CN115892506A - Spacecraft structure suitable for vertical layout of rigid flat plate - Google Patents
Spacecraft structure suitable for vertical layout of rigid flat plate Download PDFInfo
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- CN115892506A CN115892506A CN202211509766.3A CN202211509766A CN115892506A CN 115892506 A CN115892506 A CN 115892506A CN 202211509766 A CN202211509766 A CN 202211509766A CN 115892506 A CN115892506 A CN 115892506A
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Abstract
The invention provides a spacecraft structure suitable for vertical layout of a rigid flat plate in the technical field of spaceflight, which comprises a rigid flat plate spacecraft, a force transmission block, a V-shaped clamping block and a wrapping belt, wherein the force transmission block is arranged on the rigid flat plate spacecraft; the force transfer block is connected with the rigid flat plate spacecraft and is tightly pressed by the wrapping belt to form the rigid flat plate spacecraft; the rigid flat plate spacecraft is fixedly provided with a connecting ring; the V-shaped fixture block is fixedly arranged on the force transmission block, and the force transmission block is arranged at the position of the V-shaped fixture block in a limiting way; a wrapping belt is fixedly arranged on the outer side of the V-shaped clamping block. The invention is a novel spacecraft connection form by arranging the force transmission block, the V-shaped fixture block and the wrapping belt, replaces the conventional main bearing column structure form, realizes the connection of a plurality of spacecrafts, meets the vertical or oblique layout requirement of the rigid flat spacecraft, further improves the effective utilization rate of a carrying space and the launching efficiency of the spacecraft, and meets the application requirements of launching and rapid networking of the current rocket multi-spacecraft.
Description
Technical Field
The invention relates to the technical field of spaceflight, in particular to a spacecraft structure suitable for vertical layout of a rigid flat plate.
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 spacecraft communication can effectively solve the internet service problem 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 spacecraft networking plans, and the technical trend of internet multi-spacecraft systems has been raised.
The prior art searches and finds that the Chinese invention patent publication No. CN107889482A discloses a stackable satellite comprising a satellite frame and at least one vertical pillar attached to the frame. The vertical strut has an upper end and a lower end. The upper end is coupled to the lower end of the vertical column of the satellite above and the lower end is coupled to the upper end of the vertical column of the satellite below. The vertical struts receive substantially all of the vertical load of the stackable satellite and any other satellites stacked above, but the problem is that the overall size of the spacecraft is small and it is difficult to accommodate the installation requirements of multiple loads, high loads.
The search of the prior art shows that the Chinese invention patent publication No. CN103387058A discloses a multi-spacecraft launching system which can be suitable for being placed in a payload area of a carrier rocket fairing. The launch system may comprise a first spacecraft and a second spacecraft releasably attached to and oriented relative to the first spacecraft such that when they are placed within the fairing, the launch load of the first spacecraft is transferred to and borne by the second spacecraft, but with the problem that only two spacecraft can be accommodated, the need for rapid networking of multiple spacecraft is difficult to meet.
Research and analysis show that aiming at the vertical or oblique layout requirements of the rigid plate spacecraft, if traditional rocket multi-spacecraft configuration and connection form design are used continuously, a spacecraft structure design scheme suitable for vertical or oblique layout is provided, and a force transmission block, a V-shaped clamping block, a belt and other connection structures are innovatively adopted, so that the utilization rate of a carrying space and the launching efficiency of the spacecraft are further improved; the multiple spacecrafts are unlocked simultaneously, so that the reliability of unlocking design is greatly improved, and the risk is reduced; and meanwhile, the design of the pull rod is combined.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a spacecraft structure suitable for vertical layout of rigid flat plates.
The spacecraft structure suitable for the vertical layout of the rigid flat plate comprises a rigid flat plate spacecraft, a force transmission block, a V-shaped clamping block and a wrapping belt;
the force transfer block is connected with the rigid flat-plate spacecraft and is tightly pressed by the wrapping tape; the rigid flat plate spacecraft is fixedly provided with a connecting ring;
the V-shaped clamping block is fixedly arranged on the force transmission block, and the force transmission block is arranged in a limiting manner on the V-shaped clamping block; the bag belt is fixedly arranged on the outer side of the V-shaped clamping block.
In some embodiments, the rigid flat plate spacecraft is of a high-rigidity flat plate type structure, and the high-rigidity flat plate type structure is of a flat cuboid honeycomb plate structure.
