CN114735246A - Satellite launching box ejection device - Google Patents
Satellite launching box ejection device Download PDFInfo
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- CN114735246A CN114735246A CN202210426806.1A CN202210426806A CN114735246A CN 114735246 A CN114735246 A CN 114735246A CN 202210426806 A CN202210426806 A CN 202210426806A CN 114735246 A CN114735246 A CN 114735246A
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- fixing plate
- ejection device
- satellite
- link
- bushing
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
- B64G1/645—Separators
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Abstract
Disclosed is a satellite launch box ejection device (100) comprising: a lower fixing plate (101); an upper fixing plate (102); a central shaft (201); a first bushing (202); a second bushing (203); a first linkage and a second linkage, a first end of each of the first link (106) and the second link (107) is pivotally connected to the first bushing (202) and the second bushing (203), respectively, and a second end of each of the first link (106) and the second link (107) is pivotally connected; a pull ring (103); a tension spring group, wherein a first end of each tension spring (108) is connected to the pull ring (103), and a second end of each tension spring is connected to the second ends of the first connecting rod (106) and the second connecting rod (107); and the locking and releasing mechanism is used for switching the device (100) from a locking state to a releasing state, so that under the restoring action of the tension spring set in a stretching state, the first connecting rod set and the second connecting rod set are mutually expanded, and the second shaft sleeve (203) drives the upper fixing plate (102) to be bounced open to catapult and release the satellite.
Description
Technical Field
The invention relates to the technical field of spaceflight, in particular to a satellite launching box ejection device.
Background
With the rapid development of aerospace technology, the satellite transmitting frequency in China is higher and higher, and the satellite transmitting quantity is increased continuously. The ejection device of the satellite launching box is an indispensable device link for satellite launching, the satellite needs to be separated from the satellite and the rocket after being launched into the space by the rocket, and the ejection device is a driving device for completing the separation of the satellite and the rocket so that the satellite is ejected into the space from the launching box. Therefore, the design of the ejection device must strictly control the weight of the mechanism and ensure that the system has the characteristics of high reliability, high performance, high operability and the like.
At present, most of mechanisms for realizing the satellite ejection function realize the ejection of the satellite from the launching box by the recovery of a compressed compression spring. Although the device has a simpler structure and lighter weight, the ejection stroke, the elastic force and the elastic force uniformity are limited due to the characteristics of the spring, and the device is particularly not suitable for large-size satellites.
Disclosure of Invention
To this end, according to an embodiment of the present invention, there is provided a satellite launch box ejection device 100, including:
a lower fixing plate 101;
an upper fixing plate 102 on which a satellite is placed;
a center shaft 201 passing through or located at the center of the lower and upper fixing plates 101 and 102;
a first hub 202 mounted on the central shaft 201;
a second bushing 203 mounted on the central shaft 201, wherein the first bushing 202 and the second bushing 203 are located between the lower fixing plate 101 and the upper fixing plate 102, and the first bushing 202 and the second bushing 203 can slide relatively along the central shaft 201;
a first link group including a first number of a plurality of first links 106 circumferentially arranged along the central shaft 201, a first end of each first link 106 being pivotally connected to the first bushing 202;
a second linkage comprising a first number of a plurality of second links 107 arranged circumferentially along the central axis 201, a first end of each second link 107 pivotally connected to the second hub 203, wherein a second end of each first link 106 is pivotally connected to a second end of a respective second link 107;
a pull ring 103 mounted directly or indirectly on the center shaft 201 and located between the first sleeve 202 and the second sleeve 203;
a tension spring set including a second number of tension springs 108 circumferentially arranged along the central shaft 201, the second number being equal to the first number or twice the first number, each tension spring 108 having a first end connected to the pull ring 103 and a second end connected to the second end of the corresponding first and second links 106, 107; and
and a locking and releasing mechanism for switching the satellite shooting box ejection device 100 from a locking state to a releasing state, wherein in the locking state, the first shaft sleeve 202 and the second shaft sleeve 203 are close to each other, the first linkage and the second linkage are folded with each other, and the tension spring assembly is in a stretching state, so that under the restoring action of the tension spring assembly, the first linkage and the second linkage are opened with each other, the first shaft sleeve 202 and the second shaft sleeve 203 are far away from each other, and the upper fixing plate 102 is driven to be ejected and opened relative to the lower fixing plate 101, so that the satellite is ejected and released.
