connecting and unlocking devices suitable for multi-satellite separation provided in this embodiment.
It can be understood that the stackable satellite 100 is provided with a plurality of connecting and unlocking devices suitable for multi-satellite separation in the circumferential direction, and the plurality of connecting and unlocking devices suitable for multi-satellite separation are respectively arranged corresponding to the positions of the plurality of bearing rings 200. A plurality of heap satellites 100 are connected fixedly through a plurality of connection unlocking device that are applicable to the separation of many stars, realize star and arrow separation and transmission, need guarantee that every be applicable to the synchronous of the fibre rope 2 in the connection unlocking device of the separation of many stars decides simultaneously, therefore every fibre rope 2 sets up two hot cutterbars 4 and can guarantee above synchronization.
Optionally, a buffering assembly is further arranged in the base 1, the buffering assembly includes a buffering spring 5, a limiting member 6 and a fixed end cover 7, the limiting member 6 is fixedly connected with the base 1, the first end of the fiber rope 2 is fixedly connected with the fixed end cover 7, when the fiber rope 2 is in a connection state, the fixed end cover 7 abuts against the limiting member 6, and the buffering spring 5 is compressed between the fixed end cover 7 and the limiting member 6.
As shown in fig. 4, the limiting part 6 is fixedly connected with the base 1, a groove is formed in the limiting part 6, one end of the buffer spring 5 is limited in the groove, the other end of the buffer spring can abut against the fixed end cover 7, and when the fiber rope 2 is connected with the fixed end cover 7 and tensioned, the fixed end cover 7 can be driven to move towards the limiting part 6 and compress the buffer spring 5, so that a tensioning force is provided for the fiber rope 2, and meanwhile, impact force of separation of stars and arrows and separation between stars can be reduced.
Optionally, the buffer assembly further comprises a limiting chuck 8, the limiting chuck 8 is fixedly connected to the base 1, and the thermal cutter 4 is connected to the limiting chuck 8. It should be explained that the base 1 in this embodiment is a shell structure, and the limiting chuck 8 is disposed in the base 1 to facilitate the fixed connection between the thermal cutter 4 and the limiting member 6, and to make full use of the internal space of the base 1.
Optionally, the pressing assembly 3 includes a pressing ring 31, a separation spring 32 and a limit post 33, the limit post 33 is slidably connected to the pressing ring 31, the second end of the fiber rope 2 is fixedly connected to one end of the limit post 33 away from the stacked satellites 100, two ends of the separation spring 32 are respectively connected to one end of the limit post 33 facing the stacked satellites 100 and the pressing ring 31, when the fiber rope 2 is in a connected state, the pressing ring 31 abuts against the surfaces of the stacked satellites 100, and the limit post 33 can slide towards the stacked satellites 100 and stretch the separation spring 32 to tension the fiber rope 2.
As shown in fig. 3, the pressing ring 31 is cylindrical, the separation spring 32 and the spacing post 33 are disposed inside the pressing ring 31, the bottom end of the pressing ring 31 can be stopped against the surface of the stacked satellite 100 below under the pulling force of the fiber rope 2, meanwhile, the separation spring 32 can be sleeved on the spacing post 33 and fixed at one end for spacing, and when the fiber rope 2 is in a connected state, the spacing post 33 stretches the separation spring 32 and then fixed at the top of the pressing ring 31. After the fiber rope 2 is cut off, the clamp ring 31 and the fiber rope 2 are ejected out together with the stacked satellite 100 by the elastic force of the separation spring 32 and the pretightening force of the fiber rope 2, and the unlocking and separation are completed.
Optionally, the pressing assembly 3 further includes a pressing member 34, the pressing member 34 is fixedly connected with the pressing ring 31, and the limiting column 33 is slidably connected to the pressing member 34.
As shown in fig. 3, a pressing member 34 is disposed inside the pressing ring 31 near the top end, the pressing member 34 is fixedly connected to the pressing ring 31, a through hole is disposed inside the pressing member 34, the limiting column 33 is disposed in the through hole in a penetrating manner, the top of the limiting column 33 is connected to the fiber rope 2, and the bottom of the limiting column 33 is sleeved with the separation spring 32.
In conclusion, the connection unlocking device suitable for multi-satellite separation is simple in structural design and easy to operate. The buffering spring 5 arranged in the base 1 can play a role in buffering, the impact force borne by the stacked satellite 100 is reduced, the separating spring 32 arranged in the pressing component 3 can provide pretightening force before unlocking and separating, and elastic force is provided after unlocking, so that the stacked satellite 100 can be conveniently unlocked and separated.
It should be understood that the above examples are merely examples for clearly illustrating the present application, and are not intended to limit the embodiments of the present application. Numerous obvious variations, adaptations and substitutions will occur to those skilled in the art without departing from the scope of the present application. And are neither required nor exhaustive of all embodiments. Any modification, equivalent replacement, and improvement made within the spirit and principle of the present application shall be included in the protection scope of the claims of the present application.
Claims (10)
1. A connection unlocking device suitable for multi-star separation is characterized by comprising:
the base (1), the said base (1) is fixed on rocket (300);
the fiber rope (2) is provided with a first end and a second end, the first end is fixed on the base (1), and the second end can be sequentially arranged in a plurality of stacked satellites (100) in a penetrating mode;
a pressing member (3), the pressing member (3) being connected to a second end of the fiber rope (2) to press and fix the plurality of stacked satellites (100) on the base (1); a plurality of the stacked satellites (100) can be unlocked when the fiber rope (2) is cut.
