Spacecraft structure suitable for rigid panel vertical layout

Abstract

The application provides a spacecraft structure suitable for rigid flat plate vertical layout in the field of aerospace technology, which comprises a rigid flat plate spacecraft, a force transmission block, a V-shaped clamping block and a wrapping belt; the force transmission block is connected with the rigid flat plate spacecraft and is used for compressing the rigid flat plate spacecraft through the wrapping belt; a connecting ring is fixedly arranged on the rigid flat plate spacecraft; the V-shaped clamping block is fixedly arranged on the force transmission block and is used for limiting the force transmission block; and the wrapping belt is fixedly arranged outside the V-shaped clamping block. The force transmission block, the V-shaped clamping block and the wrapping belt are connected and designed as a novel spacecraft connection form, which replaces the commonly used main bearing column structure form, realizes the connection of multiple spacecrafts, meets the vertical or inclined layout requirements of the rigid flat plate spacecraft, further improves the effective utilization rate of the carrying space and the spacecraft launching efficiency, and meets the application requirements of current one rocket multiple spacecraft launching and rapid networking.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aerospace technology, in particular to a spacecraft structure suitable for rigid flat panel vertical layout. BACKGROUND

[0002] In view of the limitations of ground network coverage, being easily affected by natural environment, etc., spacecraft communication can effectively solve the Internet service problems of remote, offshore and airborne users. In recent years, countries such as the United States and Canada have successively proposed spacecraft networking plans, triggering a technical craze of Internet multi-spacecraft systems.

[0003] Through prior art retrieval, it is found that Chinese invention patent No. CN107889482A discloses a stackable satellite including a satellite frame and at least one vertical strut attached to the frame. The vertical strut has an upper end and a lower end. The upper end is coupled to a lower end of a vertical strut of an upper satellite, and the lower end is coupled to an upper end of a vertical strut of a lower satellite. The vertical strut substantially receives all vertical loads 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 adapt to the installation requirements of multiple loads and large loads.

[0004] Through prior art retrieval, it is found that Chinese invention patent No. CN103387058A discloses a multi-spacecraft launch system that can fit within a payload area of a launch vehicle fairing. The launch system can include a first spacecraft and a second spacecraft releasably attached to the first spacecraft and oriented relative to the first spacecraft such that a launch payload of the first spacecraft is transferred to and assumed by the second spacecraft when they are placed within the fairing, but the problem is that only two spacecrafts can be accommodated, and it is difficult to meet the demand of multi-spacecraft rapid networking.

[0005] Through investigation and analysis, it is found that for the vertical or inclined layout requirements of rigid flat panel spacecraft, there are many deficiencies in the traditional one-rocket multi-spacecraft configuration and connection form design, so a spacecraft structure design scheme suitable for vertical or inclined layout is proposed, which innovatively uses connecting structures such as force transfer blocks, V-shaped clamping blocks and wrapping belts, further improves the utilization rate of carrying space and the launch efficiency of the spacecraft; multiple spacecrafts are unlocked at the same time, greatly improving the reliability and reducing the risk of unlocking design; and the design of the pull rod is combined. SUMMARY

[0006] In view of the defects in the prior art, the purpose of the present application is to provide a spacecraft structure suitable for rigid flat panel vertical layout.

[0007] The application provides a spacecraft structure suitable for rigid flat plate vertical layout, which comprises a rigid flat plate spacecraft, a force transmission block, a V-shaped clamping block and a wrapping belt.

[0008] The force transmission block is connected to the rigid flat plate spacecraft and is used to compress the rigid flat plate spacecraft through the wrapping belt; and a connecting ring is fixed on the rigid flat plate spacecraft.

[0009] The V-shaped clamping block is fixed on the force transmission block and is used to limit the force transmission block; and the wrapping belt is fixed on the outer side of the V-shaped clamping block.

[0010] In some embodiments, the rigid flat plate spacecraft adopts a high-rigidity flat plate structure which is designed as a flat cuboid honeycomb plate structure.

