CN113665844B - Satellite and rocket unlocking device for separating stacked satellites from carrying satellites - Google Patents
Satellite and rocket unlocking device for separating stacked satellites from carrying satellites Download PDFInfo
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- CN113665844B CN113665844B CN202111064118.7A CN202111064118A CN113665844B CN 113665844 B CN113665844 B CN 113665844B CN 202111064118 A CN202111064118 A CN 202111064118A CN 113665844 B CN113665844 B CN 113665844B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
- B64G1/1085—Swarms and constellations
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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
- B64G1/641—Interstage or payload connectors
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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
Abstract
The utility model provides a satellite and rocket unlocking device for separating stacked satellites from carrying, which belongs to the technical field of space satellites and comprises a satellite and rocket connecting ring, a swinging rod and a plurality of satellite layers, wherein the satellite layers are stacked on the satellite and rocket connecting ring; the satellite-rocket connecting ring is provided with a pin structure through a reserved pin hole, one end of the swing rod is hinged with the pin structure, and the other end of the swing rod is provided with an unlocking component; when the satellite layers are stacked in a compressed state, the swing rods are closely attached to the side walls of the satellite layers, the multiple satellite layers are connected with the adapter through the unlocking piece to keep the compressed state, and the compression seat and the uppermost satellite layer are mutually compressed; when the satellite layers are converted into the loose state and stacked, the unlocking piece is disconnected with the adapter, the compressing seat is released from being compressed with the satellite layers, and the swing rod rotates around the axis of the pin structure in the direction away from the satellite stack. The utility model reduces the overall centroid height of the satellite group, improves the circumference utilization rate of the carrying fairing, reduces the unlocking risk of the stacked satellite layers, and improves the unlocking efficiency and the design reliability.
Description
Technical Field
The utility model relates to the technical field of space satellites, in particular to a satellite and rocket unlocking device for separating stacked satellites from carriers.
Background
Aiming at the defects of limited coverage of a ground network, easiness in influence of natural environment and the like, satellite communication can effectively solve the Internet service problems of users at remote locations, offshore, air and the like. In recent years, the countries such as the united states and canada sequentially propose global low-orbit internet constellation plans, and the technology hot trend of the internet satellite constellation is raised. In order to enhance the competitiveness of China in the field, further consolidate and improve the future international influence, the low-orbit satellite constellation construction work of China is also developed. The conventional satellite transmitting connection and disconnection design has the following disadvantages: 1. each satellite needs to be designed with an independent connection and separation structure and initiating explosive devices, and the structure is complex, so that batch production is not facilitated; 2. the separation process is complex, and is not beneficial to constellation control of satellites in orbit.
According to the technical search, the Chinese patent publication No. CN2897825 discloses a satellite and rocket unlocking and separating bag loading device, which comprises a manual hydraulic pump, a distributor, a one-way load valve and an oil cylinder, wherein the manual hydraulic pump is connected to the distributor through a pipeline, the distributor divides the pipeline into a plurality of branches, each branch is connected with the one-way load valve, the output of the one-way load valve is connected to a fastening spring of the oil cylinder, a pressure gauge is connected between the manual hydraulic pump and the distributor, and an adjusting valve is connected to each branch and used for adjusting the pressure of the branch. However, the above patent suffers from the following disadvantages: the patent designs a pretightening force loading device aiming at a traditional belted type satellite and arrow unlocking structure, can ensure uniform synchronous loading pretightening force, is not applicable to stacked satellites with structural configuration, and is difficult to meet special requirements on compaction, unlocking and separation of multi-layer satellites.
According to the technical search, the Chinese patent publication number is CN112373734A, a low-orbit satellite group wholesale launching satellite-rocket separation unlocking module and a satellite-rocket separation method are disclosed, a plurality of satellites are stacked on a rocket carrier, the bottommost one satellite is connected with the carrier through a satellite-rocket connection mechanism, the satellite-rocket separation unlocking module comprises a plurality of groups of connection and separation devices fixedly arranged on the rocket carrier, each group of connection and separation devices comprises two pull rods which are connected with the carrier and extend along the stacking direction of the satellites, a first initiating explosive device is arranged at the joint of each pull rod and the carrier, the tail ends of the two pull rods are commonly connected with a pressing plate positioned outside the tail end satellite, and a pressure-bearing body is pressed between the pressing plate and the tail end satellite. However, the above patent suffers from the following disadvantages: through the use of the bearing body, the overall mass center height of the satellite group cannot be reduced.