In some embodiments, the force transfer blocks are fixedly arranged on the side surface of the rigid flat-plate spacecraft, the force transfer blocks are in a metal T-shaped structure, the force transfer blocks are spliced to form a circular ring, and the circular ring is fixedly arranged on the side surface of the rigid flat-plate spacecraft.
In some embodiments, the strap is fixedly disposed on the circular ring, the strap is tightly pressed against the circular ring, and the strap is of a metal circular ring structure.
In some embodiments, a flange structure is fixedly arranged on the force transfer block; the V-shaped fixture block is of an arc-shaped strip structure, a groove is fixedly formed in the V-shaped fixture block, and the groove corresponds to the flange structure.
In some embodiments, the bottom surface of the rigid flat plate spacecraft is provided with cylindrical pins in a connected mode, the cylindrical pins are connected with the connecting rings, the bottom surface of the rigid flat plate spacecraft is provided with the connecting rings through the cylindrical pins in a connected mode, the connecting rings are of a metal annular thin-wall structure, and the bottom surface of the rigid flat plate spacecraft is provided with a carrying final stage through the connecting rings in a connected mode.
In some embodiments, the connecting ring is provided with the pull rod, the pull rod is provided with the wrapping tape, and the wrapping tape is arranged around a rotating shaft of the pull rod through the pull rod.
In some embodiments, the number of the rigid flat plate spacecraft is between 20 and 30, the vertical plane dimension of the rigid flat plate spacecraft is set to be in the range of 5000mm x 5000mm, and the width of the rigid flat plate spacecraft is set to be in the range of 200 mm to 1000 mm.
In some embodiments, a spring is fixedly arranged on the wrapping tape, the wrapping tape comprises an outer ring and an inner ring, the outer ring is connected with the inner ring through the spring, the inner ring is connected with the V-shaped fixture block, and the inner ring is externally tangent to the outer surface of the V-shaped fixture block; the middle part and the top part of the pull rod are respectively arranged corresponding to the corresponding positions of the outer ring, an interface is fixedly arranged on the outer ring, and the interface is connected with the pull rod.
In some embodiments, the wrapping tape is fixedly provided with unlocking devices, and the unlocking devices are arranged in a bilateral symmetry manner.
Compared with the prior art, the invention has the following beneficial effects:
1. the invention adopts a novel spacecraft connection form by arranging a force transmission block, a V-shaped clamping block and a wrapping belt to replace a main force bearing column structure form which is commonly used in the past, realizes the connection of a plurality of spacecrafts, meets the vertical or oblique layout requirement of a rigid flat-plate spacecraft, further improves the effective utilization rate of a carrying space and the launching efficiency of the spacecrafts, and meets the application requirements of launching the current rocket multi-spacecraft and rapid networking;
2. according to the invention, the rigid flat plate spacecraft is in a flat plate type configuration, and a single machine with a flat structure is matched, so that the effective volume ratio of the spacecraft is increased, more effective loads can be carried in a limited space of the fairing, and more on-orbit tasks of the spacecraft are realized;
3. according to the invention, the plurality of spacecrafts are compressed and unlocked by setting the wrapping belt for unlocking, and compared with the traditional mode that each spacecraft is independently connected with the main bearing column and unlocked, the plurality of spacecrafts are unlocked simultaneously, so that the unlocking risk can be greatly reduced, the reliability and the safety of the unlocking separation design are improved, and the method is also suitable for obliquely-arranged spacecrafts;
4. according to the invention, the connecting and unlocking devices such as the belt and the like are connected and then enter the atmosphere for destruction by arranging the pull rod, so that the destruction meets the regulations of related space environment protection.
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 schematic view of the launch state of the spacecraft structure of the present invention adapted for a rigid plate vertical layout;
FIG. 2 is a schematic view of an unlocked deployed state of a spacecraft structure suitable for rigid plate vertical layout according to the present invention;
FIG. 3 is a schematic view of a rigid plate spacecraft suitable for use in a spacecraft configuration with a rigid plate vertical layout according to the present invention;
FIG. 4 is a schematic diagram of a force transfer block of the spacecraft structure suitable for rigid plate vertical layout of the present invention;
FIG. 5 is a schematic diagram of an unassembled state of a force transfer block assembly of a spacecraft structure suitable for rigid plate vertical layout according to the present invention;
fig. 6 is a schematic view of an assembly state of a force transfer block assembly of a spacecraft structure suitable for a vertical layout of rigid plates according to the present invention;
FIG. 7 is a schematic view of a flange configuration of a spacecraft configuration suitable for rigid plate vertical layout according to the present invention;
FIG. 8 is a schematic diagram of the unassembled and assembled state of the V-shaped fixture block of the spacecraft structure suitable for the vertical layout of the rigid flat plate according to the present invention;
fig. 9 is a schematic diagram of a strap for a spacecraft structure adapted for a rigid plate vertical layout in accordance with the present invention.