[0011] In some embodiments, the force transmission blocks are fixed on the side surface of the rigid flat plate spacecraft and adopt a metal T-shaped structure; a plurality of the force transmission blocks are spliced into a circular ring which is fixed on the side surface of the rigid flat plate spacecraft.

[0012] In some embodiments, the wrapping belt is fixed on the circular ring and is used to compress the circular ring; and the wrapping belt adopts a metal circular ring structure.

[0013] In some embodiments, a flange structure is fixed on the force transmission block; the V-shaped clamping block adopts a circular arc strip structure and is provided with a groove which is correspondingly arranged with the flange structure.

[0014] In some embodiments, a cylindrical pin is connected to the bottom surface of the rigid flat plate spacecraft and is connected to the connecting ring; the connecting ring adopts a metal ring-shaped thin wall structure; and the cylindrical pin is used to connect the connecting ring to the bottom surface of the rigid flat plate spacecraft.

[0015] In some embodiments, the connecting ring is connected to the pull rod which is connected to the wrapping belt; and the wrapping belt is arranged outside the rotation shaft of the pull rod.

[0016] In some embodiments, the number of the rigid flat plate spacecraft is arranged to be between 20 and 30; the vertical plane size of the rigid flat plate spacecraft is arranged to be within the range of 5000mm*5000mm; and the width of the rigid flat plate spacecraft is arranged to be within the range of 200-1000mm.

[0017] In some embodiments, the bandage is fixedly provided with a spring, the bandage comprises an outer ring and an inner ring, the inner ring is connected to the outer ring by the spring, the inner ring is connected to the V-shaped block, and the inner ring is arranged outside the outer surface of the V-shaped block; the middle and top parts of the pull rod are respectively arranged at corresponding positions of the outer ring, and the outer ring is fixedly provided with an interface connected to the pull rod.

[0018] In some embodiments, the bandage is fixedly provided with an unlocking device, and the unlocking device is arranged symmetrically left and right.

[0019] Compared with the prior art, the present application has the following beneficial effects:

[0020] 1. The present application sets a force transmission block, a V-shaped block and a bandage connection design as a new type of spacecraft connection form, replacing the commonly used main load-bearing column structure form, realizing the connection of multiple spacecrafts, meeting the vertical or inclined layout requirements of rigid flat plate spacecrafts, further improving the effective utilization rate of carrying space and the spacecraft launch efficiency, and meeting the current one rocket multiple spacecraft launch and rapid networking application requirements.

[0021] 2. The present application sets the rigid flat plate spacecraft as a flat plate type configuration, cooperates with a single machine of a flat structure, increases the effective volume ratio of the spacecraft, can carry more effective payloads in the limited space of the fairing, and realizes more spacecraft on-orbit missions.

[0022] 3. The present application sets a bandage unlocking mode for multiple spacecraft compression unlocking. Compared with the traditional form of each spacecraft being individually connected to and unlocked from the main load-bearing column, simultaneous unlocking of multiple spacecrafts can greatly reduce the unlocking risk, improve the reliability and safety of unlocking separation design, and is also applicable to inclined layout spacecrafts.

[0023] 4. The present application sets a pull rod to realize the reentry of the bandage connection unlocking device into the atmosphere for destruction, in line with relevant space environment protection regulations. BRIEF DESCRIPTION OF DRAWINGS

[0024] Other features, objects and advantages of the present application will become more apparent from the following detailed description of non-limiting embodiments, with reference to the accompanying drawings:

[0025] Figure 1 is a schematic diagram of the launch state of the spacecraft structure suitable for the rigid flat plate vertical layout of the present application;

[0026] Figure 2 is a schematic diagram of the unlocking and unfolding state of the spacecraft structure suitable for the rigid flat plate vertical layout of the present application;

[0027] Figure 3Rigid flat spacecraft schematic diagram suitable for the spacecraft structure of the present application in rigid flat vertical layout;

[0028] Figure 4 Force block schematic diagram suitable for the spacecraft structure of the present application in rigid flat vertical layout;

[0029] Figure 5 Unassembled force block assembly schematic diagram suitable for the spacecraft structure of the present application in rigid flat vertical layout;

[0030] Figure 6 Assembled force block assembly schematic diagram suitable for the spacecraft structure of the present application in rigid flat vertical layout;

[0031] Figure 7 Flange structure schematic diagram suitable for the spacecraft structure of the present application in rigid flat vertical layout;

[0032] Figure 8 Unassembled and assembled V-shaped clamping block schematic diagram suitable for the spacecraft structure of the present application in rigid flat vertical layout;

[0033] Figure 9 Wrapping belt schematic diagram suitable for the spacecraft structure of the present application in rigid flat vertical layout.