Through prior art search, the publication: international space, 453 th period, "energy-adjustable miniaturized satellite and rocket spring separation device". The article designs a satellite-arrow spring separation device applicable to one arrow and multiple satellites, and the satellite separation posture can be adjusted by adjusting the spring travel, but the following defects exist in the technology: the dependence on a central bearing structure cannot be avoided under the condition that the number of satellites is larger, so that the overall mass center height of the satellite group is higher, and the upper limit value of the number of satellites launched by one arrow and multiple satellites is limited.
Because the structural form of the stacked satellites is very different from that of the conventional satellites, if the conventional satellite rocket unlocking device is used, the stable connection requirement of the launching stage and the unlocking separation requirement of the in-orbit stage are hardly met. Therefore, a satellite unlocking device for stacking satellites and carrying and separating satellites is provided.
Disclosure of Invention
Aiming at the defects in the prior art, the utility model aims to provide a satellite and rocket unlocking device for separating stacked satellites from carriers.
The utility model provides a satellite and rocket unlocking device for stacking satellites and carrying and separating the satellites, which comprises a satellite and rocket connecting ring, a satellite layer and a swinging rod;
the satellite layers are provided with a plurality of layers, and the plurality of layers of satellite layers are stacked on the satellite-rocket connecting ring;
the satellite-rocket connecting ring is provided with a pin structure through a reserved pin hole, one end of the swing rod is hinged with the pin structure, and the other end of the swing rod is provided with an unlocking component;
the unlocking component comprises an adapter, a pressing seat and an unlocking piece, wherein the adapter is connected to the swing rod, the unlocking piece is arranged at the other end of the adapter, and the adapter penetrates through the pressing seat;
when the satellite layers are stacked in a compressed state, the swing rods are tightly attached to the side walls of the satellite layers, a plurality of layers of the satellite layers are connected with the adapter through unlocking pieces to keep the compressed state, and the compression seat and the uppermost satellite layer are mutually compressed;
when the satellite layers are converted into the loose state and stacked, the unlocking piece is disconnected with the adapter, the pressing seat is released from being pressed with the satellite layers, and the swing rod rotates around the axis of the pin structure in a direction away from the satellite stack.
In some embodiments, the unlocking assembly further comprises an elastic piece and a sleeve, the sleeve penetrates through the compression seat, the adapter penetrates through the sleeve, the elastic piece is sleeved on the adapter, and the elastic piece is arranged between the adapter and the sleeve.
In some embodiments, the end of the swing rod is provided with a connecting end, the connecting end is connected with a rod piece at the upper part of the swing rod through a torsion-proof pin, the connecting end is provided with an opening, and the connecting end is hinged with the pin structure through the opening corresponding to the reserved pin hole of the satellite and arrow connecting ring.
In some embodiments, the unlocking piece adopts an initiating explosive device, and the elastic piece adopts a spring.
In some embodiments, the compressing seat is provided with a cold air injection thrust mechanism, and the cold air injection thrust mechanism is arranged corresponding to the upper end surface of the swing rod.
In some embodiments, the number of the pressing seats is four, the pressing seats are circumferentially arranged corresponding to the satellite and rocket connecting rings, in each pressing seat, two groups of unlocking assemblies are arranged, and the two groups of unlocking assemblies are symmetrically arranged in the pressing seats.
In some embodiments, the swing rod adopts a titanium alloy round rod, the outer diameter of the swing rod is 35mm, the thickness of the wall of the swing rod is 5mm, the length of the swing rod is 3000mm, the connecting end adopts a water drop-shaped structure, the thickness of the connecting end is 50mm, and the diameter of the opening is a pin hole of 40mm.
