CN113998152A - Star Arrow Separation Device - Google Patents
Star Arrow Separation Device Download PDFInfo
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- CN113998152A CN113998152A CN202110236898.2A CN202110236898A CN113998152A CN 113998152 A CN113998152 A CN 113998152A CN 202110236898 A CN202110236898 A CN 202110236898A CN 113998152 A CN113998152 A CN 113998152A
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- connecting body
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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
The invention provides a satellite and rocket separation device, which comprises: the satellite rocket comprises a first connecting body and a second connecting body, wherein the first connecting body is connected with a satellite, the second connecting body is connected with a rocket, and the first connecting body and the second connecting body are separably connected; the locking mechanism is arranged on the second connecting body and provided with a locking position and a separating position, the locking mechanism locks the first connecting body on the second connecting body when located at the locking position, and the locking mechanism separates the first connecting body from the second connecting body when located at the separating position; and the driving mechanism is connected with the locking mechanism to drive the locking mechanism to move between the locking position and the separation position, and comprises a driving motor and a cam assembly, and the driving motor is in driving connection with the cam assembly to control the locking mechanism to move through the cam assembly. The star-arrow separating device solves the problems that the star-arrow separating device in the prior art is unsafe and not environment-friendly.
Description
Technical Field
The invention relates to the technical field of spaceflight, in particular to a satellite-rocket separation device.
Background
The satellite-rocket separation device mainly comprises: the fire separation device, the fire belting separation device, the non-fire belting separation device and the fire belting separation device are different in satellite shape, the design of the satellite and rocket separation device is different, the satellite and rocket separation device is separated by spring ejection mostly, and the separation driving modes mainly comprise an explosion bolt, motor driving, resistance wire fusing, electromagnetic driving and the like.
The design of the satellite and arrow separating device needs to comprehensively consider the requirements of simple structure, light weight, separation precision, anti-interference capability, small separation pollution, high reliability and the like, the existing satellite and arrow separating devices are various, and the traditional satellite and arrow separating system adopts a firer separating device which has the defects of unknown safety of explosion bolts, large explosion impact, poor safety, large impact load and the like. The non-fire work bag belt separating device has various forms, but has the defects of high bag belt price, easy satellite clamping of the bag belt during separation and the like. At present, non-belted satellite arrow analysis devices are mostly adopted, wherein the separation driving is mainly divided into an electric driving mode, an electromagnetic driving mode and a resistance fusing direct driving mode, and after the separation driving mode is electrified, a certain magnetic field can be generated, so that the work of certain precise satellite instruments is influenced, and the separation driving mode is unreliable.
Disclosure of Invention
The invention mainly aims to provide a satellite and arrow separating device, which aims to solve the problems that the satellite and arrow separating device in the prior art is unsafe and not environment-friendly.
In order to achieve the above object, according to one aspect of the present invention, there is provided a satellite-rocket separation device, comprising: the satellite rocket comprises a first connecting body and a second connecting body, wherein the first connecting body is connected with a satellite, the second connecting body is connected with a rocket, and the first connecting body and the second connecting body are separably connected; the locking mechanism is arranged on the second connecting body and provided with a locking position and a separating position, the locking mechanism locks the first connecting body on the second connecting body when located at the locking position, and the locking mechanism separates the first connecting body from the second connecting body when located at the separating position; and the driving mechanism is connected with the locking mechanism to drive the locking mechanism to move between the locking position and the separation position, and comprises a driving motor and a cam assembly, and the driving motor is in driving connection with the cam assembly to control the locking mechanism to move through the cam assembly.
Further, the locking mechanism includes: and the jaw assembly is arranged on the second connector, so that the second connector is connected with the first connector in a clamping manner through the jaw assembly.
Further, the jaw assembly includes: and the clamping jaws are arranged on the second connecting body at intervals to form an annular structure, wherein each clamping jaw is arranged in a contractible mode along the radial direction of the annular structure to move close to each other to a separation position or move far away from each other to a locking position at the same time.
Furthermore, the clamping jaw is provided with a positioning bulge, the first connecting body is provided with a positioning hole, when the locking mechanism moves to the locking position, the positioning bulge is inserted into the positioning hole to fix the first connecting body and the clamping jaw together, and when the locking mechanism moves to the separation position, the positioning bulge is separated from the positioning hole to separate the first connecting body and the clamping jaw.