[0034] Reference signs:

[0035] Rigid flat spacecraft 1 Flange structure 7

[0036] Force block 2 Inner ring 8

[0037] V-shaped clamping block 3 Outer ring 9

[0038] Wrapping belt 4 Spring 10

[0039] Connecting ring 5 Unlocking device 11

[0040] Pull rod 6 Cylindrical pin 12 DETAILED DESCRIPTION

[0041] The present application will be described in detail below with specific embodiments. The following embodiments will help those skilled in the art to further understand the present application, but do not limit the present application in any form. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present application. These are within the scope of the present application.

[0042] As Figure 1 Launch state schematic diagram suitable for the spacecraft structure of the present application in rigid flat vertical layout, as Figure 2 Unlocked and deployed state schematic diagram suitable for the spacecraft structure of the present application in rigid flat vertical layout, asFigure 3 A rigid flat plate spacecraft schematic diagram suitable for the spacecraft structure of the present application in rigid flat plate vertical layout, as shown in Figure 4 A force block schematic diagram suitable for the spacecraft structure of the present application in rigid flat plate vertical layout, as shown in Figure 5 A force block assembly un-assembled state schematic diagram suitable for the spacecraft structure of the present application in rigid flat plate vertical layout, as shown in Figure 6 A force block assembly assembled state schematic diagram suitable for the spacecraft structure of the present application in rigid flat plate vertical layout, as shown in Figure 7 A flange structure schematic diagram suitable for the spacecraft structure of the present application in rigid flat plate vertical layout, as shown in Figure 8 A V-shaped clamping block un-assembled and assembled state schematic diagram suitable for the spacecraft structure of the present application in rigid flat plate vertical layout, as shown in Figure 9 A wrapping tape schematic diagram suitable for the spacecraft structure of the present application in rigid flat plate vertical layout. It includes a rigid flat plate spacecraft 1, a force block 2, a V-shaped clamping block 3, and a wrapping tape 4. The force block 2 is connected to the rigid flat plate spacecraft 1, and the rigid flat plate spacecraft 1 is tightly set by the force block 2 through the wrapping tape 4. The rigid flat plate spacecraft 1 is fixedly provided with a connecting ring 5. The V-shaped clamping block 3 is fixedly provided on the force block 2, and the V-shaped clamping block 3 limits the force block 2. The wrapping tape 4 is fixedly provided on the outer side of the V-shaped clamping block 3.

[0043] The rigid flat plate spacecraft 1 adopts a high-rigidity flat plate structure, which is designed as a flat rectangular honeycomb plate structure. The outer contour size of the rigid flat plate spacecraft 1 is 300mm×2000mm×4000mm, which includes a bottom plate, a plurality of partition plates, and a side plate. The side plate is designed with a force block 2 connection interface, and the bottom of the rigid flat plate spacecraft 1 is designed with an interface connected with the connecting ring 5. The side of the rigid flat plate spacecraft 1 is fixedly provided with the force block 2, which adopts a metal T-shaped structure and is composed of a bottom surface, a vertical surface, and a flange structure 7 on the vertical surface. The width of each force block 2 is equal to or less than the width of the rigid flat plate spacecraft 1, and the vertical surface height of the force block 2 is designed within the range of 50-100mm. A plurality of force blocks 2 are spliced to form a circular ring, which is fixedly provided on the side of the rigid flat plate spacecraft 1. The force block 2 is installed on the side of the rigid flat plate spacecraft 1 through the interface of the bottom surface, and the bottom surface of the force block 2 has a width of 300mm consistent with the width of the rigid flat plate spacecraft 1, a thickness of 10mm, and a radial length of 150mm. A plurality of force blocks 2 form a complete circular ring on the side of the rigid flat plate spacecraft 1, and the diameter of the circular ring is 1500mm.