The satellite launch box ejection device 100 according to the embodiment of the invention realizes the ejection function through the combination of the link mechanism and the extension spring, the ejection mechanism can be freely opened and folded, the gentle ejection can be realized, no impact is generated, the structure is simple, the reliability is high, the size is small, the weight is light, and the cost is low. Compared with the technical scheme that the satellite is ejected from the launching box by means of the recovery action of the compressed compression spring in the prior art, the ejection stroke and the ejection force are greatly improved, the ejection stroke and the ejection force can be adjusted according to needs, and in some embodiments, ejection with a larger stroke can be realized by superposition of a multi-level link mechanism.
Drawings
Fig. 1 shows a schematic perspective view of a satellite launch box ejection device according to an embodiment of the invention.
Fig. 2 shows another schematic perspective view of a satellite launch box ejection device according to an embodiment of the invention.
Fig. 3 shows yet another schematic perspective view of a satellite launch box ejection device according to an embodiment of the invention.
Fig. 4 shows a partially exploded perspective view of a satellite launch box ejection device according to an embodiment of the invention.
Fig. 5 shows another partially exploded perspective view of a satellite launch box ejection device according to an embodiment of the invention.
Fig. 6 shows a view of a bottom plate of a satellite launch box ejector and several cross-sectional views according to embodiments of the invention.
Detailed Description
Embodiments of the present invention are described in detail below with reference to the accompanying drawings. In the following description, numerous specific details are set forth in order to provide a more thorough understanding of the present invention to those of ordinary skill in the art. It will be apparent, however, to one skilled in the art, that the present invention may be practiced without some of these specific details. Furthermore, it should be understood that the invention is not limited to the specific embodiments described. Rather, it is contemplated that the invention may be practiced with any combination of the following features and elements, whether or not they relate to different embodiments. Thus, the following aspects, features, embodiments and advantages are merely illustrative and should not be considered elements or limitations of the claims except where explicitly recited in a claim.
The meaning of each term referred to in this specification is generally a meaning commonly understood in the art or a meaning normally understood by those skilled in the art after reading this specification. The terms "comprising" and "including" in this specification are open-ended, i.e., may include additional elements not mentioned in addition to the elements mentioned. The terms "connected," "coupled," and the like in this specification generally include mechanical connections, electrical connections, communication connections, or combinations thereof, and may generally include both direct connections and indirect connections or connections via other components. The terms "first", "second", and the like in this specification are used only for distinguishing between similar different components and do not denote any order in importance, structure, function, or the like.
Referring now to fig. 1-6, wherein fig. 1 shows a schematic perspective view of a satellite launch box ejection device 100 according to an embodiment of the present invention; fig. 2 shows another schematic perspective view of a satellite launch box ejection device 100 in accordance with an embodiment of the invention, with the electromagnet and the central shaft housing removed from the lower base plate; fig. 3 illustrates yet another schematic perspective view of a satellite launch box ejection device 100 according to an embodiment of the present invention, which more clearly illustrates the upper floor; fig. 4 illustrates a partially exploded perspective view of a satellite launch box ejection device 100 showing the internal structure and upper floor of the satellite launch box ejection device, in accordance with an embodiment of the present invention; fig. 5 illustrates another partially exploded perspective view of a satellite launch box ejection device 100 according to an embodiment of the present invention, showing the internal structure and lower plate of the satellite launch box ejection device 100; fig. 6 shows a view of a bottom-facing plate of a satellite launch box ejection device 100, and several cross-sectional views, in accordance with an embodiment of the present invention.
