Structure and method of installation with interface suitable for installation inside a load cartridge

Abstract

The application provides a structure and mounting method with an interface suitable for mounting in a load cylinder, comprising a central force bearing cylinder, a top surface compression ring and a bottom plate force bearing ring; wherein the central force bearing cylinder comprises a cylinder body, a force bearing cylinder upper end frame and a force bearing cylinder lower end frame; the top surface compression ring is arranged on the top of the force bearing cylinder upper end frame; and the bottom surface force bearing ring is arranged on the bottom of the force bearing cylinder lower end frame. The application adopts a double flange mounting precision control design, and on this basis, solves the mounting precision control and dismounting and resetting problems of the interface structure design of the double flange mounting in a large mass load cylinder, has three characteristics of high mounting precision, easy realization of dismounting and resetting and strong bearing capacity, meets the mounting requirements in a large mass load cylinder, and simultaneously has the characteristics of novel structure form and light mass, so as to guarantee the on-orbit operation effect of a satellite and improve the on-orbit operation stability.

Description

Technical Field

[0001] This invention relates to spacecraft structural products, specifically to a structure and installation method having an interface suitable for installation inside a payload cylinder. It is particularly suitable for installation inside a large-mass payload cylinder. Background Technology

[0002] Currently, the increasing functional requirements of satellites are placing ever higher demands on them, driving their development towards higher stability, higher precision, and higher resolution. This not only imposes higher performance requirements on large satellite payloads but also places more stringent demands on the mechanical environment, precision stability, and other aspects of the satellite platform structure during on-orbit operation. For payloads installed within the satellite's central load-bearing cylinder, the large size and high precision requirements of the loads mean that the stiffness, strength, and precision of the mounting interfaces significantly impact the functional performance of the payloads they support. Therefore, designing the interface structure for large-mass payloads installed within the cylinder to achieve connection strength, stiffness, and precision stability is a key focus and challenge in the collaborative design of large satellite structural platforms and payloads.

[0003] Conventional in-tube load installation designs typically employ a single-flange structure, with payload installation accuracy ensured through techniques such as locating pins and precision measurement. However, as the mass and size of satellite payloads increase, the installation interfaces manufactured and assembled using traditional methods are no longer sufficient to meet the installation requirements of new payloads in terms of local strength, stiffness, accuracy, and stability. Therefore, designing an interface structure for the in-tube installation of large-mass payloads for new large satellites, capable of simultaneously achieving installation accuracy control and stiffness strength design, has become a pressing issue in satellite structural assembly technology.

[0004] A search of existing technologies revealed that the interface structure for providing an internal single flange mounting plate for a data transmission antenna disclosed in patent document CN107323700A, and the interface structure for providing high rigidity and high stability for the load by using a single flange on the top of a satellite disclosed in patent document CN107600983A, are both single flange structures and cannot form a combination of main support and auxiliary support. Summary of the Invention

[0005] In view of the deficiencies in the prior art, the purpose of this invention is to provide a structure and installation method with an interface suitable for installation inside a load cell.

[0006] According to the present invention, a structure having an interface suitable for installation inside a load cell includes: a load-bearing cylinder 1, a top pressure ring 3, and a bottom load-bearing ring 4;

[0007] The top pressure ring 3 is set at the top of the load-bearing cylinder 1, and the bottom load-bearing ring 4 is set at the bottom of the load-bearing cylinder 1;

[0008] The bottom bearing ring 4 is provided with a guide positioning pin 8 and / or a precision reset pin 9 that extend upward along the axial direction.

[0009] Preferably, it also includes an internal load 2;

[0010] The internal load 2 is installed inside the load-bearing cylinder 1;

[0011] The load-bearing cylinder 1 provides load-bearing capacity to the load 2 inside the cylinder through the pressure ring 3 on the top surface;

[0012] The bottom bearing ring 4 provides load-bearing capacity for the load 2 inside the cylinder.

[0013] Preferably, the load-bearing cylinder 1 includes a cylinder body, an upper load-bearing cylinder frame 6, and a lower load-bearing cylinder frame 7;

[0014] The top pressure ring 3 is set at the top of the upper frame 6 of the load-bearing cylinder, and the bottom load-bearing ring 4 is set at the bottom of the lower frame 7 of the load-bearing cylinder.