Reference numerals:
Inner ring 8 of force transmission block 2
Unlocking device 11 for connecting ring 5
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will aid those skilled in the art in further understanding the present invention, but are not intended to limit the invention in any manner. 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 schematic diagram of a launching state of a spacecraft structure suitable for rigid flat plate vertical layout according to the present invention, fig. 2 is a schematic diagram of an unlocking and unfolding state of the spacecraft structure suitable for rigid flat plate vertical layout according to the present invention, fig. 3 is a schematic diagram of a rigid flat plate spacecraft structure suitable for rigid flat plate vertical layout according to the present invention, fig. 4 is a schematic diagram of a force transfer block of the spacecraft structure suitable for rigid flat plate vertical layout according to the present invention, fig. 5 is a schematic diagram of an unassembled state of a force transfer block component of the spacecraft structure suitable for rigid flat plate vertical layout according to the present invention, fig. 6 is a schematic diagram of an assembled state of a force transfer block component of the spacecraft structure suitable for rigid flat plate vertical layout according to the present invention, fig. 7 is a schematic diagram of a flange structure of the spacecraft structure suitable for rigid flat plate vertical layout according to the present invention, fig. 8 is a schematic diagram of an unassembled and assembled state of a V-shaped clamp block of the spacecraft structure suitable for rigid flat plate vertical layout according to the present invention, and fig. 9 is a schematic diagram of the spacecraft structure suitable for rigid flat plate vertical layout according to the present invention. Comprises a rigid flat-plate spacecraft 1, a force transmission block 2, a V-shaped clamping block 3 and a belting 4. The force transmission block 2 is connected with the rigid flat plate spacecraft 1, and the force transmission block 2 is tightly pressed by the wrapping belt 4 to form the rigid flat plate spacecraft 1. The rigid plate spacecraft 1 is fixedly provided with a connecting ring 5. The V-shaped clamping block 3 is fixedly arranged on the force transmission block 2, and the force transmission block 2 is arranged at the position of the V-shaped clamping block 3 in a limiting mode. The bag belt 4 is fixedly arranged on the outer side of the V-shaped clamping block 3.
The rigid plate spacecraft 1 adopts a high-rigidity plate type structure, and the high-rigidity plate type structure is a flat cuboid honeycomb panel structure. The outer contour dimension of the rigid flat plate spacecraft 1 is 300mm multiplied by 2000mm multiplied by 4000mm, the rigid flat plate spacecraft comprises a bottom plate, a plurality of partition plates and a side plate, a force transmission block 2 connecting interface is designed on the side plate, and interfaces connected with a connecting ring 5 are designed at four corner positions at the bottom of the rigid flat plate spacecraft 1. The side surface of the rigid flat plate spacecraft 1 is fixedly provided with a force transfer block 2, the force transfer block 2 is of a metal T-shaped structure, and the force transfer block 2 is composed of a bottom surface, a vertical surface and a flange structure 7 on the vertical surface. The width of each force transfer block 2 is equal to or less than that of the rigid flat-plate spacecraft 1, and the height of the vertical plane of each force transfer block 2 is designed within the range of 50-100 mm. A plurality of biography power piece 2 splice and set up into the ring, and the ring is fixed to be set up in rigidity flat plate spacecraft 1 side. The force transfer block 2 is installed on the side face of the rigid flat plate spacecraft 1 through an interface of the bottom face, the width of the bottom face of the force transfer block 2 is 300mm consistent with that of the rigid flat plate spacecraft 1, the thickness of the force transfer block is 10mm, the length of the force transfer block in the radial direction is 150mm, a plurality of force transfer blocks 2 form a complete circular ring on the side face of the rigid flat plate spacecraft 1, and the diameter of the circular ring is 1500mm.
