Laminating and pressing device of large-scale deployable phased-array antenna

Abstract

The invention discloses a stacking and pressing device for a large-scale deployable phased-array antenna. The stacking and pressing device comprises a split type shell assembly, a wrapping tape, a deployable hinge, an explosive bolt, a deployable planar phased-array antenna and a satellite platform, in the pressing state, the wrapping tape is arranged on the outer side of the split type shell assembly in a sleeving mode, the split type shell assembly is pressed, and the split type shell assembly is made to be in the folded state. The deployable planar phased-array antenna is in a folded state and is located in the split shell assembly in the folded state; the explosive bolt is arranged on the belting to lock the belting; the bottom of the split type shell assembly is hinged to the satellite platform through an unfolding hinge. According to the invention, the problem of vibration suppression is fundamentally solved, the risk of overhigh local stress on the surface of the large-scale deployable phased-array antenna is greatly reduced through uniform contact compression, and the unification of compression rigidity and structural protection is realized; and a reliable technical approach is provided for safe transportation and emission of the large-scale deployable phased-array antenna.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of spacecraft structure design, and particularly relates to a layering and compacting device for a large deployable phased array antenna. BACKGROUND

[0002] A large deployable phased array antenna is a key load of contemporary communication satellites, remote sensing observation satellites and other spacecraft. In order to adapt to the strict envelope size limit of a launch vehicle fairing, such an antenna must be in a folded state before being launched into orbit, that is, a plurality of large panels are folded into a composite structure of a multi-layered flat plate tightly stacked through an unfolding hinge and other mechanisms. This structure usually has the characteristics of large mass, complex structure, multiple internal interfaces and low overall stiffness. During the rocket launch phase, the spacecraft will be subjected to severe mechanical loads, which can easily induce damage and performance degradation of the precision structure due to friction, collision and the like. In addition, the insufficient overall stiffness of the large deployable phased array antenna in the folded state can cause its natural frequency to fall within the excitation frequency band of the rocket vibration, causing structural resonance, which can lead to excessive local stress or permanent damage to the structure.

[0003] The current commonly used large deployable phased array antenna fixing and protection measures are still relatively traditional. Common methods include using a binding belt for lashing or filling a soft material in the gap around the carrier. The former is simple and easy to implement, but it is difficult to accurately control the pre-tightening force, which can cause the binding belt structure to relax and fail under high frequency conditions. The latter provides flexible support force through soft material filling in the gap, and the compacting stiffness is severely insufficient, which cannot effectively suppress the structure vibration. SUMMARY

[0004] The technical problem of the present application is to overcome the shortcomings of the prior art and provide a layering and compacting device for a large deployable phased array antenna, which has the characteristics of strong compacting rigidity, good protection and high reliability, improves the structural stiffness, can effectively resist external impact, and can realize the fixation and protection of the large deployable phased array antenna during transportation, storage and launch phases.

[0005] To solve the above technical problems, the present application discloses a layering and compacting device for a large deployable phased array antenna, comprising: a split type shell assembly, a wrapping belt, an unfolding hinge, an explosive bolt, a deployable planar phased array antenna and a satellite platform. The deployable planar phased array antenna is installed on the satellite platform. In the compacted state, the wrapping belt is sleeved outside the split type shell assembly to compact the split type shell assembly, so that the split type shell assembly is in a folded state. The deployable planar phased array antenna is in a folded state and located in the split type shell assembly in the folded state. The explosive bolt is arranged on the wrapping belt to lock the wrapping belt. The bottom of the split type shell assembly is hinged to the satellite platform through the unfolding hinge.

[0006] In the above large deployable phased array antenna's laminated compression device, the split shell assembly includes four identical compression shells; in the compressed state, the four compression shells are in the folded state under the constraint of the wrapping belt.

[0007] In the above large deployable phased array antenna's laminated compression device, the deployment hinge is a single-axis rotation deployment hinge, and the deployment angle is 0°-90°.

[0008] In the above large deployable phased array antenna's laminated compression device, the deployment process is as follows: the explosive bolt is unlocked, the constraint on the wrapping belt is released; the wrapping belt is separated, the constraint on the four compression shells is released; the compression shells are separated from the deployable planar phased array antenna and rotate around the deployment hinge until the planar angle of the deployment hinge is 90°.

[0009] In the above large deployable phased array antenna's laminated compression device, the end surface A of the satellite platform and the split shell assembly is a square, and the circumscribed circle of the square end surface A is consistent with the shape of the bottom surface of the split shell assembly in the folded state.

[0010] In the above large deployable phased array antenna's laminated compression device, the end surface A is provided with a mounting hole A; the bottom of each compression shell is provided with a mounting hole B; the deployment hinge realizes the articulation of each compression shell and the end surface A of the satellite platform through the mounting hole A and the mounting hole B.

