CN113665844A - Satellite and rocket unlocking device for separating stacked satellites from carrier - Google Patents
Satellite and rocket unlocking device for separating stacked satellites from carrier Download PDFInfo
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- CN113665844A CN113665844A CN202111064118.7A CN202111064118A CN113665844A CN 113665844 A CN113665844 A CN 113665844A CN 202111064118 A CN202111064118 A CN 202111064118A CN 113665844 A CN113665844 A CN 113665844A
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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
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Abstract
The invention provides a satellite and rocket unlocking device for separating stacked satellites from carrying, which belongs to the technical field of space satellites and comprises satellite and rocket connecting rings, a swing rod and a plurality of satellite layers, wherein the satellite layers are stacked on the satellite and rocket connecting rings; a pin structure is arranged on the satellite-rocket connecting ring through a reserved pin hole, one end of the swing rod is hinged with the pin structure, and an unlocking assembly is arranged at the other end of the swing rod; when the satellite layers are stacked in a compressed state, the swing rod is arranged close to the side wall of the satellite layer, the multiple layers of satellite layers are mutually connected with the adapter through the unlocking piece to be in a compressed state, and the compression seat and the satellite layer on the uppermost layer are mutually compressed; when the satellite layer is converted to be stacked in a loose state, the unlocking piece is disconnected from the adapter, the pressing seat is released from being tightly pressed with the satellite layer, and the swing rod rotates around the axis of the pin structure in the direction far away from the satellite stack. The invention reduces the height of the integral mass center of the satellite group, improves the circumferential 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 invention relates to the technical field of space satellites, in particular to a satellite and rocket unlocking device for separating stacked satellites from carrying.
Background
Aiming at the defects that the ground network coverage is limited, the influence of natural environment is easy to influence and the like, the satellite communication can effectively solve the problem of internet service of users in remote areas, on the sea, in the air and the like. In recent years, countries such as the united states and canada have successively proposed global low-earth-orbit internet constellation plans, and the technical trend of internet satellite constellations has been raised. In order to enhance the competitiveness of China in the field and further consolidate and improve the future international influence, the low-orbit satellite constellation construction work of China is also continuously developed. The traditional satellite transmission connection separation mode design has the following defects: 1. each satellite needs to be designed with an independent connection and separation structure and initiating explosive devices, and the structure is complex and is not beneficial to batch production; 2. the separation process is complex, which is not beneficial to the constellation control of the satellite in orbit.
Found through prior art retrieval, chinese utility model patent publication No. CN2897825 discloses a star and arrow unblock separation band loading device includes manual hydraulic pump, distributor, one-way load valve, hydro-cylinder, and manual hydraulic pump connects to the distributor through the pipeline, and the distributor divides into a plurality of branch road with the pipeline, has all connect one-way load valve in every branch road, and the output of one-way load valve connects to the fastening spring of hydro-cylinder it has connect the manometer to connect between manual hydraulic pump and the distributor for, still connect the governing valve in every branch road, be used for adjusting the pressure of branch road. However, the above patents have the following disadvantages: this patent designs pretightning force loading device to traditional belted star arrow unblock structure, can ensure even synchronous loading pretightning force, nevertheless is not suitable for the pile up satellite of structural configuration, is difficult to satisfy the special requirement that compresses tightly, unblock the separation to the multilayer satellite.
The invention discloses a satellite and rocket separation unlocking module and a method for separating satellites and arrows in low-orbit satellite group batch emission, wherein a plurality of satellites are stacked on a rocket carrier, the bottommost satellite is connected with the carrier through a satellite and rocket connecting mechanism, the satellite and 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 connected with the carrier and extending along the satellite stacking direction, a first initiating explosive device is arranged at the joint of the pull rods and the carrier, the tail ends of the two pull rods are connected with a pressing plate located outside the tail-end satellite, and a pressure-bearing body is arranged between the pressing plate and the tail-end satellite in a pressing mode. However, the above patents have the following disadvantages: the height of the integral mass center of the satellite group cannot be reduced by using the bearing body.
According to the search of the prior art, publications: international space, 453 th, "energy adjustable miniature satellite-rocket spring separation device". The article designs a satellite and rocket spring separation device suitable for one-rocket-multi-satellite, and the satellite separation attitude can be adjusted by adjusting the spring stroke, but the technology has the following defects: the dependence on a central force bearing structure cannot be avoided under the condition that the number of satellites is larger, so that the overall mass center height of a satellite group is higher, and the upper limit value of the number of one-rocket multi-satellite launching satellites is limited.