Further, the satellite-rocket separation device further comprises: the rand subassembly, rand subassembly and a plurality of jack catch are all connected, and wherein, actuating mechanism passes through the rand subassembly and drives a plurality of jack catches removal simultaneously.
Further, the rand subassembly includes the rand, and the rand cover is established in the outside of jack catch subassembly, and wherein, the rand is the annular structure of not closing, and the rand has first drive end and second drive end, and actuating mechanism drives first drive end and second drive end simultaneously and moves near each other or keep away from ground to drive a plurality of jack catches and move near each other or keep away from ground simultaneously.
Further, satellite-rocket separation device still includes slider mechanism, and slider mechanism sets up on the second connector, and wherein, slider mechanism includes: the sliding rail component is arranged on the second connecting body; the locking block is movably arranged on the slide rail assembly and is simultaneously in driving connection with the first driving end and the second driving end; the driving mechanism is in driving connection with the locking block, the locking block is provided with a first position and a second position, so that the first driving end and the second driving end are driven to be close to each other when the locking block moves to the first position, and the first driving end and the second driving end are driven to be away from each other when the locking block moves to the second position.
Further, the satellite-rocket separation device further comprises: and the ejection mechanism is arranged on the second connecting body and is in driving connection with the first connecting body so as to drive the first connecting body to be separated from the second connecting body when the locking mechanism moves to the separation position.
Further, the ejection mechanism includes: and the springs are uniformly distributed on the second connecting body and are respectively connected with different positions of the first connecting body, wherein each spring is respectively in a compressed state so as to push the first connecting body to move when the locking mechanism moves to the separation position.
The satellite and rocket separation device adopting the technical scheme of the invention is mainly applied to controlling the separation of the satellite and the rocket when the satellite and the rocket are separated, particularly, the first connecting body of the rocket separation device is fixed with the satellite, the second connecting body is fixed on the rocket, the satellite is connected with the rocket through the satellite and rocket separation device, when the satellite and the rocket are separated, the driving motor of the driving mechanism works, the locking mechanism is driven to move from the locking position to the separation position through driving the rotation of the cam component, the locking mechanism moves to the separation position, so that the first connecting body and the second connecting body can be separated, at the moment, the first connecting body and the second connecting body can be separated through pushing force far away from the rocket to the satellite, the separation device adopts mechanical structure action to complete the separation of the satellite and the rocket, and compared with a firer separation device, the separation is more environment-friendly, and the separation is safer and more reliable, and does not cause interference to other equipment.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate embodiments of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:
FIG. 1 shows a schematic structural view of an embodiment of a satellite-rocket separation device according to the invention;
FIG. 2 is a partial schematic structural view of an embodiment of the satellite-rocket separation device of the invention;
FIG. 3 shows an exploded schematic view of an embodiment of the satellite-rocket separation device of the present invention;
FIG. 4 shows a schematic view of a jaw embodiment of the satellite-rocket separation device of the present invention;
FIG. 5 shows a schematic view of an embodiment of an ejection mechanism of the satellite and rocket separation device of the present invention;
FIG. 6 shows a schematic view of a collar assembly embodiment of the satellite-rocket separation device of the present invention;
fig. 7 shows a schematic view of an embodiment of the driving mechanism of the satellite-rocket separation device of the invention.
Wherein the figures include the following reference numerals:
10. a first connecting body; 11. positioning holes; 20. a second connector; 30. a locking mechanism; 31. a claw; 311. positioning the projection; 40. a collar; 41. a drive motor; 42. a cam assembly; 43. a first driving end; 44. a second drive end; 45. a first locking block structure; 46. a second locking block structure; 51. a locking block; 52. a slide rail assembly; 60. a spring.
Detailed Description
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
The invention provides a satellite and arrow separating device, aiming at solving the problems that the satellite and arrow separating device in the prior art is unsafe and not environment-friendly.
Referring to fig. 1 to 7, a satellite-rocket separation device includes: the satellite rocket comprises a first connecting body 10 and a second connecting body 20, wherein the first connecting body 10 is connected with a satellite, the second connecting body 20 is connected with a rocket, and the first connecting body 10 and the second connecting body 20 are detachably connected; a locking mechanism 30, wherein the locking mechanism 30 is disposed on the second connecting body 20, the locking mechanism 30 has a locking position and a separation position, the locking mechanism 30 locks the first connecting body 10 on the second connecting body 20 when located at the locking position, and the locking mechanism 30 separates the first connecting body 10 from the second connecting body 20 when located at the separation position; and a driving mechanism connected with the locking mechanism 30 to drive the locking mechanism 30 to move between the locking position and the separation position, wherein the driving mechanism comprises a driving motor 41 and a cam assembly 42, and the driving motor 41 is in driving connection with the cam assembly 42 to control the locking mechanism 30 to move through the cam assembly 42.