As shown in fig. 1 to 6, a satellite shooting box ejection device 100 according to an embodiment of the present invention includes:
a lower fixing plate 101;
an upper fixing plate 102 on which a satellite is placed;
a center shaft 201 passing through or located at the center of the lower and upper fixing plates 101 and 102;
a first hub 202 mounted on the central shaft 201;
a second bushing 203 mounted on the central shaft 201, wherein the first bushing 202 and the second bushing 203 are located between the lower fixing plate 101 and the upper fixing plate 102, and the first bushing 202 and the second bushing 203 can slide relatively along the central shaft 201;
a first link group including a first number of a plurality of first links 106 circumferentially arranged along the central shaft 201, a first end of each first link 106 being pivotally connected to the first bushing 202;
a second linkage comprising a first plurality of second links 107 circumferentially arranged about the central axis 201, a first end of each second link 107 pivotally connected to the second hub 203, wherein a second end of each first link 106 is pivotally connected to a second end of a respective second link 107;
a pull ring 103 mounted directly or indirectly on the center shaft 201 and located between the first sleeve 202 and the second sleeve 203;
a tension spring set including a second number of tension springs (i.e., extension springs) 108 circumferentially arranged along the central shaft 201, the second number being equal to or twice the first number, each tension spring 108 having a first end connected to the pull ring 103 and a second end connected to a second end of the respective first and second links 106 and 107; and
and a locking and releasing mechanism for switching the satellite launching box ejection device 100 from a locking state to a releasing state, wherein in the locking state, the first shaft sleeve 202 and the second shaft sleeve 203 are close to each other, the first link set and the second link set are folded with each other, and the tension spring set is in a stretching state, so that under the restoring action of the tension spring set, the first link set and the second link set are opened with each other, the first shaft sleeve 202 and the second shaft sleeve 203 are far away from each other, and the upper fixing plate 101 is driven to be ejected relative to the lower fixing plate 102, so that the satellite ejection is released.
In some embodiments, as shown in fig. 4-6, the first bushing 202 is fixedly connected to the lower fixing plate 101, the second bushing 203 is fixedly connected to the upper fixing plate 102 and the central shaft 201, and the central shaft 201 can slide in the first bushing 202. For example, the first bushing 202 may be fixedly connected to the lower fixing plate 101 by means of bolts or the like; the second shaft sleeve 203 may be fixedly connected to the upper fixing plate 102 by means of bolts, and may be fixedly connected to the central shaft 201 by means of interference fit, pin connection, key connection, or the like.
In other embodiments, the first bushing 202 is fixedly connected to the lower fixing plate 101 and the central shaft 201, the second bushing 203 is fixedly connected to the upper fixing plate 102, and the central shaft 201 can slide in the second bushing 203. For example, the first shaft sleeve 202 may be fixedly connected to the lower fixing plate 101 by means of bolts, and may be fixedly connected to the central shaft 201 by means of interference fit, pin connection, key connection, and the like; the second shaft sleeve 203 may be fixedly connected to the upper fixing plate 102 by means of bolts or the like.
In some embodiments, as shown in fig. 4-6, the first end of each first link 106 is pivotally connected to the first bushing 202 via a first pin 104 disposed on the first bushing 202; a second end of each first link 106 is pivotally connected to a second end of a corresponding second link 107 by a second pin 105; a first end of each second link 107 is pivotally connected to the second bushing 203 by a third pin 109 provided on the second bushing 203.
In some embodiments, as shown in fig. 4-6, each pair of the first link 106 and the corresponding second link 107, the second ends of which are pivotally connected by the second pin 105, are provided with a pair of tension springs 108 on both sides thereof, and the second ends of the pair of tension springs 108 are respectively connected to both ends of the second pin 105, and the first ends of the pair of tension springs 108 are respectively connected to the pull ring 103.
In some embodiments, as shown in fig. 6, the pull ring 103 fits over a portion of the second bushing 203. In other embodiments, the pull ring 103 may be sleeved on a portion of the first sleeve 202 or directly on the central shaft 201.
In some embodiments, as shown in fig. 4-6, the first number of the first plurality of first links 106 of the first linkage and the first number of the second plurality of second links 107 of the second linkage are arranged evenly along a circumference of the central shaft 201.
In some embodiments, as shown in fig. 4-6, the first number is 4. That is, the first link group includes 4 first links 106 arranged circumferentially along the center shaft 201, and the second link group includes 4 second links 107 arranged circumferentially along the center shaft 201. Correspondingly, the tension spring set comprises 8 tension springs 108 arranged circumferentially along the central shaft 201. In other embodiments, the first number may be 3, 5, etc.
In some embodiments, the cross-sectional shape of the central shaft 201 is circular. In other embodiments, the cross-sectional shape of the central shaft 201 may be other shapes, such as oval, square, hexagon, etc.
In some embodiments, the satellite launch box ejection device 100 is switchable between a locked state in which the first sleeve 202 and the second sleeve 203 are adjacent to each other, the first linkage and the second linkage are folded to each other, and the plurality of tension springs 108 in the tension spring set are in a stretched state; in the released state, the plurality of tension springs 108 in the tension spring group are in a natural state, the first link group and the second link group are mutually expanded, and the first shaft sleeve 202 and the second shaft sleeve 203 are mutually far away.
