CN212243887U - Combined type satellite-borne load ejection unlocking device - Google Patents
Combined type satellite-borne load ejection unlocking device Download PDFInfo
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- CN212243887U CN212243887U CN202020897484.5U CN202020897484U CN212243887U CN 212243887 U CN212243887 U CN 212243887U CN 202020897484 U CN202020897484 U CN 202020897484U CN 212243887 U CN212243887 U CN 212243887U
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- borne load
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Abstract
The utility model discloses a combination formula satellite-borne load launches unlocking device, which comprises a housin, be equipped with the holder that is used for centre gripping satellite-borne load in the casing, holder main part and the guide piece sliding fit in the casing, the one end of holder is equipped with the chuck, the chuck with by the cooperation of the portion of waiting to hold of centre gripping satellite-borne load, the other end of holder is equipped with the clamping handle, the inboard or the outside of clamping handle are equipped with the elastic component, be equipped with the inflation part in the outside or the inboard of the clamping handle corresponding with the elastic component position, be equipped with the support positioning part in the outside of elastic component and inflation part, it launches the bucket to be equipped with below the satellite-borne load of waiting to launch, it supports bottom and/or the lateral wall at the casing through support piece to launch the bucket, the inner wall of launching the bucket is equipped with the support step of the satellite-borne load that. The combined satellite-borne load ejection unlocking device has the characteristics of simple structure, safe and reliable release of the satellite-borne load, easiness in control, small size, light weight, reusability and the like.
Description
Technical Field
The utility model relates to an aerospace transmission technical field, concretely relates to combination formula spaceborne load launches unlocking device.
Background
With the development of space technology and the increasing frequency of space exploration activities of human beings, the number of satellites in the space is increased, and simultaneously, the functions required to be completed by the satellites also need to be upgraded. While the functions performed by the satellite are mainly performed by the loading task. Therefore, if the satellite loading task can be separated, different flight tasks can be completed on one satellite body based on the basis of the docking technology and the on-orbit service technology. In conventional satellites, the load tasks are fixed in a monolithic design and cannot be changed during orbital flight. With the rapid development of the aerospace technology, the on-orbit service technology of the spacecraft comes up. The on-orbit service technology is provided, and the service spacecraft is required to realize the capabilities of refueling, replacing a fault module, maintaining and the like. Between the small satellites and the serving spacecraft, a technology must therefore be developed in which the load can be replaced and the satellite body can be reused.
To achieve this function, the satellite body and the load task subsystem module are required to have a supporting replaceable transmitting interface to meet the replaceable transmitting of the load task. The interface has to be reusable, and can realize that the satellite body and the load task subsystem module can be ejected out from the main body of the mother satellite without damaging the load task subsystem;
therefore, a small satellite catapult launching device must be designed to solve the technical problem of releasing the load task.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to overcome the defect that exists among the prior art, provide a simple structure, spaceborne load release safe and reliable, easily control, small, light in weight, repeatedly usable's combination formula spaceborne load launch unlocking device.
In order to achieve the purpose, the technical proposal of the utility model is to provide a combined satellite-borne load ejection unlocking device, the device comprises a shell, a clamping piece for clamping the satellite-borne load is arranged in the shell, a main body of the clamping piece is in sliding fit with a guide piece in the shell, one end of the clamping piece is provided with a chuck which is matched with a part to be clamped of the clamped satellite-borne load, the other end of the clamping piece is provided with a clamping handle, the inner side or the outer side of the clamping handle is provided with an elastic piece, an expansion part is arranged at the outer side or the inner side of the clamp handle corresponding to the position of the elastic part, a supporting and positioning part is arranged outside the elastic part and the expansion part, an ejection barrel is arranged below the satellite-borne load to be ejected, the ejection barrel is supported at the bottom and/or the side wall of the shell through a supporting piece, a supporting step of the satellite-borne load to be ejected is arranged on the inner wall of the ejection barrel, and an ejector is arranged in the ejection barrel below the supporting step.
In order to facilitate the satellite-borne load to be placed at a proper position in the main body of the mother satellite and ensure that the satellite-borne load cannot fall off before re-emission, the preferred technical scheme is that the shell is of a barrel-shaped structure, the shape and the size of the outer wall of the shell are matched with those of a reserved cavity in the carrying body, a shell cover is arranged on the shell, and the shell cover is hinged with the upper edge of the shell through a torsion spring hinge.