The satellite and rocket separation device is mainly applied to controlling the separation of a satellite and a rocket when the satellite and the rocket are separated, specifically, a first connecting body 10 of the rocket separation device is fixed with the satellite, a second connecting body 20 is fixed on the rocket, the satellite is connected with the rocket through the satellite and rocket separation device, when the satellite and the rocket are separated, a driving motor 41 of a driving mechanism works, a cam component 42 is driven to rotate to drive a locking mechanism 30 to move from a locking position to a separation position, the locking mechanism 30 moves to the separation position, so that the first connecting body 10 is separated from the second connecting body 20, at the moment, the first connecting body 10 can be separated from the second connecting body 20 by pushing force far away from the rocket to the satellite, the separation device adopts mechanical structure action to complete the separation of the satellite and the rocket, and compared with an firer separation device, the separation device is more environment-friendly, and compared with electromagnetic separation, the separation device is safer and more reliable, and does not cause interference to other equipment.
The lock mechanism 30 includes: and the jaw assembly is arranged on the second connecting body 20, so that the second connecting body 20 is connected with the first connecting body 10 in a clamping manner through the jaw assembly.
The jaw assembly includes: a plurality of jaws 31, the plurality of jaws 31 being arranged on the second coupling body 20 at intervals to enclose an annular structure, wherein each jaw 31 is retractably arranged in a radial direction of the annular structure to move simultaneously closer to each other to a separated position or simultaneously move away from each other to a locked position.
As shown in fig. 3 and 4, the locking mechanism 30 in this embodiment connects the first connecting body 10 and the second connecting body 20 in a snap-fit manner, specifically, the first connecting body 10 and the second connecting body 20 are both annular structures, a plurality of claws 31 are uniformly distributed on the second connecting body 20 and enclose an annular structure, the claws 31 can move in parallel along a radial direction of the annular structure to contract or one ends of the claws 31 are rotatably connected with the second connecting body 20, and the other ends of the claws 31 are driven by the collar 40 to rotate in a radial direction to contract or rotate outward.
Preferably, the claw 31 is rotatably disposed on the second connecting body 20, and specifically, a rotating shaft and a torsion spring are disposed on the second connecting body 20, the claw 31 is rotatably disposed on the rotating shaft, and the torsion spring gives an outward expanding pushing force to the claw 31, so that the positioning protrusion 311 on the claw 31 is inserted into the positioning hole 11, and the locking mechanism 30 is in the locking position.
The claw 31 is provided with a positioning protrusion 311, the first connecting body 10 is provided with a positioning hole 11, when the locking mechanism 30 moves to the locking position, the positioning protrusion 311 is inserted into the positioning hole 11 to fix the first connecting body 10 and the claw 31 together, and when the locking mechanism 30 moves to the separation position, the positioning protrusion 311 is separated from the positioning hole 11 to separate the first connecting body 10 and the claw 31.
As shown in fig. 4, two positioning protrusions 311 are disposed on the outer side of the clamping jaws 31 in the present embodiment, and two positioning holes 11 are correspondingly disposed on the first connecting body 10 for respectively engaging with the positioning protrusions 311, when the clamping ring 40 is retracted inward, the clamping upper portion is driven to rotate toward the inner side of the annular structure, so that the positioning protrusions 311 are disengaged from the positioning holes 11, and when the clamping ring 40 is tensioned outward, the clamping jaws 31 are driven by the torsion spring to rotate outward, so that the positioning protrusions 311 are inserted into the positioning holes 11, so that the clamping rings 40 and the clamping jaws 31 are fixed together.
The satellite-rocket separation device further comprises: and the clamping ring assembly is connected with the plurality of clamping jaws 31, and the driving mechanism drives the plurality of clamping jaws 31 to move simultaneously through the clamping ring assembly.
The clamping ring assembly comprises a clamping ring 40, the clamping ring 40 is sleeved on the outer side of the jaw assembly, wherein the clamping ring 40 is of an unclosed annular structure, the clamping ring 40 is provided with a first driving end 43 and a second driving end 44, and the driving mechanism simultaneously drives the first driving end 43 and the second driving end 44 to move close to or away from each other so as to drive the jaws 31 to move close to or away from each other simultaneously.
