Satellite-rocket separation surface structural plate

Abstract

The invention relates to the technical field of aerospace equipment, in particular to a satellite-rocket separation surface structural plate which comprises a plate body, a connecting piece, four reinforcing ribs and four satellite-rocket butt joint surface embedded parts, and the connecting piece, the four reinforcing ribs and the four satellite-rocket butt joint surface embedded parts are all located in the plate body. The four satellite-rocket butt joint surface embedded parts are arranged at the positions of the four corners of the plate body in a one-to-one correspondence mode, the two ends of each reinforcing rib are a first connecting end and a second connecting end respectively, all the first connecting ends are connected with all the satellite-rocket butt joint surface embedded parts in a one-to-one correspondence mode, and all the second connecting ends are connected with the connecting parts. The invention aims to provide the satellite-rocket separation surface structural plate for solving the technical problems in the prior art.

Description

Technical Field

[0001] This application relates to the field of aerospace equipment technology, and more specifically, to a star-rocket separation surface structure plate. Background Technology

[0002] The satellite-launch separation surface is the interface between the satellite and the launch vehicle, containing critical mechanical interfaces. Formed on the separation surface structure plate (usually the separation plate on the satellite side), its structural performance directly affects the safety and reliability of the launch mission. The separation surface structure plate must withstand multiple core functions: during launch, it must bear enormous axial loads (thrust, overload), lateral loads (vibration, bending moment), and separation impact loads. It must possess extremely high strength and stiffness to ensure structural integrity. Furthermore, spacecraft are extremely sensitive to weight; the separation plate, while meeting strength and stiffness requirements, must be as lightweight as possible to maximize payload capacity. In other words, the separation surface structure plate must simultaneously possess load-bearing and force-transfer capabilities, as well as lightweight design. Summary of the Invention

[0003] The purpose of this application is to provide a star-rocket separation surface structure plate to address at least one of the technical problems involved in the background art.

[0004] To achieve the above objectives, this application adopts the following technical solution: One aspect of this application provides a star-rocket separation surface structure plate, including a plate body, and connectors, four reinforcing ribs, and four star-rocket docking surface embedded parts all located within the plate body. The four star-rocket docking surface embedded parts are correspondingly disposed at the four corners of the plate body. The two ends of the reinforcing ribs are respectively a first connecting end and a second connecting end. Each first connecting end is correspondingly connected to each star-rocket docking surface embedded part, and each second connecting end is connected to the connector. The star-rocket docking surface is disposed on the star-rocket docking surface embedded part, and the plate body is a honeycomb core.

[0005] Optionally, the star-rocket separation surface structure plate provided in this application further includes an aluminum skin, and both sides of the plate are covered with the aluminum skin.

[0006] The beneficial effects of this technical solution are that the aluminum skin can protect the internal honeycomb core and improve the shear strength of the star-rocket separation surface structure plate.

[0007] Optionally, the cross-section of the reinforcing rib is I-shaped, the reinforcing rib is mechanically connected to and bonded to the connector, and the reinforcing rib is mechanically connected to and bonded to the embedded part of the star-rocket docking surface.

[0008] The beneficial effects of this technical solution are as follows: the cross-section of the reinforcing rib is I-shaped, which not only gives the reinforcing rib sufficient rigidity and strength, but also makes the reinforcing rib lighter in weight; the reinforcing rib and the connector and the embedded part of the star-rocket docking surface adopt a composite connection method of mechanical connection and adhesive bonding, which improves the reliability of the connection. Optionally, a transverse rib fixed to the reinforcing rib is provided inside the reinforcing rib.

[0009] The beneficial effect of this technical solution is that the strength of the reinforcing rib can be improved by setting this transverse rib.

[0010] Optionally, the connector is cylindrical, and its axial direction is perpendicular to the plate. The positions where the reinforcing ribs connect to the connector are distributed in the circumferential direction of the connector.

[0011] The beneficial effects of this technical solution are as follows: the cylindrical connectors can effectively connect the four reinforcing ribs together, increasing the structural connection strength between the reinforcing ribs and strengthening the structural plate.

[0012] Optionally, an annular groove is formed on the outer periphery of the connector, the annular groove extending circumferentially along the connector, and each of the second connecting ends extends into the annular groove.

[0013] The beneficial effect of this technical solution is that by setting the annular groove, the weight of the connector can be reduced, thereby reducing the weight of the star-rocket separation surface structure plate.

[0014] Optionally, the embedded part of the star-rocket docking surface is block-shaped, and a weight-reducing groove is provided on the embedded part of the star-rocket docking surface.