2. The connection unlocking device suitable for multi-star separation according to claim 1, wherein the fiber rope (2) is an aramid fiber rope.
3. The connection release device for multi-star disconnection according to claim 1, characterized in that a thermal cutter (4) is arranged in the base (1), the thermal cutter (4) being configured to cut the fiber rope (2).
4. The connection unlocking device suitable for multi-star separation according to claim 3, wherein the number of the thermal cutters (4) is two, and the two thermal cutters (4) are arranged at intervals in the length direction of the fiber rope (2).
5. The connecting and unlocking device for separating multiple satellites according to claim 1 is characterized in that a bearing ring (200) is arranged on the stacked satellite (100), the bearing ring (200) is provided in plurality, the bearing rings (200) are distributed at intervals in the circumferential direction of the stacked satellite (100), and the fiber rope (2) is arranged in the bearing rings (200) in a penetrating manner.
6. The device for unlocking a multi-star connection suitable for separation according to claim 5, wherein a plurality of the devices for unlocking a multi-star connection suitable for separation are provided in a circumferential direction of the stacked satellite (100), and are respectively provided corresponding to positions of the force bearing rings (200).
7. The connection unlocking device suitable for multi-star separation according to claim 3, wherein a buffer assembly is further disposed in the base (1), the buffer assembly includes a buffer spring (5), a limiting member (6) and a fixed end cap (7), the limiting member (6) is fixedly connected with the base (1), the first end of the fiber rope (2) is fixedly connected with the fixed end cap (7), when the fiber rope (2) is in a connection state, the fixed end cap (7) abuts against the limiting member (6), and the buffer spring (5) is compressed between the fixed end cap (7) and the limiting member (6).
8. The connection unlocking device for multi-star separation according to claim 7, wherein the buffering assembly further comprises a limit chuck (8), the limit chuck (8) is fixedly connected to the base (1), and the hot cutter (4) is connected to the limit chuck (8).
9. The connection unlocking device for multi-star separation according to claim 1, the pressing component (3) comprises a pressing ring (31), a separation spring (32) and a limiting column (33), the limit column (33) is connected with the compression ring (31) in a sliding way, the second end of the fiber rope (2) is fixedly connected with one end of the limit column (33) far away from the stacked satellite (100), two ends of the separation spring (32) are respectively connected with one end of the limit column (33) facing the stacked satellite (100) and the compression ring (31), when the fiber rope (2) is in a connected state, the compression ring (31) is stopped against the surfaces of a plurality of stacked satellites (100), the restraining post (33) is slidable in the direction of the stacked satellite (100) and stretches the separation spring (32) to tension the fiber rope (2).
10. The connection unlocking device for multi-star separation according to claim 9, wherein the pressing assembly (3) further comprises a pressing member (34), the pressing member (34) is fixedly connected with the pressing ring (31), and the limiting column (33) is slidably connected with the pressing member (34).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110195551.8A CN114963892A (en) | 2021-02-19 | 2021-02-19 | Connecting and unlocking device suitable for multi-satellite separation |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110195551.8A CN114963892A (en) | 2021-02-19 | 2021-02-19 | Connecting and unlocking device suitable for multi-satellite separation |
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| Publication Number | Publication Date |
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| CN114963892A true CN114963892A (en) | 2022-08-30 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202110195551.8A Withdrawn CN114963892A (en) | 2021-02-19 | 2021-02-19 | Connecting and unlocking device suitable for multi-satellite separation |
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| US20200130073A1 (en) * | 2017-06-22 | 2020-04-30 | Rheinmetall Waffe Munition Gmbh | Cutting device |
| CN111086658A (en) * | 2019-12-31 | 2020-05-01 | 东方红卫星移动通信有限公司 | Connection and separation device for satellite group transmission |
| CN111453003A (en) * | 2020-05-18 | 2020-07-28 | 苏州馥昶空间技术有限公司 | Compressing and releasing mechanism |
| CN214792812U (en) * | 2021-02-19 | 2021-11-19 | 北京九天微星科技发展有限公司 | Connecting and unlocking device suitable for multi-satellite separation |
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2021
- 2021-02-19 CN CN202110195551.8A patent/CN114963892A/en not_active Withdrawn
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104859870A (en) * | 2014-10-09 | 2015-08-26 | 航天东方红卫星有限公司 | Integrally-designed satellite-rocket separation mechanism |
| CN107889482A (en) * | 2015-04-30 | 2018-04-06 | 沃尔德伍卫星有限公司 | Stackable satellite and its stacking method |
| CN105292523A (en) * | 2015-10-27 | 2016-02-03 | 浙江大学 | Separating device and satellite and rocket separating device with buffering structure |
| US20200130073A1 (en) * | 2017-06-22 | 2020-04-30 | Rheinmetall Waffe Munition Gmbh | Cutting device |
| US20200017243A1 (en) * | 2018-07-16 | 2020-01-16 | Planetary Systems Corporation | System and method to attach and remove space vehicles |
| CN109733646A (en) * | 2018-12-29 | 2019-05-10 | 深圳航天东方红海特卫星有限公司 | A kind of elastic compensation drawstring retaining mechanism |
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Application publication date: 20220830 |
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