In some embodiments, the locking and releasing mechanism is used to lock the satellite launch box ejection device 100 in the locked state and to release the satellite launch box ejection device 100 from the locked state, so that under the natural restoring action of the plurality of tension springs 108 in the stretched state, the satellite launch box ejection device 100 is switched to the released state, that is, the first linkage and the second linkage are caused to expand, the first bushing 202 and the second bushing 203 are caused to move away from each other, so that the upper fixing plate 101 is caused to be ejected relative to the lower fixing plate 102, and the satellite on the upper fixing plate 102 is released.
In some embodiments, the lock-release mechanism comprises:
an electromagnet 301 fixed on the surface of the lower fixing plate 101 and including a pull rod 302, wherein the pull rod 302 extends out when the electromagnet 301 is powered off and retracts when the electromagnet 301 is powered on;
a locking pin 303 connected to the pull rod 302;
wherein, the outer surface of the lower part of the central shaft 201 is provided with a ring groove 204, and the locking pin 303 is pushed by the pull rod 302 to clamp the ring groove 204 when the electromagnet 301 is powered off, so as to lock the satellite launch box ejection device 100 in a locked state; and the locking pin 303 is pulled by the pull rod 302 to withdraw from the annular groove 204 when the electromagnet 301 is electrified, so that the satellite launching box ejection device 100 is switched to a release state.
In some embodiments, the electromagnet 301 may be electrically connected to a satellite launch system on the rocket, and may be energized in response to a launch command or an electrical signal from the satellite launch system.
In some embodiments, the pull rod 302 of the electromagnet 301 is surrounded by a spring which abuts between the electromagnet 301 and the end surface of the locking pin 303, so that when the electromagnet 301 is de-energized, the locking pin 303 abuts in the annular groove 204 of the central shaft 201, thereby locking the satellite launch box ejection device 100 in a locked state; when the electromagnet 301 is energized, the pull rod 302 overcomes the resistance of the spring, and drives the locking pin 303 to withdraw from the annular groove 204 of the central shaft 201, so that the central shaft 201, the second shaft sleeve 203 and the upper fixing plate 102 move upward relative to the first shaft sleeve 202 and the lower fixing plate 101 as the first link group and the second link group are mutually opened under the restoring action of the tension spring group, thereby ejecting the satellite on the upper fixing plate 102.
In some embodiments, the locking pin 303 and the pull rod 302 may be coupled together by a pin 304, and the pin 304 may pass through pin holes provided in the locking pin 303 and the pull rod 302 to couple the two together.
As mentioned above, in other embodiments, the first bushing 202 is fixedly connected to the lower fixing plate 101 and the central shaft 201, the second bushing 203 is fixedly connected to the upper fixing plate 102, and the central shaft 201 can slide in the second bushing 203. In such an embodiment, the locking and releasing mechanism and the electromagnet 301 thereof can be fixed on the surface of the upper fixing plate 101, the upper outer surface of the central shaft 201 is provided with a ring groove 204, and the locking pin 303 is pushed by the pull rod 302 to clamp the ring groove 204 when the electromagnet 301 is powered off, so as to lock the satellite shooting box ejector 100 in a locking state; when the electromagnet 301 is powered on, the pull rod 302 drives the locking pin 303 to withdraw from the annular groove 204 of the central shaft 201, so that the second bushing 203 and the upper fixing plate 102 are together, and under the restoring action of the tension spring set, as the first link set and the second link set are mutually opened, the first bushing 202 and the lower fixing plate 101 move upwards relative to the central shaft 201, the first bushing 202 and the lower fixing plate 101, so as to launch the satellite on the upper fixing plate 102.
In some embodiments, the length of the extension spring set in the locked state of the satellite pod ejector 101 depends on the required ejection stroke of the satellite pod ejector 100, and/or the elastic modulus of the extension spring set depends on the required ejection force of the satellite pod ejector. That is, the tensile length and the elastic modulus of the tension spring set can be determined or adjusted according to the required ejection stroke and ejection force. If the ejection stroke required by the satellite launch box ejection device 100 is larger, the stretching length of each tension spring 108 in the tension spring set in the locking state of the satellite launch box ejection device 101 is made larger; the greater the ejection force required by the satellite pod ejection device 100, the greater the modulus of elasticity of each tension spring 108 in the set of tension springs. As known to those skilled in the art, the elastic modulus of the tension spring is related to the material, shape and thickness of the tension spring, and thus can be selected by selecting an appropriate material (e.g., spring steel, etc.), shape and thickness of the tension spring.