[0044] The circular ring is fixedly provided with a band 4, the band 4 is tightly arranged on the circular ring, and the band 4 adopts a metal circular ring structure. The circular rings are tightly connected by the pre-tightening force of the band 4, and the detailed design can be adaptively modified according to the number and width of the rigid flat plate spacecraft 1. The transmission block 2 is fixedly provided with a flange structure 7, the V-shaped clamping block 3 adopts a circular arc strip structure, the V-shaped clamping block 3 is fixedly provided with a groove, and the groove is correspondingly arranged with the flange structure 7. The vertical surface height of the transmission block 2 is 70 mm, and the outer surface of the transmission block 2 is designed with the flange structure 7, the flange structure 7 is consistent with the groove profile on the inner side of the V-shaped clamping block 3, the V-shaped clamping block 3 is embedded at the joint position of adjacent transmission blocks 2, and the transverse sliding of the transmission blocks 2 is prevented.

[0045] The bottom surface of the rigid flat plate spacecraft 1 is connected and arranged with a cylindrical pin 12, the cylindrical pin 12 is connected and arranged with the connecting ring 5, the bottom surface of the rigid flat plate spacecraft 1 is connected and arranged with the connecting ring 5 through the cylindrical pin 12, the connecting ring 5 adopts a metal ring-shaped thin-walled structure, the connecting ring 5 is connected and arranged with the rigid flat plate spacecraft 1 and the final stage of the carrier, and the bottom surface of the rigid flat plate spacecraft 1 is connected and arranged with the final stage of the carrier through the connecting ring 5. The connecting ring 5 is connected and arranged with a pull rod 6, and the pull rod 6 is connected and arranged with the band 4, and the band 4 is arranged outside the rotation shaft of the pull rod 6 by swinging around the pull rod 6.

[0046] After the band 4 is unlocked and separated from the rigid flat plate spacecraft 1, the band 4 re-enters the atmosphere together with the connecting ring 5. A new type of connection mode is designed for the vertical or inclined layout requirement of the rigid flat plate spacecraft 1, the main bearing column structure form commonly used in the past is cancelled, and the effective utilization rate of the carrying space is improved. The number of the rigid flat plate spacecraft 1 is arranged to be between 20-30, the vertical plane size of the rigid flat plate spacecraft 1 is arranged to be within the range of 5000mm*5000mm, and the width of the rigid flat plate spacecraft 1 is arranged to be within the range of 200-1000mm, and the detailed design can be adaptively modified according to the fairing size and load requirement.

[0047] The band 4 is fixedly provided with a spring 10, the band 4 includes an outer ring 9 and an inner ring 8, the inner ring 8 of the band 4 is circumscribed on the outer surfaces of the plurality of V-shaped clamping blocks 3, the outer ring 9 of the band 4 is designed with an interface at a corresponding position and is connected and arranged with the pull rod 6, and the outer ring 9 is connected and arranged with the inner ring 8 through the spring 10. The two sides of the rigid flat plate spacecraft 1 are composed of four circular ring structures by a plurality of transmission blocks 2, the band 4 is installed on the V-shaped clamping block 3, the tight connection between the adjacent transmission blocks 2 is realized by applying a pre-tightening force, and then the tight connection between the plurality of rigid flat plate spacecrafts 1 is realized.

[0048] After the rigid flat spacecraft 1 is in orbit, the unlocking device 11 is unlocked, the whole bandage 4 is separated from the rigid flat spacecraft 1, the adjacent force blocks 2 are separated, and the adjacent rigid flat spacecraft 1 are no longer fastened and connected. The unlocking device 11 is fixedly arranged on the bandage 4, the unlocking device 11 is symmetrically arranged left and right, the simultaneous unlocking of the plurality of rigid flat spacecraft 1 is realized, the reliability of the unlocking process is improved, and the risk is reduced. The pre-tightening force is applied on the inner ring 8 of the bandage 4 in the launch section, when the rigid flat spacecraft 1 needs to be separated in the stable flight in orbit, the unlocking device 11 is unlocked, the pull rod 6 takes the outer ring 9, the spring 10 and the inner ring 8 of the bandage 4 and re-enters the atmosphere together with the carrier final stage. The spacecraft connection and unlocking form in the scheme is also applicable to the spacecraft in the oblique layout.