Because the structural form of the stacked satellite is greatly different from that of the traditional satellite, if the traditional satellite-rocket unlocking device is continuously used, the requirements of stable connection in a launching stage and unlocking separation in an in-orbit stage are difficult to meet. Therefore, the satellite and rocket unlocking device for separating the stacked satellites from the carrier is provided.
Disclosure of Invention
In view of the defects in the prior art, the invention aims to provide a satellite and rocket unlocking device for separating stacked satellites from carriers.
The satellite and rocket unlocking device for separating stacked satellites from carrying provided by the invention comprises a satellite and rocket connecting ring, a satellite layer and a swing rod;
the satellite layer is provided with a plurality of layers, and the plurality of layers of satellite layers are stacked on the satellite arrow 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 assembly;
the unlocking assembly comprises an adapter, a pressing seat and an unlocking piece, the adapter is connected and arranged on 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 rod is arranged to be tightly attached to the side wall of the satellite layer, the satellite layers are connected with the adapter through the unlocking piece to be in a compressed state, and the compression seat and the satellite layer on the uppermost layer are arranged in a compressed mode;
when the satellite layer is converted to a loose state and stacked, the unlocking piece is disconnected with the adapter, the pressing seat is released from the pressing setting of the satellite layer, and the swing rod rotates around the axis of the pin structure towards the direction far away from the satellite stack.
In some embodiments, the unlocking assembly further comprises an elastic member and a sleeve, the sleeve penetrates through the pressing seat, the adapter penetrates through the sleeve, the elastic member is sleeved on the adapter, and the elastic member 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 part of rod pieces on the swing rod through a torsion-proof pin, the connecting end is provided with an opening, and the connecting end is hinged to the pin structure through the opening and the pin hole reserved in the satellite-rocket connecting ring.
In some embodiments, the unlocking member is an initiating explosive device, and the elastic member is a spring.
In some embodiments, a cold air injection thrust mechanism is arranged on the pressing seat, and the cold air injection thrust mechanism is arranged corresponding to the upper end face of the swing rod.
In some embodiments, the number of the compression seats is four, the compression seats are circumferentially arranged corresponding to the satellite-rocket connecting rings, two groups of the unlocking assemblies are arranged in each compression seat, and the two groups of the unlocking assemblies are symmetrically arranged in the compression seats.
In some embodiments, the swing rod is a titanium alloy round rod, the outer diameter of the swing rod is 35mm, the thickness of the rod wall of the swing rod is 5mm, the length of the swing rod is 3000mm, the connecting end is arranged in a drop-shaped structure, the thickness of the connecting end is 50mm, and the diameter of the hole is 40 mm.
In some embodiments, eight pin hole interfaces are arranged on the satellite-rocket connecting ring, eight groups of pin hole interfaces are arranged, eight pin structures are circumferentially arranged on the satellite-rocket connecting ring corresponding to the pin hole interfaces, the diameter of each pin hole interface is 40mm, and the diameter of each pin structure is 40 mm.
In some embodiments, 5-30 satellite layers are stacked on the satellite arrow connecting ring.
In some embodiments, when a plurality of satellite layers are stacked on the satellite connecting ring, the swing rod is arranged to be attached to the plurality of satellite layers, the pressing seat is arranged to correspond to the uppermost satellite layer, and a pre-tightening force is applied to the pressing seat, so that the elastic member in the pressing seat is in a compressed state to keep the pressing seat pressing the satellite layers;
the unlocking piece in the unlocking assembly unlocks after the satellite stably spins in orbit, the unlocking piece is disconnected with the connection of a transfer joint in the unlocking assembly, the unlocking assembly passes through the elastic piece recovers deformation and follows the axial direction of the elastic piece to move, the pressing seat is released from being right to the pressing setting of the satellite layer, a cold air injection thrust mechanism on the pressing seat works to push the pressing seat and the oscillating bar to wind the axis of the pin structure to rotating in the direction of keeping away from the satellite layer, and the satellite layer is separated from the satellite connecting ring in an unlocking mode.