[0015] The beneficial effects of this technical solution are as follows: the block-shaped satellite-rocket docking surface embedded part has greater rigidity and strength; the weight-reducing groove on the satellite-rocket docking surface embedded part reduces its weight, thereby reducing the weight of the satellite-rocket separation surface structural plate. By making the cross-section of the reinforcing ribs I-shaped and providing weight-reducing grooves on the satellite-rocket docking surface embedded part, the weight is effectively reduced while improving the effective payload and effective launch efficiency, thus reducing the satellite launch cost.

[0016] Optionally, an installation groove is formed on the embedded part of the star-rocket docking surface, and each of the first connecting ends extends into the installation groove and is fixedly connected to the embedded part of the star-rocket docking surface.

[0017] The beneficial effects of this technical solution are that by setting the mounting groove, the weight of the embedded part of the star-rocket docking surface is reduced, and the assembly and connection between the embedded part of the star-rocket docking surface and the reinforcing rib is facilitated.

[0018] Optionally, a limit switch pressing surface and a separation spring pressing surface are also provided on the embedded part of the star-rocket docking surface. The star-rocket docking surface, the limit switch pressing surface and the separation spring pressing surface are all processed last when assembling the star-rocket separation surface structure plate.

[0019] The beneficial effects of this technical solution are as follows: it avoids the accumulated errors caused by separately manufacturing and processing the star-rocket docking surface, the limit switch pressure surface, and the separation spring clamping surface of the embedded parts of the star-rocket docking surface before assembling the star-rocket separation surface structure plate. It significantly improves the overall flatness and positional tolerance of these key functional areas, such as the star-rocket docking surface, the limit switch pressure surface, and the separation spring clamping surface, meeting the stringent requirements of star-rocket separation for ultra-high flatness and precise positioning, and ensuring the reliability and accuracy of separation.

[0020] Another aspect of this application provides a satellite, including the star-rocket separation surface structure plate provided in this application.

[0021] The technical solution provided in this application can achieve at least one of the following beneficial effects: The satellite-rocket separation surface structure plate and satellite provided in this application use a honeycomb core to make the plate lighter. Placing the satellite-rocket docking surface on the embedded parts of the satellite-rocket docking surface can improve the strength at the docking surface. The four reinforcing ribs are connected by connectors to form a radial structure, which in turn forms an effective force transmission path. It can evenly distribute the concentrated load to the entire plate and the embedded parts of the satellite-rocket docking surface at the four corners, increasing the overall strength of the satellite-rocket separation surface structure plate and resisting the impact load during the rocket launch phase. In this way, the satellite-rocket separation surface structure plate has the functions of load bearing, force transmission, and lightweight.

[0022] The additional technical features and advantages of this application will become more apparent from the following description or from practical application. Attached Figure Description

[0023] To more clearly illustrate the technical solutions of the specific embodiments of this application, the accompanying drawings used in the description of the specific embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are some embodiments of this application. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0024] Figure 1 A top view schematic diagram of one embodiment of the star-rocket separation surface structure plate provided in this application; Figure 2 A partial three-dimensional structural schematic diagram of one embodiment of the star-rocket separation surface structure plate provided in this application; Figure 3This is a partial three-dimensional structural diagram of one embodiment of the star-rocket separation surface structure plate provided in this application.

[0025] Figure label: 01. Embedded parts for the star-rocket docking surface; 02. Mounting groove; 03. Star-rocket docking surface; 04. Aluminum skin; 05. Reinforcing ribs; 06. Connecting parts; 07. Annular groove; 08. Horizontal rib; 09. Second connection end; 10. First connection end. Detailed Implementation

[0026] The technical solutions of this application will now be clearly and completely described with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this application. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0027] In the description of this application, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0028] In the description of this application, it should be noted that, unless otherwise expressly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection between two components. Those skilled in the art can understand the specific meaning of the above terms in this application based on the specific circumstances.

[0029] like Figures 1 to 3As shown, one aspect of this application provides a star-rocket separation surface structure plate, including a plate body, and connectors 06, four reinforcing ribs 05, and four star-rocket docking surface embedded parts 01 all located within the plate body. The four star-rocket docking surface embedded parts 01 are respectively disposed at the four corners of the plate body. The two ends of the reinforcing ribs 05 are respectively a first connecting end 10 and a second connecting end 09. Each first connecting end 10 is connected to each star-rocket docking surface embedded part 01, and each second connecting end 09 is connected to the connector 06. The star-rocket docking surface 03 is disposed on the star-rocket docking surface embedded part 01, and the plate body is a honeycomb core.