In order to simplify the structure of the clamping piece, the clamped satellite-borne load is firmly clamped, and the clamping piece cannot swing in a shell in a deviating way, the preferred technical scheme is that the clamping piece at least comprises a crossed clamp, the middle part of the clamp is hinged through a pin shaft, a chuck of the crossed clamp is in sliding fit with at least one section of a clamp handle and a guide groove arranged on the inner wall of the shell, or guide holes are arranged on the chuck and the clamp handle and are in sliding fit with guide columns arranged on the inner wall of the shell.
In order to simplify the structure of the clamping member, firmly clamp the clamped satellite-borne load, and prevent the clamping member from deviating and swinging in the shell, a further preferable technical scheme is that the pair of crossed clamps are arranged and distributed in a cross shape.
In order to simplify the structure of the clamping piece, the clamped satellite-borne load is clamped firmly, and the clamping piece cannot swing in a shell in a deviating manner.
In order to simplify the structure of the clamping piece, the clamped satellite-borne load is firmly clamped, and the clamping piece cannot swing in a shell in a deviating way, the preferred technical scheme is that three cosine waveform clamping pieces are arranged, and the three cosine waveform clamping pieces are uniformly distributed on the circumferential section.
In order to prevent the clamped satellite-borne load from falling off, a further preferred embodiment is that a hook facing the clamping direction is provided at the chuck portion.
In order to ensure that the clamping piece has lasting clamping force and can ensure that the elastic piece cannot fall off, the further preferred technical scheme is that the elastic piece is a pressure spring, and a pressure spring installation groove or a pressure spring installation hole or a flexible sleeve sleeved with the pressure spring is arranged outside the pressure spring.
In order to ensure that the clamped satellite-borne load can be quickly and reliably separated from the clamping of the clamping piece and can be kept in a separated clamping state for a certain time, the expansion part is preferably an expansion air bag, expansion medicine is filled in the expansion air bag, and a guide switch triggering the expansion medicine is connected with a controller outside the shell through a lead, a plug or a socket.
In order to ensure that the clamped satellite-borne load can be quickly and reliably separated from the clamping of the clamping piece and simultaneously ejected, the satellite-borne load cannot be damaged, the separated clamping state can be maintained for a certain time, the preferred technical scheme is that the ejector is a quick expansion compound, a gasket is arranged between the quick expansion compound and the satellite-borne load to be ejected, and a guide switch of the quick expansion compound is connected with a controller outside the shell through a lead, a plug or a socket.
The utility model has the advantages of beneficial effect lie in, this combination formula satellite-borne load launches unlocking device simple structure, satellite-borne load release safe and reliable, characteristics such as easy control, small, light in weight, repeatedly usable. The satellite-borne load is tightly clamped by a clamping piece before ejection is sent, an elastic piece is arranged on one side of a clamping handle part at the bottom of the clamping piece, the satellite-borne load is kept clamped by the clamping piece through the elasticity of the elastic piece, the clamping piece is positioned and guided through a guide piece, the guide piece is arranged on the inner wall of a shell, the bottom of the satellite-borne load to be launched is supported on a stepped seat on the inner wall of a launching barrel, a quick expansion compound is arranged below the stepped seat on the inner wall of the launching barrel, a base plate is arranged between the quick expansion compound and the satellite-borne load, and an expansion piece is arranged on the other side of the clamping handle part at the bottom of the. When the satellite-borne load needs to be launched, the expansion piece such as an air bag expands, the expansion piece presses the elastic piece after expanding, the clamped satellite-borne load is released after the elasticity is pressed, meanwhile, the quick expansion compound is ignited, the quick expansion compound pushes the gasket, and the gasket pushes the satellite-borne load to launch the satellite-borne load. The dosage of the quick-expansion compound is calculated and set in advance, and the set thrust and the set ejection speed can be generated on the satellite-borne load through the set charge.