In some embodiments, the star arrow connecting ring is provided with pin hole interfaces, the pin hole interfaces are provided with eight groups, the pin structures are provided with eight pin hole interfaces, eight pin structures are circumferentially arranged on the star arrow connecting ring corresponding to the pin hole interfaces, the diameter of the pin hole interfaces is 40mm, and the diameter of the pin structures is 40mm.
In some embodiments, 5-30 satellite layers are stacked on the satellite-rocket connection ring.
In some embodiments, when a plurality of satellite layers are stacked on the satellite-rocket connection ring, the swing rod is attached to a plurality of satellite layers, the compression seat is arranged corresponding to the uppermost satellite layer, and a pre-tightening force is applied to the compression seat, so that an elastic piece in the compression seat is in a compressed state to keep the compression seat to compress the satellite layers;
the unlocking component is used for unlocking after the satellite stably spins in orbit, the unlocking component is disconnected with the transfer joint of the unlocking component, the unlocking component moves along the axial direction of the elastic component through the deformation recovery of the elastic component, the compressing seat is used for releasing the compressing setting of the satellite layer, the cold air injection thrust mechanism on the compressing seat works to push the compressing seat and the swing rod to rotate around the axis of the pin structure in the direction away from the satellite layer, and the satellite layer is separated from the satellite-rocket connecting ring in an unlocking mode.
Compared with the prior art, the utility model has the following beneficial effects:
1. according to the utility model, the swing rod is arranged, the compression seat is arranged on the swing rod, the multi-layer satellite layer is kept in a compressed state by applying the pre-tightening force by the compression seat and is arranged on the satellite-rocket connecting ring, so that the overall mass center height of the satellite group is reduced, and the circumference utilization rate of the carrying fairing is improved;
2. according to the utility model, the unlocking component is arranged, the adapter, the elastic piece and the unlocking piece are arranged, so that the compressing seat can be compressed on the satellite layer, the compressing seat can be used for decompressing the satellite layer, the design is simplified, the risk of unlocking the stacked satellite layers is reduced, and the unlocking efficiency and the reliability of the design are improved;
3. according to the utility model, the initiating explosive device is adopted as the unlocking piece, the swing rod is hinged with the satellite and rocket connecting rod through the pin structure, after the unlocking piece is unlocked, the unlocking component still keeps connection with the swing rod, and after the swing rod swings outwards, the unlocking component still keeps connection with the satellite and rocket connecting ring, so that the generation of space garbage is avoided, and the pollution to the space environment is reduced.
Drawings
Other features, objects and advantages of the present utility model will become more apparent upon reading of the detailed description of non-limiting embodiments, given with reference to the accompanying drawings in which:
FIG. 1 is a first view of a stacked satellite and carrier separated satellite-rocket unlocking device in a collapsed state prior to unlocking;
FIG. 2 is a second view of the stacked satellites and the satellite-rocket unlocking device for carrying and separating the stacked satellites after unlocking;
FIG. 3 is a diagram showing the outward swing of the stacked satellites and the carrier separated satellite rocket unlocking device after unlocking;
FIG. 4 is a schematic diagram of the structure of the swing link and unlocking assembly of the satellite-rocket unlocking device for stacking satellites and carrying and separating satellites;
FIG. 5 is a partial schematic view of a pendulum rod and unlocking assembly of the satellite-rocket unlocking device for stacking satellites and carrying and separating satellites according to the present utility model;
FIG. 6 is a schematic cross-sectional view of an unlocking assembly of the satellite-rocket unlocking device for stacking satellites and carrying and separating satellites according to the present utility model;
FIG. 7 is a pivotal view of the stacked satellites and carrier separated satellites of the utility model prior to unlocking;
FIG. 8 is a pivotal view of the stacked satellites and the carrier separated satellite unlocking device according to the present utility model after unlocking.
Reference numerals:
Detailed Description
The present utility model will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the present utility model, but are not intended to limit the utility model in any way. It should be noted that variations and modifications could be made by those skilled in the art without departing from the inventive concept. These are all within the scope of the present utility model.