In some embodiments, the first shaft sleeve 202, the second shaft sleeve 203, the first link assembly, the second link assembly, the pull ring 103, and the tension spring assembly are provided in plurality, and are repeatedly arranged along the central axis 201 between the upper fixing plate 102 and the lower fixing plate 101, and only the first shaft sleeve 202 near the lower fixing plate 101 among the plurality of first shaft sleeves 202 is fixedly connected to the lower fixing plate 101, only the second shaft sleeve 203 near the upper fixing plate 102 among the plurality of second shaft sleeves 203 is fixedly connected to the upper fixing plate 102, and the rest of the adjacent first shaft sleeves 202 and second shaft sleeves 203 are integrated or fixedly connected to each other. That is, the pairs of the first and second link groups and the corresponding tension spring groups may be provided in a multi-stage manner along the central shaft 201 in a superimposed manner, so that the ejection stroke of the satellite shooting box ejector 100 may be further significantly increased.
In some embodiments, the relevant structural components of the satellite launch box ejection device 101 (other than the tension springs) may be made of a lighter material such as magnesium aluminum alloy to further reduce weight.
The satellite launch box ejection device 100 according to embodiments of the present invention is described above with reference to the accompanying drawings, it being noted that the above description and illustrations are only examples and are not limiting of the present invention. In other embodiments of the invention, the apparatus may have more, fewer, or different components, and the connections, inclusion, and functional relationships between the components may be different from those described and illustrated. For example, typically a component will contain sub-components in addition to those shown and described; multiple components may be combined into a single larger component, and so on. All such variations are within the spirit and scope of the present invention.
The satellite launch box ejection device 100 according to the embodiment of the invention realizes the ejection function through the combination of the link mechanism and the extension spring, the ejection mechanism can be freely opened and folded, the gentle ejection can be realized, no impact is generated, the structure is simple, the reliability is high, the size is small, the weight is light, and the cost is low. Compared with the technical scheme that the satellite is ejected from the launching box by means of the recovery action of the compressed compression spring in the prior art, the ejection stroke and the ejection force are greatly improved, the ejection stroke and the ejection force can be adjusted according to needs, and in some embodiments, ejection with a larger stroke can be realized by superposition of a multi-level link mechanism.
Although the present invention has been disclosed above by way of examples, the present invention is not limited thereto. Various changes and modifications within the spirit and scope of the invention will become apparent to those skilled in the art from this disclosure, and the scope of the invention should be determined only by the language of the claims and the equivalents thereof.
Claims (8)
1. A satellite launch box ejection device (100), comprising:
a lower fixing plate (101);
an upper fixing plate (102) for placing a satellite thereon;
a central shaft (201) passing through or located at the center of the lower fixing plate (101) and the upper fixing plate (102);
a first bushing (202) mounted on the central shaft (201);
a second shaft sleeve (203) which is installed on the central shaft (201), wherein the first shaft sleeve (202) and the second shaft sleeve (203) are positioned between the lower fixing plate (101) and the upper fixing plate (102), and the first shaft sleeve (202) and the second shaft sleeve (203) can slide relatively along the central shaft (201);
a first link group including a first number of a plurality of first links (106) circumferentially arranged along the central shaft (201), a first end of each first link (106) being pivotally connected to the first bushing (202);
a second linkage comprising a first number of a plurality of second links (107) arranged circumferentially along the central axis (201), a first end of each second link (107) being pivotally connected to the second hub (203), wherein a second end of each first link (106) is pivotally connected to a second end of the respective second link (107);
a pull ring (103) mounted directly or indirectly on the central shaft (201) and located between the first sleeve (202) and the second sleeve (203);
a tension spring set comprising a second number of a plurality of tension springs (108) circumferentially arranged along the central shaft (201), the second number being equal to the first number or twice the first number, each tension spring (108) having a first end connected to the pull ring (103) and a second end connected to a second end of the respective first link (106) and second link (107); and
and the locking and releasing mechanism is used for switching the satellite launching box ejection device (100) from a locking state to a releasing state, wherein in the locking state, the first shaft sleeve (202) and the second shaft sleeve (203) are close to each other, the first link group and the second link group are folded with each other, the tension spring group is in a stretching state, so that under the restoring action of the tension spring group, the first link group and the second link group are mutually unfolded, the first shaft sleeve (202) and the second shaft sleeve (203) are mutually separated, and the upper fixing plate (102) is driven to be ejected relative to the lower fixing plate (101), so that the satellite is ejected and released.