Drawings
Fig. 1 is one of schematic cross-sectional structural diagrams of the combined satellite-borne load ejection unlocking device of the present invention;
fig. 2 is a second schematic sectional view of the combined satellite-borne load ejection unlocking device of the present invention;
FIG. 3 is a schematic sectional view A-A of FIG. 2;
FIG. 4 is a schematic cross-sectional view B-B of FIG. 2;
fig. 5 is a third schematic view of a sectional structure of the combined satellite-borne load ejection unlocking device of the present invention;
fig. 6 is a schematic cross-sectional structure view of fig. 5C-C.
In the figure: 1. a housing; 1.1, a shell cover; 1.2, a support member; 2. carrying out satellite-borne load; 3. a clamping member; 3.1, clamping heads; 3.2, clamping a handle; 3.3, a pin shaft; 3.4, hooking; 4. a guide member; 5. an elastic member; 6. an expansion member; 7. a support positioning member; 8. ejecting a barrel; 8.1, a support member; 8.2, supporting a step; 9. a projectile body; 10. and (7) a gasket.
Detailed Description
The following description will further describe embodiments of the present invention with reference to the accompanying drawings and examples. The following examples are only for illustrating the technical solutions of the present invention more clearly, and the protection scope of the present invention is not limited thereby.
As shown in fig. 1-5, the utility model relates to a combined satellite-borne load ejection unlocking device, which comprises a housing 1, a clamping member 3 for clamping a satellite-borne load 2 is arranged in the housing 1, the main body of the clamping member 3 is in sliding fit with a guide member 4 in the housing 1, one end of the clamping member 3 is provided with a chuck 3.1, the chuck 3.1 is matched with a part to be clamped of the satellite-borne load 2, the other end of the clamping member 3 is provided with a clamping handle 3.2, the inner side or the outer side of the clamping handle 3.2 is provided with an elastic member 5 (a pressure spring), the outer side or the inner side of the clamping handle 3.2 corresponding to the position of the elastic member 5 is provided with an expansion member 6 (an inflatable air bag), a supporting and positioning member 7 is arranged outside the elastic member 5 and the expansion member 6, an ejection barrel 8 is arranged below the satellite-borne load 2 to be ejected, the ejection barrel 8 is supported at the bottom and/or the side wall of the housing 1 through a supporting step 8.1, the inner wall of the ejection, an ejection body 9 is arranged in the ejection barrel 8 below the supporting step 8.2.
The shell 1 can be made of metal or plastic, the external shape of the shell can be the same as or different from the internal shape of the shell, the shell can be of an integral structure or a split structure, and the shell of the integral structure can be made of stamping parts or castings. The split type can be connected through connecting pieces, such as riveting, welding, bolt connection and the like, and can also be connected through a plug-in or buckling connection structure. The guide 4 in the housing can be made as a fitting fitted on the inside of the housing or as an integral guide structure with the housing. The guide piece of the accessory structure can be fixedly connected with the inner wall of the shell in a connecting mode of riveting, welding, bolt connection, insertion and the like. The integral guide piece structure integrated with the shell can be a guide groove arranged on a convex edge of the inner wall of the shell. The clamping piece 3 can adopt an integral structure or a split structure, and the shell of the integral structure can adopt a stamping piece or a casting piece. The split type can be connected through connecting pieces, such as riveting, welding, bolt connection and the like, and can also be connected through a plug-in or buckling connection structure. The clamp members of fig. 1-4 are of the type employing a pair of jaws hinged to one another in a cross-wise fashion. The clamping piece is simple in structure, easy to machine and manufacture, firm in clamping and high in reliability when clamping the satellite-borne load. The elastic part 5 can adopt a helical compression spring, also can adopt an arch-shaped elastic sheet structure, and also can adopt an elastic rubber part or a plastic structural part with arch-shaped elasticity. The expansion part 6 can adopt a nylon bag or a plastic bag, or can adopt a cloth bag with the inner surface coated with an elastic glue layer. The supporting and positioning component 7 can be a frame structural component, a net structural component, a shell structural component, a light foaming component and the like. The ejection barrel 8 has a supporting effect on the ejected satellite-borne load 2 and is used for filling the medicament for ejecting the satellite-borne load 2, the ejection barrel 8 can be of an integral structure or a split structure, and a shell of the integral structure can be a stamping part or a casting part. The split type can be connected through connecting pieces, such as riveting, welding, bolt connection and the like, and can also be connected through a plug-in or buckling connection structure. The projectile 9 may be solid powder or liquid powder, or may be an elastic device driven by an electromagnetic relay.