Fig. 1 is a drawing-in state diagram one before unlocking a satellite unlocking device for separating a stacked satellite from a carrier, fig. 2 is a drawing-in state diagram two after unlocking the satellite unlocking device for separating the stacked satellite from the carrier, and fig. 3 is a swinging-out state diagram after unlocking the satellite unlocking device for separating the stacked satellite from the carrier, wherein the swinging-out state diagram comprises a satellite-arrow connecting ring 1, a satellite layer 2 and a swinging rod 3, the satellite layer 2 is provided with multiple layers, and the multiple layers of satellite layers 2 are stacked on the satellite-arrow connecting ring 1. In this embodiment, 5-30 satellite layers 2 are stacked on the satellite-rocket connection ring 1.
Fig. 7 shows a pivot diagram before unlocking in a satellite unlocking device for stacking satellites and carrying and separating satellites, fig. 8 shows a pivot diagram after unlocking in a satellite unlocking device for stacking satellites and carrying and separating satellites, a pin structure 5 is arranged on a satellite connecting ring 1 through a reserved pin hole, one end of a swinging rod 3 is hinged with the pin structure 5, and an unlocking component 4 is arranged at the other end of the swinging rod 3. In this embodiment, the end of the swing rod 3 is provided with a connection end 11, the connection end 11 is connected with a part of rod piece on the swing rod 3 through a torsion-proof pin 12, an opening is provided on the connection end 11, and the connection end 11 is hinged with the pin structure 5 through the opening corresponding to the reserved pin hole of the satellite and rocket connection ring 1.
When the satellite layers 2 are stacked in a compressed state, the swinging rods 3 are tightly attached to the side walls of the satellite layers 2, the multi-layer satellite layers 2 are connected with the adapter 7 through the unlocking piece 10 to be in a compressed state, and the compression seat 6 and the uppermost satellite layer 2 are mutually compressed. When the satellite layers 2 are stacked in a loose state, the unlocking piece 10 is disconnected with the adapter 7, the pressing seat 6 is not pressed with the satellite layers 2, and the swinging rod 3 rotates around the axis of the pin structure 5 in a direction away from the satellite stack.
Fig. 4 is a schematic structural view of the swing rod 3 and the unlocking component 4 in the satellite and carrier separated satellite unlocking device, fig. 5 is a partial schematic view of the swing rod 3 and the unlocking component 4 in the satellite and carrier separated satellite unlocking device, and fig. 6 is a schematic sectional view of the unlocking component 4 in the satellite and carrier separated satellite unlocking device, the unlocking component 4 comprises an adapter 7, a pressing seat 6 and an unlocking piece 10, the adapter 7 is connected and arranged on the swing rod 3, the unlocking piece 10 is arranged at the other end of the adapter 7, and the adapter 7 penetrates through the pressing seat 6. The unlocking component 4 further comprises an elastic piece 8 and a sleeve 9, the sleeve 9 penetrates through the pressing seat 6, the adapter 7 penetrates through the sleeve 9, the elastic piece 8 is sleeved on the adapter 7, and the elastic piece 8 is arranged between the adapter 7 and the sleeve 9. In this embodiment, the unlocking member 10 is a initiating explosive device, and the elastic member 8 is a spring.
In this embodiment, four compressing seats 6 are provided, the compressing seats 6 are circumferentially arranged corresponding to the satellite arrow connecting ring 1, in each compressing seat, two groups of unlocking assemblies 4 are provided, and the two groups of unlocking assemblies 4 are symmetrically arranged in the compressing seats 6. The compressing seat 6 is provided with a cold air injection thrust mechanism which is arranged corresponding to the upper end face of the swing rod 3.
The swing rod 3 adopts a titanium alloy round rod, the outer diameter of the swing rod 3 is 35mm, the thickness of the rod wall of the swing rod 3 is 5mm, the length of the swing rod 3 is 3000mm, the connecting end 11 is arranged in a drop-shaped structure, the thickness of the connecting end 11 is 50mm, and the diameter of the open hole is a pin hole of 40mm. The star arrow connecting ring 1 is provided with pin hole interfaces, the pin hole interfaces are provided with eight groups, the pin structures 5 are provided with eight groups, the eight pin structures 5 are circumferentially arranged on the star arrow connecting ring 1 corresponding to the pin hole interfaces, the diameter of the pin hole interfaces is 40mm, the diameter of the pin structures 5 is 40mm, and smooth outward swinging of the swinging rod 3 is ensured through design dimensional tolerance.