As shown in fig. 6, in this embodiment, an annular collar 40 in a semi-closed state is disposed on the outside of the jaw assembly, when the driving mechanism drives the retainer ring 40 to contract, the clamping jaws 31 are pushed inwards to move, when the retainer ring 40 expands outwards, the clamping jaws 31 move outwards under the action of external force, specifically, the locking block 51 is fixed at one end of the sliding block assembly through a bolt or stopped at one end of the sliding rail assembly 52 through a stopping block, at the moment, the retainer ring 40 is in a tensioning state, the positioning protrusions 311 on the clamping jaws 31 are inserted into the positioning holes 11, when the star and arrow are separated, the first driving end 43 and the second driving end 44 of the retainer ring 40 contract inwards under the action of the self-elasticity to drive the locking block 51 to move along the slide rail assembly 52, at the moment, each claw 31 rotates inwards, so that the positioning protrusion 311 is separated from the positioning hole 11, the first coupling body 10 is then moved upward to be separated from the second coupling body 20 by the urging of the spring 60.
Satellite-rocket separator still includes slider mechanism, and slider mechanism sets up on second connector 20, and wherein, slider mechanism includes:
the slide rail component 52, the slide rail component 52 is arranged on the second connecting body 20; the locking block 51 is movably arranged on the slide rail assembly 52 and is simultaneously in driving connection with the first driving end 43 and the second driving end 44; the driving mechanism is drivingly connected to the locking block 51, and the locking block 51 has a first position and a second position, so as to drive the first driving end 43 and the second driving end 44 to approach each other when the locking block 51 moves to the first position, and drive the first driving end 43 and the second driving end 44 to move away from each other when the locking block 51 moves to the second position.
As shown in fig. 3, in the present embodiment, the slide rail assembly 52 includes a linear slide rail, the linear slide rail extends along a radial direction of the annular structure, the linear slide rail is mounted on the second connecting body 20 through a bolt, a locking block 51 is disposed on the linear slide rail to move the plug cover along the linear slide rail, the elastic pin is mounted on the plug cover, the stopper is mounted on the linear guide rail, the locking block 51 is a wedge-shaped block, the locking block 51 is mounted on the stopper, the locking block 51 is connected to the first driving end 43 and the second driving end 44 respectively, the locking block 51 moves inward along the linear slide rail, and the first driving end 43 and the second driving end 44 are close to each other to enable the collar 40 to retract; the locking block 51 moves outwardly along the linear slide and the first and second actuating ends 43, 44 move away from each other to tighten the collar 40.
The satellite-rocket separation device further comprises: and the ejection mechanism is arranged on the second connecting body 20 and is in driving connection with the first connecting body 10 so as to drive the first connecting body 10 to be separated from the second connecting body 20 when the locking mechanism 30 moves to the separation position.
The ejection mechanism includes: a plurality of springs 60, the plurality of springs 60 being uniformly distributed on the second connecting body 20 to be respectively connected with different positions of the first connecting body 10, wherein each spring 60 is respectively in a compressed state to push the first connecting body 10 to move when the locking mechanism 30 moves to the separated position.
When the locking mechanism 30 moves to the separation position, an external force is needed to push the first connecting body 10 away from the second connecting body 20, in this embodiment, a circle of guide posts are arranged on the second connecting body 20, the spring 60 is sleeved on the guide posts to ensure that the spring 60 always moves along the vertical direction, when the locking mechanism 30 is in the locking position, the first connecting body 10 and the second connecting body 20 are locked together, the spring 60 is in a compression state, and when the locking mechanism 30 is in the separation position, the spring 60 pushes the first connecting body 10 and the second connecting body 20 upwards to separate. In order to ensure the satellite attitude after separation to be stable, the springs 60 are uniformly distributed.
In addition, as shown in fig. 7, the cam mechanism includes a first locking block structure 45, a cam and a second locking block structure 46, and the driving motor 41 pushes the stopper to move through the cam mechanism to lock the locking block 51 or move the locking block 51 along the linear slide.
The satellite and rocket separation device also reserves the installation positions of the satellite and rocket separation switch, and the satellite separation switch and the satellite sensor plug are installed on the first connecting body. The rocket disconnecting switch and the satellite sensor socket are arranged on the second connecting body, and the satellite sensor socket and the satellite sensor plug can customize a communication interface according to needs.