In order to facilitate placing satellite-borne load 2 at the inside appropriate position of mother satellite main part to can ensure that it can not drop before reemission, the utility model discloses preferred embodiment is, casing 1 is the tubbiness structure, and 1 outer wall shape of casing and size and the shape and the size looks adaptation of carrying the inside reservation cavity of physique are equipped with cap 1.1 on the casing 1, and cap 1.1 is articulated through torsional spring hinge and 1 upper edge of casing. Can be connected through hinge structure between casing and the cap, also can be connected through buckle structure, can also connect through adhesive structure, can set up easily to tear the line on the cap, the cap can also adopt hot melt material to make, or adopt broken material to make, like this can be broken after the cap receives the impact force.
In order to simplify the structure of holder 3, make by the 2 centre gripping of the spaceborne load of centre gripping firm, make holder 3 can not take place the skew swing in casing 1, the utility model discloses preferred embodiment still, holder 3 is at least including a crossing clamp, and the middle part of clamp is articulated through round pin axle 3.3, and the chuck of crossing clamp and the at least one section on the clamping holder and the guide way sliding fit of setting on casing 1 inner wall, or be equipped with the guiding hole on chuck and clamping holder, guiding hole and the guide post sliding fit of setting on shells inner wall. The guide post or the guide hole can be arranged on the forceps handle and can also be arranged on the inner wall of the shell. The clamp can be made into metal clamps or plastic clamps.
In order to simplify the structure of holder 3, make by the centre gripping of 2 centre grippings of spaceborne load firm, make the holder can not take place the skew swing in casing 1, the utility model discloses further preferred embodiment still, the cross clamp is equipped with a pair ofly, and a pair of cross clamp is the cross and distributes. The crossed clamp can also be provided with a plurality of pairs which are uniformly distributed in the shell.
As shown in fig. 5 and 6, in order to simplify the structure of the holding member 3, the holding member 3 is clamped firmly by the satellite-borne load 2, so that the holding member 3 does not swing in the housing 1, the preferred embodiment of the present invention is also that the holding member 3 is in a cosine wave structure, the holding member 3 is at least provided with two holding members, the middle part of the holding member 3 is hinged to the supporting member 1.2 arranged on the inner wall of the housing 1, at least one section of the clamping head 3.1 and the clamping handle 3.2 of the holding member 3 is in sliding fit with the guide groove arranged on the inner wall of the housing 1, or the clamping head 3.1 and the clamping handle 3.2 are provided with guide holes, and the guide holes are in sliding fit with the guide posts arranged on the inner wall of the housing 1.
The shell 1 in fig. 5 and 6 can be made of metal or plastic, the external shape of the shell can be the same or different with the internal shape of the shell, the shell can be of an integral structure or a split structure, and the shell of the integral structure can be made of stamping parts or castings. The split type can be connected through connecting pieces, such as riveting, welding, bolt connection and the like, and can also be connected through a plug-in or buckling connection structure. The guide 4 in the housing can be made as a fitting fitted on the inside of the housing or as an integral guide structure with the housing. The guide piece of the accessory structure can be fixedly connected with the inner wall of the shell in a connecting mode of riveting, welding, bolt connection, insertion and the like. The integral guide piece structure integrated with the shell can be a guide groove arranged on a convex edge of the inner wall of the shell. The clamping piece 3 can adopt an integral structure or a split structure, and the shell of the integral structure can adopt a stamping piece or a casting piece. The split type can be connected through connecting pieces, such as riveting, welding, bolt connection and the like, and can also be connected through a plug-in or buckling connection structure. The clamps in fig. 5 and 6 are at least 3 clamps with cosine waveforms, which are not in the shell. The clamping piece is simple in structure, easy to machine and manufacture, firm in clamping and high in reliability when clamping the satellite-borne load. The elastic part 5 can adopt a helical compression spring, also can adopt an arch-shaped elastic sheet structure, and also can adopt an elastic rubber part or a plastic structural part with arch-shaped elasticity. The expansion part 6 can adopt a nylon bag or a plastic bag, or can adopt a cloth bag with the inner surface coated with an elastic glue layer. The supporting and positioning component 7 can be a frame structural component, a net structural component, a shell structural component, a light foaming component and the like. The ejection barrel 8 has a supporting effect on the ejected satellite-borne load 2 and is used for filling the medicament for ejecting the satellite-borne load 2, the ejection barrel 8 can be of an integral structure or a split structure, and a shell of the integral structure can be a stamping part or a casting part. The split type can be connected through connecting pieces, such as riveting, welding, bolt connection and the like, and can also be connected through a plug-in or buckling connection structure. The projectile 9 may be solid powder or liquid powder, or may be an elastic device driven by an electromagnetic relay.