Working principle: when a plurality of satellite layers 2 are stacked on the satellite-rocket connecting ring 1, the swinging rod 3 is attached to the plurality of satellite layers 2, the pressing seat 6 is arranged corresponding to the uppermost satellite layer 2, and a pre-tightening force is applied to the pressing seat 6, so that an elastic piece 8 in the pressing seat 6 is in a compressed state to keep the pressing seat 6 to press the satellite layers 2;
unlocking piece 10 in unlocking component 4 carries out the unblock after the satellite is in orbit stable spin, and unlocking piece 10 disconnection and unlocking component 4 in adapter 7's connection, and unlocking component 4 resumes deformation through elastic component 8 and remove along the axial direction of elastic component 8, compresses tightly seat 6 and releases the setting of compressing tightly to satellite layer 2, compresses tightly the work of the cold jet thrust mechanism on the seat 6, promotes to compress tightly seat 6 and pendulum rod 3 and rotate to the direction of keeping away from satellite layer 2 around the axis of round pin structure 5, satellite layer 2 and satellite rocket go-between 1 unblock separation.
In the description of the present utility model, it should be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are merely for convenience in describing the present utility model and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present utility model.
The foregoing describes specific embodiments of the present utility model. It is to be understood that the utility model is not limited to the particular embodiments described above, and that various changes or modifications may be made by those skilled in the art within the scope of the appended claims without affecting the spirit of the utility model. The embodiments of the utility model and the features of the embodiments may be combined with each other arbitrarily without conflict.
Claims (6)
1. The satellite and rocket unlocking device for stacking satellites and carrying and separating the satellites is characterized by comprising a satellite and rocket connecting ring (1), a satellite layer (2) and a swinging rod (3);
the satellite layers (2) are provided with multiple layers, and the multiple layers of satellite layers (2) are stacked on the satellite-rocket connecting ring (1);
the satellite and rocket connecting ring (1) is provided with a pin structure (5) through a reserved pin hole, one end of the swing rod (3) is hinged with the pin structure (5), and the other end of the swing rod (3) is provided with an unlocking component (4);
the unlocking component (4) comprises an adapter (7), a pressing seat (6) and an unlocking piece (10), wherein the adapter (7) is connected to the swing rod (3), the unlocking piece (10) is arranged at the other end of the adapter (7), and the adapter (7) penetrates through the pressing seat (6);
when the satellite layers (2) are stacked in a compressed state, the swinging rods (3) are tightly attached to the side walls of the satellite layers (2), a plurality of layers of the satellite layers (2) are connected with the adapter (7) through the unlocking piece (10) to keep the compressed state, and the compression seat (6) and the uppermost layer of the satellite layers (2) are mutually compressed;
when the satellite layers (2) are stacked in a loose state, the unlocking piece (10) is disconnected with the adapter (7), the pressing seat (6) is not pressed with the satellite layers (2), and the swinging rod (3) rotates around the axis of the pin structure (5) in a direction away from the satellite layers (2);
the unlocking assembly (4) further comprises an elastic piece (8) and a sleeve (9), the sleeve (9) penetrates through the pressing seat (6), the adapter (7) penetrates through the sleeve (9), the elastic piece (8) is sleeved on the adapter (7), and the elastic piece (8) is arranged between the adapter (7) and the sleeve (9);
the four compressing seats (6) are arranged, the compressing seats (6) are circumferentially arranged corresponding to the satellite and rocket connecting rings (1), in each compressing seat (6), two groups of unlocking assemblies (4) are arranged, and the two groups of unlocking assemblies (4) are symmetrically arranged in the compressing seats (6);
the satellite and rocket connecting ring (1) is provided with pin hole interfaces, eight groups of pin hole interfaces are arranged, eight pin structures (5) are circumferentially arranged on the satellite and rocket connecting ring (1) corresponding to the pin hole interfaces, the diameter of each pin hole interface is 40mm, and the diameter of each pin structure (5) is 40mm;
when a plurality of satellite layers (2) are stacked on the satellite-rocket connecting ring (1), the swinging rods (3) are attached to the plurality of satellite layers (2), the compaction seat (6) is arranged corresponding to the uppermost satellite layer (2), and a pretightening force is applied to the compaction seat (6), so that an elastic piece (8) in the compaction seat (6) is in a compressed state to keep the compaction seat (6) to compact the satellite layer (2);
unlocking piece (10) among unlocking component (4) is in the stable back of spinning of satellite on orbit and is unlocked, unlocking piece (10) disconnection with the connection of joint (7) in unlocking component (4), unlocking component (4) are passed through elastic component (8) resume deformation and follow the axial direction of elastic component (8) removes, compress tightly seat (6) and are released to satellite layer (2) compress tightly the setting, compress tightly cold jet thrust mechanism work on seat (6), promote compress tightly seat (6) with pendulum rod (3) are around the axis of round pin structure (5) is to keeping away from satellite layer (2) direction rotates, satellite layer (2) with satellite arrow go-between (1) unblock separation.