[0015] The top pressure ring 3 provides an installation interface for the upper flange of the internal load 2, and the bottom bearing ring 4 provides an installation interface for the lower flange of the internal load 2; the force of the internal load 2 is distributed to the bottom bearing ring 4 and the upper end frame 6 of the bearing cylinder.

[0016] Preferably, the top pressure ring 3 is an integrated ring structure, including a high horizontal part, a high-low connecting part, and a low horizontal part;

[0017] The high-level horizontal section is an annular structure located above the load-bearing cylinder 1, and is connected to the load-bearing cylinder 1 radially outside through the upper end frame 6 of the load-bearing cylinder 1;

[0018] The lower horizontal section is an annular structure located inside the load-bearing cylinder 1, and the load 2 inside the cylinder is connected to the radial inner side of the load-bearing cylinder 1.

[0019] The high-low connection part is a ring structure, with the upper end connected to the inner edge of the high horizontal part and the lower end connected to the outer edge of the low horizontal part.

[0020] A gasket is provided between the high horizontal part and the upper frame 6 of the load-bearing cylinder.

[0021] Preferably, the bottom bearing ring 4 is an integrated ring structure, installed between the lower end frame 7 of the bearing cylinder located on the outer wall of the bearing cylinder 1 and the lower flange of the load 2 inside the cylinder, and is also connected to the satellite-rocket connection ring.

[0022] Preferably, the guide positioning pin 8 cooperates with the positioning hole at the bottom of the load 2 inside the cylinder to guide the load 2 inside the cylinder to move downward inside the load-bearing cylinder 1;

[0023] The precision reset pin 9 is connected to the pin hole at the bottom of the load 2 inside the cylinder;

[0024] The top of the guide positioning pin 8 is higher than the top of the precision reset pin 9; when the load 2 inside the cylinder moves downward, it first contacts the guide positioning pin 8.

[0025] According to the present invention, a satellite includes the aforementioned structure having an interface suitable for installation inside a payload cylinder;

[0026] The bottom bearing ring 4 is connected to the satellite-rocket connection ring.

[0027] An installation method for a structure having an interface suitable for installation inside a load cell, provided by the present invention, is characterized by comprising:

[0028] The lower flange is formed by the lower end frame 7 of the load-bearing cylinder that connects the bottom load-bearing ring 4 and the load-bearing cylinder 1.

[0029] The load 2 inside the cylinder is vertically hoisted from the top of the load-bearing cylinder 1 into the cylinder body of the load-bearing cylinder 1. After the installation accuracy is adjusted to the correct position by the guide positioning pin 8 and the precision reset pin 9, the load 2 inside the cylinder is connected to the bottom load-bearing ring 4 with screws.

[0030] Install the top pressure ring 3 to connect the upper end frame 6 of the load-bearing cylinder to the load 2 inside the cylinder, and transfer the force of the flange on the load 2 inside the cylinder to the load-bearing cylinder 1.

[0031] Preferably, if the top pressure ring 3 has a dimensional accuracy deviation in the vertical direction, the top pressure ring 3 shall be repaired or a shim shall be added.

[0032] Preferably, the load 2 inside the cylinder is installed into the load-bearing cylinder 1. When the distance between the lower flange of the load 2 inside the cylinder and the bottom load-bearing ring 4 is less than or equal to 50mm, it is guided to continue to move downward by the guide positioning pin 8, and the precision reset pin 9 is used to ensure the accuracy of load installation and repeated disassembly and assembly.

[0033] Compared with the prior art, the present invention has the following beneficial effects:

[0034] 1. The entire connection design adopts a double-flange installation method, with the lower flange serving as the main support and the upper flange as the auxiliary support. The longitudinal height can be finely adjusted during installation to allow for precision adjustment. The load is installed inside the load-bearing cylinder, with the top pressure ring providing the installation interface for the upper flange and the bottom load-bearing ring providing the installation interface for the lower flange.

[0035] 2. The load-bearing cylinder plays a major role in bearing the load, distributing the load inside the cylinder to the bottom load-bearing ring and the upper flange of the load-bearing cylinder, and directly transferring it to the star-rocket connection ring and the launch vehicle.