In order to simplify the structure of holder 3, make by the 2 centre gripping of the satellite-borne load of centre gripping firm, make holder 3 can not take place the skew swing in casing 1, the utility model discloses further preferred embodiment still, cosine waveform holder 3 is provided with threely, three cosine waveform holder 3 equipartition on circumference shape cross-section. Of course, a plurality of evenly distributed clamping elements can also be provided.
In order to prevent the clamped satellite-borne load from falling off, a further preferred embodiment of the invention is that the clamping head 3.1 is provided with a hook 3.4 facing the clamping direction. The hook and the chuck can be made into an integral structure or a split structure, and the hook of the split structure can be connected in a threaded connection mode, a welded and inserted connection mode and the like. The hooks may also be made of a hot melt material.
In order to ensure that holder 4 has lasting clamping force, can ensure moreover that elastic component 5 can not drop, the utility model discloses further preferred embodiment still has, elastic component 5 is the pressure spring, and the pressure spring outside is equipped with the pressure spring mounting groove, or the pressure spring mounting hole, or the flexible sleeve of suit pressure spring.
In order to ensure that the clamped satellite-borne load 2 can be quickly and reliably separated from the clamping part 3 and can be kept separated from the clamping state for a certain time, the utility model discloses preferred embodiment still further, the expansion part 6 is the inflation gasbag, and the inflation medicament is added in the inflation gasbag, and the guide switch that ignites the inflation medicament passes through the wire, plug or socket and is connected with the outside controller of casing.
In order to ensure that the clamped satellite-borne load 2 can be quickly and reliably released from the clamping member and simultaneously ejected, and does not cause any damage to the satellite-borne load 2, and can be kept released from the clamping state for a certain time, the preferred embodiment of the present invention is further characterized in that the ejector 6 is a quick expansion compound, a gasket 10 is provided between the quick expansion compound and the satellite-borne load 2 to be ejected, and a guide switch of the quick expansion compound is connected with a controller outside the housing through a wire, a plug or a socket.
The combined satellite-borne load ejection unlocking device has the characteristics of simple structure, safe and reliable release of the satellite-borne load, easiness in control, small size, light weight, reusability and the like. The satellite-borne load is tightly clamped by a clamping piece before ejection is sent, an elastic piece is arranged on one side of a clamping handle part at the bottom of the clamping piece, the satellite-borne load is kept clamped by the clamping piece through the elasticity of the elastic piece, the clamping piece is positioned and guided through a guide piece, the guide piece is arranged on the inner wall of a shell, the bottom of the satellite-borne load to be launched is supported on a stepped seat on the inner wall of a launching barrel, a quick expansion compound is arranged below the stepped seat on the inner wall of the launching barrel, a base plate is arranged between the quick expansion compound and the satellite-borne load, and an expansion piece is arranged on the other side of the clamping handle part at the bottom of the. When the satellite-borne load needs to be launched, the expansion piece such as an air bag expands, the expansion piece presses the elastic piece after expanding, the clamped satellite-borne load is released after the elasticity is pressed, meanwhile, the quick expansion compound is ignited, the quick expansion compound pushes the gasket, and the gasket pushes the satellite-borne load to launch the satellite-borne load. The dosage of the quick-expansion compound is calculated and set in advance, and the set thrust and the set ejection speed can be generated on the satellite-borne load through the set charge.
The foregoing is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, a plurality of improvements and decorations can be made without departing from the technical principle of the present invention, and these improvements and decorations should also be regarded as the protection scope of the present invention.