The round ring is fixedly provided with a wrapping belt 4, the wrapping belt 4 is tightly pressed with the round ring, and the wrapping belt 4 is of a metal round ring structure. The rings are connected in a pressing mode through pretightening force exerted by the wrapping belts 4, and during detailed design, the rings can be adaptively modified according to the number and the width of the rigid plate spacecraft 1. The force transmission block 2 is fixedly provided with a flange structure 7,V type clamping block 3 which adopts an arc-shaped strip structure, the V-shaped clamping block 3 is fixedly provided with a groove, and the groove is arranged corresponding to the flange structure 7. The height of the vertical surface of the force transmission block 2 is 70mm, a flange structure 7 is designed on the outer surface of the force transmission block, the flange structure 7 is consistent with the contour of a groove on the inner side of a V-shaped clamping block 3, and the V-shaped clamping block 3 is embedded in the joint position of the adjacent force transmission blocks 2 to prevent the force transmission blocks 2 from sliding transversely.
The bottom surface of the rigid flat plate spacecraft 1 is provided with cylindrical pins 12 in a connected mode, the cylindrical pins 12 are connected with the connecting rings 5 in a set mode, the bottom surface of the rigid flat plate spacecraft 1 is provided with the connecting rings 5 in a connected mode through the cylindrical pins 12, the connecting rings 5 are of metal annular thin-wall structures, the connecting rings 5 are connected with the rigid flat plate spacecraft 1 and a carrying final stage, and the bottom surface of the rigid flat plate spacecraft 1 is provided with the carrying final stage in a connected mode through the connecting rings 5. The connecting ring 5 is connected with a pull rod 6, the pull rod 6 is connected with a wrapping tape 4, and the wrapping tape 4 is arranged around a rotating shaft of the pull rod 6 through the pull rod 6.
After the wrapping tape 4 is unlocked and separated from the rigid plate spacecraft 1, the wrapping tape 4 and the connecting ring 5 enter the atmosphere again. Aiming at the vertical or oblique layout requirement of the rigid plate spacecraft 1, a novel connection mode is designed, the conventional main bearing column structure form is cancelled, and the effective utilization rate of a carrying space is improved. The number of the rigid flat plate spacecrafts 1 is set between 20-30, the vertical plane size of the rigid flat plate spacecrafts 1 is set to be within the range of 5000mm multiplied by 5000mm, the width of the rigid flat plate spacecrafts 1 is set to be within the range of 200-1000 mm, and the fairing size and the load requirement can be modified adaptively during detailed design.
The spring 10 is fixedly arranged on the wrapping tape 4, the wrapping tape 4 comprises an outer ring 9 and an inner ring 8, the inner ring 8 of the wrapping tape 4 is externally tangent to the outer surfaces of the V-shaped clamping blocks 3, the corresponding position on the outer ring 9 of the wrapping tape 4 is provided with an interface which is connected with the pull rod 6, and the outer ring 9 is connected with the inner ring 8 through the spring 10. Four circular ring structures are formed by a plurality of force transmission blocks 2 on two sides of a rigid flat plate spacecraft 1, the wrapping belts 4 are installed on the V-shaped clamping blocks 3, fastening connection between the adjacent force transmission blocks 2 is realized by applying pretightening force, and then fastening connection between a plurality of rigid flat plate spacecrafts 1 is realized.
After the rigid flat plate spacecraft 1 enters the orbit, the unlocking device 11 unlocks, the whole bag belt 4 is separated from the rigid flat plate spacecraft 1, the adjacent force transmission blocks 2 are separated, and the adjacent rigid flat plate spacecraft 1 are not fastened and connected. The unlocking device 11 is fixedly arranged on the wrapping belt 4, the unlocking device 11 is arranged in a bilateral symmetry mode, simultaneous unlocking of the rigid plate spacecrafts 1 is achieved, reliability of an unlocking process is improved, and risks are reduced. The launching section applies pretightening force on the inner ring 8 of the wrapping tape 4, when the rigid plate spacecraft 1 needs to be separated due to stable in-orbit flight, the unlocking device 11 is unlocked, and the pull rod 6 drives the outer ring 9 of the wrapping tape 4, the spring 10 and the inner ring 8 of the wrapping tape to enter the atmosphere together with the final carrying stage. The connection and unlocking mode of the spacecraft in the scheme is also suitable for the spacecraft in an oblique layout.
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, merely for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore, are not to be construed as limiting the present application.