Compared with the prior art, the invention has the following beneficial effects:
1. according to the invention, the swing rod is arranged, the pressing seat is arranged on the swing rod, and the multi-layer satellite layer is arranged on the satellite and rocket connecting ring in a pressing state by applying pretightening force through the pressing seat, so that the integral mass center height of a satellite group is reduced, and the circumferential utilization rate of the carrying fairing is improved;
2. according to the invention, by arranging the unlocking component, the adapter, the elastic piece and the unlocking piece, the pressing seat can be tightly pressed on the satellite layer, and the pressing seat can release the pressing on the satellite layer through the unlocking piece, so that the design is simplified, the risk of unlocking the stacked satellite layer is reduced, and the unlocking efficiency and the reliability of the design are improved;
3. according to the invention, the initiating explosive device is used as the unlocking piece, the swing rod is hinged with the satellite-rocket connecting rod through the pin structure, the unlocking assembly still keeps the connection with the swing rod after the unlocking piece is unlocked, and the swing rod still keeps the connection with the satellite-rocket connecting ring after swinging outwards, 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 invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
FIG. 1 is a drawing state diagram I before unlocking of a satellite and rocket unlocking device for stacking satellites and carrying separation, disclosed by the invention;
FIG. 2 is a drawing showing a second folded state of the satellite and rocket unlocking device for separating stacked satellites from carrier after unlocking;
FIG. 3 is a state diagram of the outward swinging of the stacked satellite and carrier separated satellite unlocking device after unlocking;
FIG. 4 is a schematic structural diagram of a swing rod and an unlocking assembly in the satellite and rocket unlocking device for stacking satellites and carrying separation according to the invention;
FIG. 5 is a partial schematic view of a swing rod and an unlocking assembly in the satellite and rocket unlocking device for stacking satellites and carrying separation according to the invention;
FIG. 6 is a schematic cross-sectional view of an unlocking assembly in the satellite and rocket unlocking device for stacking satellites and carrying separation according to the invention;
FIG. 7 is a view of the pivot shaft of the present invention before unlocking in a satellite and rocket unlocking device for stacked satellites and carrier separation;
fig. 8 is a view of the pivot shaft after unlocking in the satellite and rocket unlocking device for stacking satellites and carrying separation according to the invention.
Reference numerals:
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
Fig. 1 is a drawing state diagram of a first folded state before unlocking of a satellite and rocket unlocking device for stacking satellites and carrying separation, fig. 2 is a drawing state diagram of a second folded state after unlocking of the satellite and rocket unlocking device for stacking satellites and carrying separation, and fig. 3 is a drawing state diagram of an outward swinging state after unlocking of the satellite and rocket unlocking device for stacking satellites and carrying separation, the outward swinging state diagram comprises a satellite and rocket 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 and rocket connecting ring 1. In the embodiment, 5-30 satellite layers 2 are stacked on the satellite arrow connecting ring 1.
Fig. 7 shows a diagram of a rotating pivot before unlocking in the satellite and rocket unlocking device for stacking satellites and carrying separation, fig. 8 shows a diagram of a rotating pivot after unlocking in the satellite and rocket unlocking device for stacking satellites and carrying separation, a pin structure 5 is arranged on a satellite and rocket connecting ring 1 through a reserved pin hole, one end of a swing rod 3 is hinged with the pin structure 5, and an unlocking assembly 4 is arranged at the other end of the swing rod 3. In this embodiment, the end of the swing link 3 is provided with a connecting end 11, the connecting end 11 is connected with a part of the rod elements on the swing link 3 through a torsion-proof pin 12, the connecting end 11 is provided with an opening, and the connecting end 11 is hinged to the pin structure 5 through the opening corresponding to the reserved pin hole of the satellite-rocket connecting ring 1.
When satellite layer 2 kept compressing tightly the state and piled up, the lateral wall setting on satellite layer 2 is hugged closely to pendulum rod 3, and multilayer satellite layer 2 keeps the compression state through unblock piece 10 and adapter 7 interconnect, compresses tightly the setting of compressing tightly each other of the satellite layer 2 of seat 6 and the superiors. When the satellite layer 2 is converted to be in a loose state and stacked, the unlocking piece 10 is disconnected from the adapter 7, the pressing seat 6 is released from pressing with the satellite layer 2, and the swing rod 3 rotates around the axis of the pin structure 5 in the direction far away from the satellite stack.