2. The satellite launch box ejection device of claim 1, wherein the first bushing (202) is fixedly connected to the lower fixed plate (101), the second bushing (203) is fixedly connected to the upper fixed plate (102) and the central shaft (201), and the central shaft (201) is slidable in the first bushing (202).
3. The satellite launch box ejection device of claim 2, wherein the lock-release mechanism comprises:
the electromagnet (301) is fixed on the surface of the lower fixing plate (101) and comprises a pull rod (302), and the pull rod (302) extends out when the electromagnet (301) is powered off and retracts when the electromagnet (301) is powered on;
a locking pin (303) connected with the pull rod (302);
wherein, the outer surface of the lower part of the central shaft (201) is provided with a ring groove (204), and the locking pin (303) is pushed by the pull rod (302) to clamp the ring groove (204) when the electromagnet (301) is powered off, so that the satellite launching box ejection device (100) is locked in a locking state; and the locking pin (303) is pulled by the pull rod (302) to withdraw from the annular groove (204) when the electromagnet (301) is electrified, so that the satellite launching box ejection device (100) is switched to a release state.
4. The satellite launch box ejection device of claim 1, wherein the first bushing (202) is fixedly connected to the lower fixed plate (101) and the central shaft (201), the second bushing (203) is fixedly connected to the upper fixed plate (102), and the central shaft (201) is slidable in the second bushing (203).
5. The satellite launch box ejection device of claim 4, wherein the lock-release mechanism comprises:
an electromagnet (301) fixed on the surface of the upper fixing plate (102) and comprising a pull rod (302), wherein the pull rod (302) extends out when the electromagnet (301) is powered off and retracts when the electromagnet (301) is powered on;
a locking pin (303) connected with the pull rod (302);
wherein, an annular groove (204) is arranged on the outer surface of the upper part of the central shaft (201), and the locking pin (303) is pushed by the pull rod (302) to clamp the annular groove (204) when the electromagnet (301) is powered off, so that the satellite launching box ejection device (100) is locked in a locking state; and the locking pin (303) is pulled by the pull rod (302) to withdraw from the annular groove (204) when the electromagnet (301) is electrified, so that the satellite launching box ejection device (100) is switched to a release state.
6. The satellite launch box ejection device of claim 1, wherein the first number is four.
7. The satellite launch box ejection device of claim 1, wherein the extension length of the extension spring set in the locked state of the satellite launch box ejection device is dependent on the required ejection stroke of the satellite launch box ejection device, and/or the modulus of elasticity of the extension spring set is dependent on the required ejection force of the satellite launch box ejection device.
8. The satellite launch box ejection device of any one of claims 1-7,
the first shaft sleeve (202), the second shaft sleeve (203), the first connecting rod group, the second connecting rod group, the pull ring (103) and the tension spring group are multiple, the first shaft sleeve (202) close to the lower fixing plate (101) is fixedly connected with the lower fixing plate (101) in the first shaft sleeves (202) along the central shaft (201), the second shaft sleeve (203) close to the upper fixing plate (102) is fixedly connected with the upper fixing plate (102) in the second shaft sleeves (203), and the rest adjacent first shaft sleeves (202) and second shaft sleeves (203) are integrated or fixedly connected with each other.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210426806.1A CN114735246A (en) | 2022-04-22 | 2022-04-22 | Satellite launching box ejection device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210426806.1A CN114735246A (en) | 2022-04-22 | 2022-04-22 | Satellite launching box ejection device |
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| Publication Number | Publication Date |
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| CN114735246A true CN114735246A (en) | 2022-07-12 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210426806.1A Pending CN114735246A (en) | 2022-04-22 | 2022-04-22 | Satellite launching box ejection device |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115057012A (en) * | 2022-08-03 | 2022-09-16 | 北京劢亚科技有限公司 | Multi-satellite chain type launching, locking, unlocking and ejecting mechanism |
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2022
- 2022-04-22 CN CN202210426806.1A patent/CN114735246A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115057012A (en) * | 2022-08-03 | 2022-09-16 | 北京劢亚科技有限公司 | Multi-satellite chain type launching, locking, unlocking and ejecting mechanism |
| CN115057012B (en) * | 2022-08-03 | 2022-10-25 | 北京劢亚科技有限公司 | Multi-satellite chain type launching, locking, unlocking and ejecting mechanism |
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