Claims (10)
1. Modular satellite-borne load ejection unlocking device, its characterized in that, the device includes: the device comprises a shell, a clamping piece used for clamping the satellite-borne load is arranged in the shell, a clamping piece body is in sliding fit with a guide piece in the shell, a chuck is arranged at one end of the clamping piece and is matched with a to-be-clamped part of the clamped satellite-borne load, a clamping handle is arranged at the other end of the clamping piece, an elastic piece is arranged on the inner side or the outer side of the clamping handle, an expansion part is arranged on the outer side or the inner side of the clamping handle corresponding to the position of the elastic piece, a supporting and positioning part is arranged outside the elastic piece and the expansion part, an ejection barrel is arranged below the satellite-borne load to be ejected and is supported at the bottom and/or the side wall of the shell through a supporting piece, a supporting step of the satellite-borne load to be ejected is arranged on the inner wall of the.
2. The combined type satellite-borne load ejection unlocking device as claimed in claim 1, wherein the housing is a barrel-shaped structure, the shape and the size of the outer wall of the housing are matched with those of a cavity reserved in the carrying body, and a housing cover is arranged on the housing and hinged to the upper edge of the housing through a torsion spring hinge.
3. The combined satellite-borne load ejection unlocking device as claimed in claim 2, wherein the clamping member comprises at least one cross-type clamp, the middle part of the clamp is hinged through a pin shaft, a chuck of the cross-type clamp and at least one section of the clamp holder are in sliding fit with a guide groove arranged on the inner wall of the shell, or a guide hole is arranged on the chuck and the clamp holder and is in sliding fit with a guide column arranged on the inner wall of the shell.
4. The combined satellite-borne load ejection unlocking device as claimed in claim 3, wherein the cross-type clamps are provided in a pair, and the pair of cross-type clamps are distributed in a cross shape.
5. The combined satellite-borne load ejection unlocking device as claimed in claim 1, wherein the clamping member is of a cosine wave structure, at least two clamping members are provided, the middle part of the clamping member is hinged with a support member arranged on the inner wall of the shell, and a clamping head of the clamping member and at least one section of the clamping handle are in sliding fit with a guide groove arranged on the inner wall of the shell, or a guide hole is formed on the clamping head and the clamping handle and is in sliding fit with a guide column arranged on the inner wall of the shell.
6. The combined satellite-borne load ejection unlocking device according to claim 5, wherein three cosine-wave-shaped clamping pieces are provided, and the three cosine-wave-shaped clamping pieces are uniformly distributed on the circumferential section.
7. The combined satellite-borne load ejection unlocking device as claimed in any one of claims 3 to 6, wherein a hook facing the tightening direction is provided at the chuck portion.
8. The combined type satellite-borne load ejection unlocking device according to claim 7, wherein the elastic member is a compression spring, and a compression spring installation groove is formed in the outer portion of the compression spring, or a compression spring installation hole is formed in the outer portion of the compression spring, or a flexible sleeve is sleeved on the compression spring.
9. The combined satellite-borne load ejection unlocking device as claimed in claim 1, wherein the expansion part is an expansion air bag, an expansion medicament is filled in the expansion air bag, and a guide switch for triggering the expansion medicament is connected with a controller outside the shell through a lead, a plug or a socket.
10. The combination satellite-borne load ejection unlocking device of claim 1, wherein the projectile is a quick-expansion compound, a gasket is provided between the quick-expansion compound and the satellite-borne load to be ejected, and a guide switch of the quick-expansion compound is connected with the controller outside the housing through a wire, a plug or a socket.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020897484.5U CN212243887U (en) | 2020-05-25 | 2020-05-25 | Combined type satellite-borne load ejection unlocking device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020897484.5U CN212243887U (en) | 2020-05-25 | 2020-05-25 | Combined type satellite-borne load ejection unlocking device |
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| Publication Number | Publication Date |
|---|---|
| CN212243887U true CN212243887U (en) | 2020-12-29 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202020897484.5U Expired - Fee Related CN212243887U (en) | 2020-05-25 | 2020-05-25 | Combined type satellite-borne load ejection unlocking device |
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| CN (1) | CN212243887U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114180108A (en) * | 2021-11-29 | 2022-03-15 | 中国航天科工集团八五一一研究所 | Air spring-based casting and separating device |
-
2020
- 2020-05-25 CN CN202020897484.5U patent/CN212243887U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114180108A (en) * | 2021-11-29 | 2022-03-15 | 中国航天科工集团八五一一研究所 | Air spring-based casting and separating device |
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