[0011] In the above large deployable phased array antenna's laminated compression device, the inner wall of each compression shell is provided with a plurality of ball sockets; the outer surface of the deployable planar phased array antenna is provided with a plurality of spherical limiting structures; wherein the number of ball sockets and spherical limiting structures is consistent, the positions correspond, and the sizes match; in the compressed state, the spherical limiting structures are located in the ball sockets to prevent relative movement between the compression shell and the deployable planar phased array antenna.

[0012] In the above large deployable phased array antenna's laminated compression device, the wrapping belt is a separable circular ring structure, and the surface is provided with a mounting hole C for mounting the explosive bolt.

[0013] In the above large deployable phased array antenna's laminated compression device, the wrapping belt is any one of a separable annular clamp, a winding compression belt and a heat shrinkable sleeve.

[0014] In the above large deployable phased array antenna's laminated compression device, the number of wrapping belts is one or more.

[0015] The present application has the following advantages: (1) The application discloses a laminated pressing device for a large deployable phased array antenna, fundamentally solves the problem of vibration suppression, greatly reduces the risk of excessive local stress on the surface of the large deployable phased array antenna through uniform contact pressing, realizes the unity of pressing rigidity and structural protection, and provides a reliable technical approach for safe transportation and launching of the large deployable phased array antenna.

[0016] (2) The application discloses a laminated pressing device for a large deployable phased array antenna, four pressing housings are consistent in shape, and the folded shape under the pressing state is a circumscribed circle of the pressed square satellite platform, so that the pressing force is uniformly distributed on the pressed surface.

[0017] (3) The application discloses a laminated pressing device for a large deployable phased array antenna, which is simple in structure, simple in operation process and reusable.

[0018] (4) The application discloses a laminated pressing device for a large deployable phased array antenna, which is independent of the specific size and layer number of the large deployable phased array antenna and can adapt to different products by adjusting the frame and the pressing housing. BRIEF DESCRIPTION OF DRAWINGS

[0019] Figure 1 is a structural schematic diagram of a laminated pressing device for a large deployable phased array antenna in a pressing state according to an embodiment of the application; Figure 2 is a connection schematic diagram among a split type shell assembly, a deployment hinge and a satellite platform in a pressing state according to an embodiment of the application; Figure 3 is a structural schematic diagram of a laminated pressing device for a large deployable phased array antenna in an unfolded state according to an embodiment of the application. DETAILED DESCRIPTION

[0020] In order to make the purpose, technical scheme and advantages of the application more clear, the following will further describe the disclosed embodiments of the application in combination with the drawings.

[0021] The application discloses a laminated pressing device for a large deployable phased array antenna, proposes a concept design of active rigidization from inside to outside, and realizes pressing of the carrier. First, a rigid frame accurately controllable inside is used to apply uniformly distributed pressing force to the side surface of the large deployable phased array antenna. Further, an annular pressing member outside is used for overall reinforcement, forming a double insurance mechanism. The design fundamentally solves the problem of vibration suppression, greatly reduces the risk of excessive local stress on the surface of the large deployable phased array antenna through uniform contact pressing, realizes the unity of pressing rigidity and structural protection, and provides a reliable technical approach for safe transportation and launching of the large deployable phased array antenna.

[0022] Referring to Figures 1-2 In the embodiment, the layering and compacting device of the large deployable phased array antenna comprises a split shell assembly, a wrapping belt 2, a deployment hinge 3, an explosive bolt 4, a deployable planar phased array antenna 5 and a satellite platform 6. The deployable planar phased array antenna 5 is installed on the satellite platform 6. In the compacted state, the wrapping belt 2 is wrapped outside the split shell assembly to compact the split shell assembly so that the split shell assembly is in the folded state. The deployable planar phased array antenna 5 is in the folded state and located in the split shell assembly in the folded state. The explosive bolt 4 is arranged on the wrapping belt 2 to lock the wrapping belt 2. The bottom of the split shell assembly is hinged to the satellite platform 6 through the deployment hinge 3.

[0023] In the embodiment, the split shell assembly comprises four compacting shells 1 with the same shape. The end surface A of the satellite platform 6 hinged to the split shell assembly is square, and the end surface A is provided with a mounting hole A. The bottom of each compacting shell 1 is provided with a mounting hole B. The deployment hinge 3 realizes the hinge connection of each compacting shell 1 and the end surface A of the satellite platform 6 through the mounting hole A and the mounting hole B.