Fig. 4 is a schematic structural diagram of a swing rod 3 and an unlocking assembly 4 in a satellite and carrier separation satellite unlocking device, fig. 5 is a partial schematic structural diagram of the swing rod 3 and the unlocking assembly 4 in the satellite and carrier separation satellite unlocking device, fig. 6 is a schematic sectional diagram of the unlocking assembly 4 in the satellite and carrier separation satellite unlocking device, the unlocking assembly 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. Unblock subassembly 4 still includes elastic component 8 and sleeve 9, and the excessive compression seat 6 is worn to establish by sleeve 9, and adapter 7 is worn to establish in sleeve 9, and 8 covers of elastic component are established on adapter 7, and elastic component 8 sets up between adapter 7 and sleeve 9. In this embodiment, the unlocking member 10 is an initiating explosive device, and the elastic member 8 is a spring.
In this embodiment, the number of the pressing seats 6 is four, the pressing seats 6 are circumferentially arranged corresponding to the satellite-rocket connecting ring 1, two groups of unlocking assemblies 4 are arranged in each pressing seat, and the two groups of unlocking assemblies 4 are symmetrically arranged in the pressing seats 6. The pressing 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 pendulum rod 3 adopts titanium alloy round bar, and the external diameter of pendulum rod 3 is 35mm, and the pole wall thickness of pendulum rod 3 is 5mm, and the length of pendulum rod 3 is 3000mm, and link 11 adopts the drop shape structure to set up, and the thickness of link 11 is 50mm, and the diameter of trompil is 40 mm's pinhole. The star-arrow connecting ring 1 is provided with eight pin hole interfaces, the pin hole interfaces are provided with eight groups, the pin structures 5 are eight, the eight pin structures 5 are circumferentially arranged on the star-arrow connecting ring 1 corresponding to the pin hole interfaces, the diameters of the pin hole interfaces are 40mm, the diameters of the pin structures 5 are 40mm, and the pendulum rod 3 can smoothly swing outwards through the design size tolerance.
The working principle is as follows: when a plurality of satellite layers 2 are stacked on the satellite connecting ring 1, the swing rod 3 is arranged to be attached to the plurality of satellite layers 2, the pressing seat 6 is arranged to correspond to the uppermost satellite layer 2, pre-tightening force is applied to the pressing seat 6, and the 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 unblock subassembly 4 unlocks after the stable spin in orbit of satellite, unblock piece 10 disconnection and unblock subassembly 4 in the swivel joint 7 be connected, unblock subassembly 4 recovers deformation and removes along the axial direction of elastic component 8 through elastic component 8, compress tightly seat 6 and remove the setting of compressing tightly to satellite layer 2, compress tightly the work of cold jet thrust mechanism on the seat 6, the promotion compresses tightly seat 6 and pendulum rod 3 and rotates around the axis of round pin structure 5 to the direction of keeping away from satellite layer 2, satellite layer 2 and the separation of the unblock of satellite arrow go-between 1.
In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (10)
1. A satellite and rocket unlocking device for stacking satellites and carrying separation is characterized by comprising a satellite and rocket connecting ring (1), a satellite layer (2) and a swing rod (3);
the satellite layer (2) is provided with a plurality of layers, and the satellite layers (2) are stacked on the satellite arrow connecting ring (1);
the satellite-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 assembly (4);
the unlocking assembly (4) comprises an adapter (7), a pressing seat (6) and an unlocking piece (10), 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 kept in a compressed state and stacked, the swing rod (3) is tightly attached to the side wall of the satellite layer (2), the satellite layers (2) in multiple layers are mutually connected with the adapter (7) through the unlocking piece (10) to be kept in a compressed state, and the compressing seat (6) and the satellite layer (2) on the uppermost layer are mutually compressed;
satellite layer (2) conversion to the relaxation state when piling up, unblock piece (10) disconnection with the connection of adapter (7), compress tightly seat (6) remove with satellite layer (2) compress tightly the setting, pendulum rod (3) are wound the axis of round pin structure (5) is to keeping away from the direction that the satellite piled rotates.