[0030] In this embodiment of the application, preferably, the honeycomb core is made of aluminum, with a thickness of 24.4 mm and a density of 27 kg / m³. 3 It is much smaller than the 2700 kg / m³ of aluminum alloy. 3 The honeycomb core is embedded with titanium alloy embedded parts for installing equipment. The embedded part 01 of the star-rocket docking surface is preferably made of titanium alloy and is integrated with the plate through a co-curing process.

[0031] The rocket-satellite separation surface structure plate provided in this application uses a honeycomb core to make the plate lighter. Setting the rocket-satellite docking surface 03 on the rocket-satellite docking surface embedded part 01 can improve the strength at the rocket-satellite docking surface 03. The four reinforcing ribs 05 are connected by connectors 06 to form a radial structure, thereby forming an effective force transmission path. It can evenly distribute the concentrated load to the entire plate and the rocket-satellite docking surface embedded parts 01 at the four corners, increasing the overall strength of the rocket-satellite separation surface structure plate and resisting the impact load during the rocket launch stage. In this way, the rocket-satellite separation surface structure plate has the functions of load bearing, force transmission, and lightweight.

[0032] Optionally, the star-rocket separation surface structure plate provided in this embodiment further includes an aluminum skin 04, with both sides of the plate covered by the aluminum skin 04. In this way, the aluminum skin 04 can protect the internal honeycomb core and improve the shear strength of the star-rocket separation surface structure plate. Preferably, the aluminum skin 04 is cured and connected by adhesive bonding.

[0033] Optionally, the reinforcing rib 05 has an I-shaped cross-section. The reinforcing rib 05 is mechanically connected to and bonded to the connector 06, and also mechanically connected to and bonded to the embedded part 01 of the star-rocket docking surface. The I-shaped cross-section of the reinforcing rib 05 provides sufficient rigidity and strength while reducing its weight. The combined mechanical and adhesive connection between the reinforcing rib 05 and both the connector 06 and the embedded part 01 improves the reliability of the connection. Preferably, the mechanical connection is a bolted connection. Optionally, a transverse rib 08 fixed to the reinforcing rib 05 is provided within the reinforcing rib 05. By providing this transverse rib 08, the strength of the reinforcing rib 05 can be improved.

[0034] Optionally, the connector 06 is cylindrical, and its axial direction is perpendicular to the plate. The connections between each reinforcing rib 05 and the connector 06 are distributed circumferentially on the connector 06. The cylindrical connector 06 effectively connects the four reinforcing ribs 05 together, increasing the structural connection strength between the reinforcing ribs 05 and strengthening the structural plate. In this embodiment, preferably, the dimensional relationship between the connector 06 and the reinforcing ribs 05 satisfies the following formula: , Where D is the diameter of connector 06, L is the length of reinforcing rib 05, B is the width of reinforcing rib 05, and H is the height of reinforcing rib 05.

[0035] Optionally, an annular groove 07 is formed on the outer periphery of the connector 06, extending circumferentially along the connector 06, with each of the second connecting ends 09 extending into the annular groove 07. By providing the annular groove 07, the weight of the connector 06 can be reduced, thereby reducing the weight of the star-rocket separation surface structure plate. The connection between each reinforcing rib 05 and the connector 06 avoids the situation where multiple reinforcing ribs 05 intersect and break each other, while also ensuring the connection strength of the reinforcing ribs 05.

[0036] Optionally, the satellite-rocket docking surface embedded part 01 is block-shaped, and a weight-reducing groove is provided on the satellite-rocket docking surface embedded part 01. The block-shaped satellite-rocket docking surface embedded part 01 has greater rigidity and strength. The weight-reducing groove on the satellite-rocket docking surface embedded part 01 reduces the weight of the satellite-rocket docking surface embedded part 01, thereby reducing the weight of the satellite separation surface structural plate. By making the cross-section of the reinforcing rib 05 I-shaped and providing a weight-reducing groove on the satellite-rocket docking surface embedded part 01, the weight is effectively reduced while improving the effective payload and effective launch efficiency, thus reducing the satellite launch cost.

[0037] Optionally, a mounting groove 02 is formed on the embedded part 01 of the star-rocket docking surface, and each of the first connecting ends 10 extends into the mounting groove 02 and is fixedly connected to the embedded part 01 of the star-rocket docking surface. By setting the mounting groove 02, the weight of the embedded part 01 of the star-rocket docking surface is reduced, and the assembly connection between the embedded part 01 of the star-rocket docking surface and the reinforcing rib 05 is facilitated.