From the above description, it can be seen that the above-described embodiments of the present invention achieve the following technical effects:
the satellite and rocket separation device is mainly applied to controlling the separation of a satellite and a rocket when the satellite and the rocket are separated, specifically, a first connecting body 10 of the rocket separation device is fixed with the satellite, a second connecting body 20 is fixed on the rocket, the satellite is connected with the rocket through the satellite and rocket separation device, when the satellite and the rocket are separated, a driving motor 41 of a driving mechanism works, a cam component 42 is driven to rotate to drive a locking mechanism 30 to move from a locking position to a separation position, the locking mechanism 30 moves to the separation position, so that the first connecting body 10 is separated from the second connecting body 20, at the moment, the first connecting body 10 can be separated from the second connecting body 20 by pushing force far away from the rocket to the satellite, the separation device adopts mechanical structure action to complete the separation of the satellite and the rocket, and compared with an firer separation device, the separation device is more environment-friendly, and compared with electromagnetic separation, the separation device is safer and more reliable, and does not cause interference to other equipment.
It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of example embodiments according to the present application. As used herein, the singular forms "a", "an" and "the" are intended to include the plural forms as well, and it should be understood that when the terms "comprises" and/or "comprising" are used in this specification, they specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof, unless the context clearly indicates otherwise.
The relative arrangement of the components and steps, the numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present invention unless specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective portions shown in the drawings are not drawn in an actual proportional relationship for the convenience of description. Techniques, methods, and apparatus known to those of ordinary skill in the relevant art may not be discussed in detail, but are intended to be part of the specification where appropriate. In all examples shown and discussed herein, any particular value should be construed as merely illustrative, and not limiting. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, further discussion thereof is not required in subsequent figures.
In the description of the present invention, it is to be understood that the orientation or positional relationship indicated by the orientation words such as "front, rear, upper, lower, left, right", "lateral, vertical, horizontal" and "top, bottom", etc. are usually based on the orientation or positional relationship shown in the drawings, and are only for convenience of description and simplicity of description, and in the case of not making a reverse description, these orientation words do not indicate and imply that the device or element being referred to must have a specific orientation or be constructed and operated in a specific orientation, and therefore, should not be considered as limiting the scope of the present invention; the terms "inner and outer" refer to the inner and outer relative to the profile of the respective component itself.
Spatially relative terms, such as "above … …," "above … …," "above … …," "above," and the like, may be used herein for ease of description to describe one device or feature's spatial relationship to another device or feature as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures. For example, if a device in the figures is turned over, devices described as "above" or "on" other devices or configurations would then be oriented "below" or "under" the other devices or configurations. Thus, the exemplary term "above … …" can include both an orientation of "above … …" and "below … …". The device may be otherwise variously oriented (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.
It should be noted that the terms "first", "second", and the like are used to define the components, and are only used for convenience of distinguishing the corresponding components, and the terms have no special meanings unless otherwise stated, and therefore, the scope of the present invention should not be construed as being limited.
The above is only a preferred embodiment of the present invention, and is not intended to limit the present invention, and various modifications and changes will occur to those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (9)
1. A satellite-rocket separation device is characterized by comprising:
a first connection body (10) and a second connection body (20), wherein the first connection body (10) is connected with a satellite, the second connection body (20) is connected with a rocket, and the first connection body (10) and the second connection body (20) are detachably connected;
a locking mechanism (30), wherein the locking mechanism (30) is disposed on the second connecting body (20), wherein the locking mechanism (30) has a locking position and a disengagement position, the locking mechanism (30) in the locking position locks the first connecting body (10) to the second connecting body (20), and the locking mechanism (30) in the disengagement position disengages the first connecting body (10) from the second connecting body (20);
the driving mechanism is connected with the locking mechanism (30) to drive the locking mechanism (30) to move between the locking position and the separation position, wherein the driving mechanism comprises a driving motor (41) and a cam assembly (42), and the driving motor (41) is in driving connection with the cam assembly (42) to control the locking mechanism (30) to move through the cam assembly (42).
2. The star-arrow separation device according to claim 1, characterized in that the locking mechanism (30) comprises:
and the jaw assembly is arranged on the second connecting body (20) so that the second connecting body (20) is connected with the first connecting body (10) in a clamping manner through the jaw assembly.