The foregoing description has described specific embodiments of the present invention. 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 spacecraft structure suitable for vertical layout of a rigid flat plate is characterized by comprising a rigid flat plate spacecraft (1), a force transmission block (2), a V-shaped fixture block (3) and a belting (4);
the force transmission block (2) is connected with the rigid flat plate spacecraft (1), and the force transmission block (2) is tightly pressed by the strap (4) to be arranged on the rigid flat plate spacecraft (1); the rigid flat plate spacecraft (1) is fixedly provided with a connecting ring (5);
the V-shaped clamping block (3) is fixedly arranged on the force transmission block (2), and the force transmission block (2) is arranged on the V-shaped clamping block (3) in a limiting manner; the bag belt (4) is fixedly arranged on the outer side of the V-shaped clamping block (3).
2. Spacecraft structure suitable for rigid flat vertical layout according to claim 1, the rigid flat spacecraft (1) being of high stiffness flat structure arranged as flat cuboid honeycomb panel structure.
3. The spacecraft structure suitable for the vertical layout of rigid flat plates according to claim 1, wherein the force transfer blocks (2) are fixedly arranged on the side surface of the rigid flat spacecraft (1), the force transfer blocks (2) are of a metal T-shaped structure, a plurality of the force transfer blocks (2) are spliced to form a circular ring, and the circular ring is fixedly arranged on the side surface of the rigid flat spacecraft (1).
4. The spacecraft structure suitable for the vertical layout of rigid flat plates according to claim 3, characterized in that the straps (4) are fixedly arranged on the circular rings, the straps (4) are tightly pressed to arrange the circular rings, and the straps (4) adopt a metal circular ring structure.
5. Spacecraft structure suitable for rigid flat vertical layout according to claim 1, characterized in that the force transfer block (2) is fixedly provided with a flange structure (7); the V-shaped fixture block (3) is of an arc-shaped strip structure, a groove is fixedly arranged on the V-shaped fixture block (3), and the groove corresponds to the flange structure (7).
6. A spacecraft structure suitable for rigid flat vertical layout according to claim 1, wherein the rigid flat spacecraft (1) is provided with cylindrical pins (12) connected to the bottom surface, the cylindrical pins (12) are connected to the connecting ring (5) for arrangement, the connecting ring (5) is connected to the bottom surface of the rigid flat spacecraft (1) through the cylindrical pins (12), the connecting ring (5) is a metal annular thin-wall structure, and the carrying final stage is connected to the bottom surface of the rigid flat spacecraft (1) through the connecting ring (5).
7. A spacecraft structure suitable for a vertical layout of rigid plates according to claim 6, wherein the connecting rings (5) are provided with the pull rods (6) in a connected manner, the pull rods (6) are provided with the belting (4) in a connected manner, and the belting (4) is arranged around the rotating shaft of the pull rods (6) through the pull rods (6) in an outward swinging manner.
8. Spacecraft structure suitable for rigid flat plate vertical layout according to claim 1, characterized in that the number of rigid flat plate spacecraft (1) is set between 20-30, the vertical plane dimension of the rigid flat plate spacecraft (1) is set in the range of 5000mm x 5000mm, the width of the rigid flat plate spacecraft (1) is set in the range of 200-1000 mm.
9. The spacecraft structure suitable for rigid flat vertical layout according to claim 1, wherein the straps (4) are fixedly provided with springs (10), the straps (4) comprise an outer ring (9) and an inner ring (8), and the outer ring (9) is connected with the inner ring (8) through the springs (10); the inner ring (8) is connected with the V-shaped fixture block (3), and the inner ring (8) is externally tangent to the outer surface of the V-shaped fixture block (3); the middle part and the top part of the pull rod (6) are respectively arranged corresponding to the corresponding positions of the outer ring (9), an interface is fixedly arranged on the outer ring (9), and the interface is connected with the pull rod (6).
10. Spacecraft structure suitable for rigid flat vertical layout according to claim 1, characterized in that unlocking devices (11) are fixedly arranged on the straps (4), and the unlocking devices (11) are arranged in bilateral symmetry.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211509766.3A CN115892506A (en) | 2022-11-29 | 2022-11-29 | Spacecraft structure suitable for vertical layout of rigid flat plate |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211509766.3A CN115892506A (en) | 2022-11-29 | 2022-11-29 | Spacecraft structure suitable for vertical layout of rigid flat plate |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115892506A true CN115892506A (en) | 2023-04-04 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211509766.3A Pending CN115892506A (en) | 2022-11-29 | 2022-11-29 | Spacecraft structure suitable for vertical layout of rigid flat plate |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115892506A (en) |
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2022
- 2022-11-29 CN CN202211509766.3A patent/CN115892506A/en active Pending
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