[0038] Optionally, a limit switch pressing surface and a separation spring clamping surface are also provided on the embedded part 01 of the star-rocket docking surface. The star-rocket docking surface 03, the limit switch pressing surface, and the separation spring clamping surface are all processed last when assembling the star-rocket separation surface structure plate. This avoids the accumulated errors caused by separately manufacturing and processing the star-rocket docking surface 03, the limit switch pressing surface, and the separation spring clamping surface of the embedded part 01 before assembling the star-rocket separation surface structure plate. It significantly improves the overall flatness and positional tolerance of these key functional areas, such as the star-rocket docking surface 03, the limit switch pressing surface, and the separation spring clamping surface, meeting the stringent requirements of ultra-high flatness and precise positioning for star-rocket separation, and ensuring the reliability and accuracy of separation. In the embodiments of this application, the overall flatness of these key functional areas is better than 0.1 mm, and the positional tolerance is better than 0.1 mm.

[0039] Another aspect of this application provides a satellite, including the star-rocket separation surface structure plate provided in the embodiments of this application.

[0040] The satellite provided in this application adopts the satellite-rocket separation surface structure plate provided in this application. The plate body adopts a honeycomb core to make the satellite-rocket separation surface structure plate lighter. Setting the satellite-rocket docking surface 03 on the satellite-rocket docking surface embedded part 01 can improve the strength at the satellite-rocket docking surface 03. The four reinforcing ribs 05 are connected by connectors 06 to form a radial structure, thereby forming an effective force transmission path. It can evenly distribute the concentrated load to the entire plate body and the satellite-rocket docking surface embedded parts 01 at the four corners, increasing the overall strength of the satellite-rocket separation surface structure plate and resisting the impact load during the rocket launch stage. In this way, the satellite-rocket separation surface structure plate has the functions of load bearing, force transmission, and lightweight.

[0041] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of this application, and are not intended to limit them. Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of this application.

Claims

1. A star-rocket separation surface structure plate, characterized in that, The plate includes a plate body, as well as connectors, four reinforcing ribs, and four star-and-arrow docking surface embedded parts all located within the plate body. The four star-and-arrow docking surface embedded parts are respectively located at the four corners of the plate body. The two ends of the reinforcing ribs are a first connecting end and a second connecting end, respectively. Each first connecting end is connected to each star-and-arrow docking surface embedded part, and each second connecting end is connected to the connector. The star-and-arrow docking surface is set on the star-and-arrow docking surface embedded part. The plate body is a honeycomb core.

2. The star-rocket separation surface structure plate according to claim 1, characterized in that, It also includes an aluminum skin, which covers both sides of the plate.

3. The star-rocket separation surface structure plate according to claim 1, characterized in that, The reinforcing rib has an I-shaped cross-section. The reinforcing rib is mechanically connected to the connecting member and bonded with adhesive. The reinforcing rib is also mechanically connected to the embedded part of the star-rocket docking surface and bonded with adhesive.

4. The star-rocket separation surface structure plate according to claim 3, characterized in that, A transverse rib fixed to the reinforcing rib is provided inside the reinforcing rib.

5. The star-rocket separation surface structure plate according to claim 3, characterized in that, The connector is cylindrical, and its axial direction is perpendicular to the plate. The positions where the reinforcing ribs connect to the connector are distributed in the circumferential direction of the connector.

6. The star-rocket separation surface structure plate according to claim 5, characterized in that, An annular groove is formed on the outer periphery of the connector, the annular groove extends circumferentially along the connector, and each of the second connecting ends extends into the annular groove.

7. The star-rocket separation surface structure plate according to claim 1, characterized in that, The embedded part of the star-rocket docking surface is block-shaped, and a weight reduction groove is provided on the embedded part of the star-rocket docking surface.

8. The star-rocket separation surface structure plate according to claim 7, characterized in that, An installation groove is formed on the embedded part of the star-rocket docking surface, and each of the first connecting ends extends into the installation groove and is fixedly connected to the embedded part of the star-rocket docking surface.

9. The star-rocket separation surface structure plate according to any one of claims 1 to 8, characterized in that, The embedded part of the star-rocket docking surface is also provided with a limit switch pressing surface and a separation spring pressing surface. The star-rocket docking surface, the limit switch pressing surface and the separation spring pressing surface are all processed last when assembling the star-rocket separation surface structure plate.

10. A satellite, characterized in that, Includes the star-rocket separation surface structure plate as described in any one of claims 1 to 9.

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