2. The satellite and rocket unlocking device for stacking satellites and carrying separation according to claim 1, wherein said unlocking assembly (4) further comprises an elastic member (8) and a sleeve (9), said sleeve (9) penetrates through said pressing seat (6), said adapter (7) penetrates through said sleeve (9), said elastic member (8) is sleeved on said adapter (7), and said elastic member (8) is disposed between said adapter (7) and said sleeve (9).
3. The satellite unlocking device for separating satellite stacking and satellite carrying according to claim 1, wherein a connecting end (11) is arranged at an end of the swing rod (3), the connecting end (11) is connected with a part of rod pieces on the swing rod (3) through a torsion-proof pin (12), an opening is formed in the connecting end (11), and the connecting end (11) is hinged to the pin structure (5) through the opening and the reserved pin hole of the satellite connecting ring (1) corresponding to each other.
4. Satellite and rocket unlocking device for stacked satellites and carrier separation according to claim 2, wherein said unlocking member (10) is made of initiating explosive device and said elastic member (8) is made of spring.
5. The satellite and rocket unlocking device for stacking satellites and carrying separation according to claim 1, wherein the pressing seat (6) is provided with a cold air injection thrust mechanism, and the cold air injection thrust mechanism is arranged corresponding to the upper end face of the swing rod (3).
6. The satellite and rocket unlocking device for separating stacked satellites from carrier of claim 2, wherein the number of the pressing seats (6) is four, the pressing seats (6) are circumferentially arranged corresponding to the satellite and rocket connecting ring (1), two groups of the unlocking assemblies (4) are arranged in each pressing seat (6), and the two groups of the unlocking assemblies (4) are symmetrically arranged in the pressing seats (6).
7. The satellite and rocket unlocking device for stacking satellites and carrying separation according to claim 3, wherein the swing rod (3) is 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 water drop-shaped structure, the thickness of the connecting end (11) is 50mm, and the diameter of the hole is a 40mm pin hole.
8. The satellite unlocking device for separation of stacking satellite and carrying according to claim 6 is characterized in that the satellite connecting ring (1) is provided with eight 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 satellite 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 40 mm.
9. The satellite unlocking device for the separation of stacked satellites and carrier of claim 1 is characterized in that 5-30 layers of satellite layers (2) are stacked on the satellite connecting ring (1).
10. The satellite unlocking device for separating satellite stacking and carrying according to claim 1, wherein when a plurality of satellite layers (2) are stacked on the satellite connecting ring (1), the swing rod (3) is arranged to be attached to the plurality of satellite layers (2), the pressing seat (6) is arranged to correspond to the uppermost satellite layer (2), and pretightening force is applied to the pressing seat (6) to enable the elastic member (8) in the pressing seat (6) to be in a compressed state to keep the pressing seat (6) pressed against the satellite layers (2);
unlocking piece (10) among unblock subassembly (4) is in the satellite and is carried out the unblock after the stable spin of orbit, unblock piece (10) disconnection with the connection of unblock subassembly (4) transfer joint (7), unblock subassembly (4) pass through elastic component (8) resume deformation and follow the axial direction of elastic component (8) removes, it is right to compress tightly seat (6) release the setting of compressing tightly of satellite layer (2), compress tightly the work of the jet-propelled thrust mechanism 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 the direction of satellite layer (2) rotates, satellite layer (2) with satellite arrow go-between (1) unblock separation.
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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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Cited By (8)
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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 |
| CN114229047A (en) * | 2021-12-23 | 2022-03-25 | 中国科学院力学研究所 | Based on liquid CO2Satellite-rocket separation device driven by rapid gasification |
| CN114353603A (en) * | 2022-01-13 | 2022-04-15 | 北京中科宇航技术有限公司 | Separation unlocking device for non-explosive device star and arrow |
| 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 |
| CN114802824A (en) * | 2022-04-14 | 2022-07-29 | 北京微分航宇科技有限公司 | Heap compress tightly release |
| CN115009549A (en) * | 2022-08-09 | 2022-09-06 | 北京星河动力装备科技有限公司 | Locking and releasing mechanism, control method thereof and carrier rocket |
| CN115231004A (en) * | 2022-09-20 | 2022-10-25 | 北京宇航系统工程研究所 | Connection and separation mechanism for stacked satellites |
| CN115675938A (en) * | 2022-11-21 | 2023-02-03 | 北京中科宇航技术有限公司 | Low-orbit mobile stack constellation satellite unlocking distributor |
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