[0024] In the embodiment, the deployment hinge 3 is a single-axis rotation deployment hinge, and the deployment angle is 0°-90°. In the compacted state, the four compacting shells 1 are in the folded state under the constraint of the wrapping belt 2. At this time, the plane angle of the deployment hinge 3 is 0°, and the bottom surface shape of the split shell assembly in the folded state is consistent with the circumscribed circle shape of the square end surface A. The deployment process is as follows: the explosive bolt 4 is unlocked to release the constraint of the wrapping belt 2; the wrapping belt 2 is separated to release the constraint of the four compacting shells 1; the compacting shell 1 is separated from the deployable planar phased array antenna 5 and rotates around the deployment hinge 3 until the plane angle of the deployment hinge 3 is 90°, as shown in FIG. 2. Figure 3

[0025] In the embodiment, the inner wall of each compacting shell 1 is provided with a plurality of ball sockets 8, and the outer surface of the deployable planar phased array antenna 5 is provided with a plurality of spherical limiting structures 7. The number of the ball sockets 8 and the spherical limiting structures 7 is consistent, the positions are corresponding, and the sizes are matched. In the compacted state, the spherical limiting structure 7 is located in the ball socket 8 to prevent the relative movement between the compacting shell 1 and the deployable planar phased array antenna 5.

[0026] In the embodiment, the wrapping belt 2 is a separable circular ring structure, and the surface is provided with a mounting hole C for mounting the explosive bolt 4. Preferably, the wrapping belt 2 is any one of the following types: a separable annular clamp, a winding compacting belt and a heat shrinkable sleeve. The number of the wrapping belt 2 is one or more.

[0027] ​In the embodiment, the compact housing 1 is made of high-strength light metal material (such as aluminum alloy, etc.).

[0028] Although the present application has been disclosed with reference to the preferred embodiments, it is not intended to limit the present application thereto, and any person skilled in the art can make possible changes and modifications to the technical solutions of the present application by using the disclosed methods and technical contents without departing from the spirit and scope of the present application. Therefore, any simple modification, equivalent change and modification made to the above embodiments according to the technical essence of the present application without departing from the technical solutions of the present application shall fall within the protection scope of the present application.

[0029] The contents not described in detail in the specification of the present application are known to the person skilled in the art.

Claims

1. A stacking and clamping device for a large deployable phased array antenna, characterized in that, include: The components include a split-type housing assembly, a strap (2), a deployable hinge (3), an explosive bolt (4), a deployable planar phased array antenna (5), and a satellite platform (6). The deployable planar phased array antenna (5) is mounted on the satellite platform (6). In the compressed state, the strap (2) is fitted onto the outside of the split-type housing assembly to compress the split-type housing assembly, so that the split-type housing assembly is in a closed state. The deployable planar phased array antenna (5) is in a retracted state and is located inside the split-type housing assembly in the closed state. The explosive bolt (4) is set on the strap (2) to lock the strap (2). The bottom of the split-type housing assembly is hinged to the satellite platform (6) through the deployable hinge (3).

2. The stacking and pressing device for a large deployable phased array antenna according to claim 1, characterized in that, The split housing assembly includes four identical compression shells (1); in the compression state, the four compression shells (1) are closed under the constraint of the straps (2).

3. The stacking and pressing device for a large deployable phased array antenna according to claim 2, characterized in that, The unfolding hinge (3) is a single-axis rotation unfolding hinge with an unfolding angle of 0°~90°.

4. The stacking and pressing device for a large deployable phased array antenna according to claim 3, characterized in that, The unfolding process is as follows: the explosive bolt (4) is unlocked, releasing the constraint on the strap (2); the strap (2) is separated, releasing the constraint on the four clamping shells (1); the clamping shell (1) is separated from the unfoldable planar phased array antenna (5) and rotates around the unfolding hinge (3) until the plane angle of the unfolding hinge (3) is 90°.

5. The stacking and pressing device for a large deployable phased array antenna according to claim 2, characterized in that, The end face A of the satellite platform (6) that is hinged to the split shell assembly is square, and the circumcircle of the square end face A is consistent with the shape of the bottom surface of the split shell assembly in the closed state.

6. The stacking and clamping device for a large deployable phased array antenna according to claim 5, characterized in that, Mounting hole A is provided on end face A; mounting hole B is provided at the bottom of each clamping shell (1); the unfolding hinge (3) realizes the hinge connection between each clamping shell (1) and end face A of the satellite platform (6) through mounting hole A and mounting hole B.

7. The stacking and pressing device for a large deployable phased array antenna according to claim 2, characterized in that, Several spherical sockets (8) are provided on the inner wall of each compression shell (1); several spherical limiting structures (7) are provided on the outer surface of the deployable planar phased array antenna (5); the number of spherical sockets (8) and spherical limiting structures (7) are the same, their positions are corresponding and their sizes are matched; in the compression state, the spherical limiting structures (7) are located in the spherical sockets (8) to prevent relative movement between the compression shell (1) and the deployable planar phased array antenna (5).

8. The stacking and pressing device for a large deployable phased array antenna according to claim 1, characterized in that, The strap (2) is a separable annular structure with mounting holes C on its surface for mounting the explosion bolts (4).

9. The stacking and clamping device for a large deployable phased array antenna according to claim 1, characterized in that, The strap (2) is any one of the following: a split ring clamp, a spiral compression strap, and a heat shrink collar.

10. The stacking and clamping device for a large deployable phased array antenna according to claim 1, characterized in that, The number of straps (2) is one or more.

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