3. The satellite-rocket separation device of claim 2, wherein the jaw assembly comprises:
a plurality of jaws (31), a plurality of the jaws (31) being arranged on the second coupling body (20) at intervals so as to enclose an annular structure, wherein each of the jaws (31) is arranged contractibly in a radial direction of the annular structure so as to be moved simultaneously closer to each other to the separated position or simultaneously moved away from each other to the locked position.
4. The star-arrow separation device according to claim 3, wherein the claw (31) is provided with a positioning protrusion (311), the first connecting body (10) is provided with a positioning hole (11), when the locking mechanism (30) moves to the locking position, the positioning protrusion (311) is inserted into the positioning hole (11) to fix the first connecting body (10) and the claw (31) together, and when the locking mechanism (30) moves to the separation position, the positioning protrusion (311) is disengaged from the positioning hole (11) to separate the first connecting body (10) and the claw (31).
5. The satellite-rocket separation device according to claim 3, further comprising:
the clamping ring assembly is connected with the plurality of clamping jaws (31), and the driving mechanism drives the plurality of clamping jaws (31) to move simultaneously through the clamping ring assembly.
6. The star-arrow separation device according to claim 5, characterized in that the collar assembly comprises a collar (40), the collar (40) is sleeved outside the jaw assembly, wherein the collar (40) is an unclosed annular structure, the collar (40) is provided with a first driving end (43) and a second driving end (44), and the driving mechanism simultaneously drives the first driving end (43) and the second driving end (44) to move close to or away from each other so as to drive the jaws (31) to move close to or away from each other simultaneously.
7. The star-arrow separation device according to claim 6, further comprising a slider mechanism disposed on the second connecting body (20), wherein the slider mechanism comprises:
a slide rail assembly (52), the slide rail assembly (52) being disposed on the second connecting body (20);
the locking block (51) is movably arranged on the slide rail component (52) and is simultaneously in driving connection with the first driving end (43) and the second driving end (44);
the driving mechanism is in driving connection with the locking block (51), the locking block (51) is provided with a first position and a second position, so that the first driving end (43) and the second driving end (44) are driven to be close to each other when the locking block (51) moves to the first position, and the first driving end (43) and the second driving end (44) are driven to be away from each other when the locking block (51) moves to the second position.
8. The satellite-rocket separation device according to claim 1, further comprising:
the ejection mechanism is arranged on the second connecting body (20) and is in driving connection with the first connecting body (10) so as to drive the first connecting body (10) to be separated from the second connecting body (20) when the locking mechanism (30) moves to the separation position.
9. The satellite-rocket separation device according to claim 8, wherein the ejection mechanism comprises:
a plurality of springs (60), the plurality of springs (60) being uniformly distributed on the second connecting body (20) to be respectively connected with different positions of the first connecting body (10), wherein each spring (60) is respectively in a compressed state to push the first connecting body (10) to move when the locking mechanism (30) moves to the separated position.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110236898.2A CN113998152B (en) | 2021-03-03 | 2021-03-03 | Satellite-rocket separation device |
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|---|---|---|---|
| CN202110236898.2A CN113998152B (en) | 2021-03-03 | 2021-03-03 | Satellite-rocket separation device |
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| CN113998152B CN113998152B (en) | 2025-05-27 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114435633A (en) * | 2022-02-22 | 2022-05-06 | 江苏深蓝航天有限公司 | Interstage separation device, rocket and separation method |
| CN116147431A (en) * | 2023-02-13 | 2023-05-23 | 航天科工空间工程发展有限公司 | a driving device |
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| CN107826271A (en) * | 2017-12-07 | 2018-03-23 | 上海宇航系统工程研究所 | Jack catchs type satellite and the rocket connection separation mechanism |
| CN110356593A (en) * | 2019-07-12 | 2019-10-22 | 北京卫星制造厂有限公司 | A kind of repeatable locking separation device |
| CN214608150U (en) * | 2021-03-03 | 2021-11-05 | 东方空间技术(山东)有限公司 | Star and arrow separating device |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114435633A (en) * | 2022-02-22 | 2022-05-06 | 江苏深蓝航天有限公司 | Interstage separation device, rocket and separation method |
| CN116147431A (en) * | 2023-02-13 | 2023-05-23 | 航天科工空间工程发展有限公司 | a driving device |
| CN116147431B (en) * | 2023-02-13 | 2025-07-11 | 航天科工空间工程发展有限公司 | A driving device |
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