[0049] In the description of the present application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like indicate the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, therefore cannot be understood as a limitation on the present application.

[0050] The specific embodiments of the present application are described above. It should be understood that the present application is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which does not affect the essential content of the present application. In the case of no conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims

1. A spacecraft structure suitable for rigid panel vertical configuration, characterized by, It includes rigid flat spacecraft (1), force block (2), V-shaped block (3) and band (4); The force block (2) is connected with the rigid flat spacecraft (1), and the force block (2) is arranged by pressing the rigid flat spacecraft (1) through the band (4); The connecting ring (5) is fixedly arranged on the rigid flat spacecraft (1); The V-shaped block (3) is fixedly arranged on the force block (2), and the V-shaped block (3) limits the force block (2); The V-shaped block (3) is fixedly arranged on the outside of the band (4); The side of the rigid flat spacecraft (1) is fixedly provided with the force block (2), the force block (2) adopts a metal T-shaped structure, a plurality of the force block (2) are arranged in a ring, and the ring is fixedly arranged on the side of the rigid flat spacecraft (1); The band (4) is fixedly arranged on the ring, the band (4) is arranged by pressing the ring, and the band (4) adopts a metal ring structure.

2. The spacecraft structure suitable for rigid flat vertical layout according to claim 1, wherein the rigid flat spacecraft (1) adopts a high-rigidity flat structure, and the high-rigidity flat structure is arranged as a flat cuboid honeycomb plate structure.

3. The spacecraft structure suitable for rigid panel vertical layout according to claim 1, characterized in that, The flange structure (7) is fixedly arranged on the force block (2); the V-shaped block (3) adopts a circular arc strip structure, the V-shaped block (3) is fixedly provided with a groove, and the groove is arranged correspondingly with the flange structure (7).

4. The spacecraft structure suitable for rigid panel vertical layout according to claim 1, characterized in that, The bottom of the rigid flat spacecraft (1) is connected with the cylindrical pin (12), the cylindrical pin (12) is connected with the connecting ring (5), the bottom of the rigid flat spacecraft (1) is connected with the connecting ring (5) through the cylindrical pin (12), the connecting ring (5) adopts a metal ring-shaped thin-walled structure, and the bottom of the rigid flat spacecraft (1) is connected with the final stage through the connecting ring (5).

5. The spacecraft structure suitable for rigid panel vertical layout according to claim 4, characterized in that, The pull rod (6) is connected with the connecting ring (5), and the pull rod (6) is connected with the band (4); the band (4) is arranged outside the rotation shaft of the pull rod (6) by swinging around the pull rod (6).

6. The spacecraft structure suitable for rigid panel vertical configuration according to claim 1, characterized in that, The number of the rigid flat spacecraft (1) is arranged to be 20-30, the vertical plane size of the rigid flat spacecraft (1) is arranged to be 5000mm*5000mm, and the width of the rigid flat spacecraft (1) is arranged to be 200-1000mm.

7. The spacecraft structure suitable for rigid panel vertical layout according to claim 5, characterized in that, The spring (10) is fixedly arranged on the band (4), the band (4) comprises an outer ring (9) and an inner ring (8), the outer ring (9) is connected with the inner ring (8) through the spring (10); the inner ring (8) is connected with the V-shaped block (3), and the inner ring (8) is arranged to circumscribe the outer surface of the V-shaped block (3); the middle part and the top part of the pull rod (6) are arranged correspondingly with the corresponding positions of the outer ring (9), and the interface is fixedly arranged on the outer ring (9) and connected with the pull rod (6).

8. The spacecraft structure suitable for rigid panel vertical layout according to claim 1, characterized in that, The bandage (4) is fixedly provided with an unlocking device (11), and the unlocking device (11) is symmetrically arranged left and right.

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