2. The satellite and rocket unlocking device for stacking satellites and carrying and separating satellites according to claim 1, wherein a connecting end (11) is arranged at the end part of the swinging rod (3), the connecting end (11) is connected with a rod piece at the upper part of the swinging rod (3) through a torsion-proof pin (12), an opening is arranged on the connecting end (11), and the connecting end (11) is hinged with the pin structure (5) through the opening corresponding to a reserved pin hole of the satellite and rocket connecting ring (1).
3. The satellite and rocket unlocking device for stacking satellites and carrying and separating satellites according to claim 1 is characterized in that the unlocking piece (10) adopts an initiating explosive device and the elastic piece (8) adopts a spring.
4. The satellite and rocket unlocking device for stacking satellites and carrying and separating satellites according to claim 1 is characterized in that a cold air injection thrust mechanism is arranged on the pressing seat (6), and the cold air injection thrust mechanism is arranged corresponding to the upper end face of the swinging rod (3).
5. The satellite and rocket unlocking device for stacking satellites and carrying and separating satellites according to claim 2, wherein the swinging rod (3) is a titanium alloy round rod, the outer diameter of the swinging rod (3) is 35mm, the thickness of the rod wall of the swinging rod (3) is 5mm, the length of the swinging rod (3) is 3000mm, the connecting end (11) is arranged in a water-drop-shaped structure, the thickness of the connecting end (11) is 50mm, and the diameter of the opening is a pin hole of 40mm.
6. The satellite-rocket unlocking device for separating stacked satellites from carriers according to claim 1, wherein 5-30 layers of the satellite layers (2) are stacked on the satellite-rocket connecting ring (1).
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| CN202111064118.7A CN113665844B (en) | 2021-09-10 | 2021-09-10 | Satellite and rocket unlocking device for separating stacked satellites from carrying satellites |
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| CN202111064118.7A CN113665844B (en) | 2021-09-10 | 2021-09-10 | Satellite and rocket unlocking device for separating stacked satellites from carrying satellites |
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| CN113665844A CN113665844A (en) | 2021-11-19 |
| CN113665844B true CN113665844B (en) | 2023-09-19 |
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| CN113955156A (en) * | 2021-11-26 | 2022-01-21 | 长光卫星技术有限公司 | Satellite and rocket connecting device of stacked satellite |
| CN114353603B (en) * | 2022-01-13 | 2023-11-14 | 北京中科宇航技术有限公司 | Non-initiating explosive device satellite and rocket separation unlocking device |
| CN114537710A (en) * | 2022-01-18 | 2022-05-27 | 上海卫星工程研究所 | Flexible solar cell array pressing device, working method and satellite |
| CN115009549B (en) * | 2022-08-09 | 2022-11-18 | 北京星河动力装备科技有限公司 | Locking and releasing mechanism, control method thereof and carrier rocket |
| CN115231004B (en) * | 2022-09-20 | 2023-01-24 | 北京宇航系统工程研究所 | Connection and separation mechanism for stacked satellites |
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