[0036] 3. The bottom bearing ring is equipped with a guide positioning pin, which facilitates the installation and repeated disassembly of the load inside the cylinder, while reducing the work of precision resetting.

[0037] 4. A precision reset pin is provided on the bottom bearing ring to meet the requirement of precision reset when the load is installed inside the cylinder and repeatedly disassembled. Attached Figure Description

[0038] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0039] Figure 1 This is a structural diagram of the present invention;

[0040] Figure 2 This is a cross-sectional view of the overall structure of the present invention;

[0041] Figure 3 This is a schematic diagram of the load-bearing cylinder of the present invention;

[0042] Figure 4 , Figure 5 These are schematic diagrams of the overall top surface pressure ring and the cross-section of the top surface pressure ring of the present invention;

[0043] Figure 6 , Figure 7 These are schematic diagrams of the overall bottom bearing ring and the cross-section of the bottom bearing ring of the present invention;

[0044] Figure 8 This is a schematic cross-sectional view of the top pressure ring, the upper frame of the load-bearing cylinder, and the load connection inside the cylinder of the present invention.

[0045] Figure 9 This is a schematic cross-sectional view of the bottom bearing ring, the lower end frame of the bearing cylinder, and the load connection inside the cylinder of the present invention.

[0046] Figure 10 This is a schematic cross-sectional view of the bottom bearing ring, the lower end frame of the bearing cylinder, the guide positioning pin, and the load connection inside the cylinder of the present invention.

[0047] Figure 11 This is a schematic cross-sectional view of the bottom bearing ring, the lower end frame of the bearing cylinder, the precision reset pin, and the load connection inside the cylinder of the present invention.

[0048] The diagram shows:

[0049] Detailed Implementation

[0050] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0051] This invention innovatively adopts a dual-flange installation precision control design. Based on this, it solves the problems of installation precision control and disassembly / reset of the interface structure design for dual-flange installation inside a large-mass payload cylinder. It has three characteristics: high installation precision, easy disassembly / reset, and strong load-bearing capacity. It meets the requirements for installation inside a large-mass payload cylinder. At the same time, it has the characteristics of novel structure and light weight, thereby ensuring the satellite's on-orbit operation effect and improving its on-orbit stability.

[0052] The present invention will now be described in detail. Please also refer to... Figures 1 to 11 .

[0053] This invention provides an interface structure design suitable for installation inside a load cell, particularly for installation inside a large-mass load cell. It includes a centrally located load-bearing cylinder 1, a top pressure ring 3, a bottom load-bearing ring 4, a guide positioning pin 8, and a precision reset pin 9. The load-bearing cylinder 1 includes a cylinder body, an upper load-bearing frame 6, and a lower load-bearing frame 7. The top pressure ring 3 is located on top of the upper load-bearing frame 6. Figure 10 As shown, the bottom bearing ring 4 is located at the bottom of the lower end frame 7 of the bearing cylinder. Figure 11 As shown, the guide positioning pin 8 is disposed on the bottom bearing ring 4; the precision reset pin 9 is disposed on the bottom bearing ring 4.

[0054] More specifically, in the interface structure design, the internal load 2 is installed inside the load-bearing cylinder 1, and the top pressure ring 3 provides an installation interface for the upper flange of the internal load 2, such as... Figure 8 As shown; the bottom bearing ring 4 provides an installation interface for the lower flange of the internal load 2, as... Figure 9 As shown in the diagram, in the interface structure design, the load-bearing cylinder 1 plays the main load-bearing role, distributing the force of the load 2 inside the cylinder to the bottom load-bearing ring 4 and the upper frame 6 of the load-bearing cylinder, and then transmitting it downwards to the star-rocket connection ring and the launch vehicle. The top pressure ring 3 is an integrated ring structure with an approximately Z-shaped cross-section, as shown in the diagram. Figure 5 As shown, two rings of mounting holes are provided, installed between the upper flange of the upper frame 6 of the load-bearing cylinder and the upper flange of the load 2 inside the cylinder; the top pressure ring 3 can be adjusted in height by adding shims or pads for adjusting the longitudinal installation accuracy. The bottom load-bearing ring 4 is an integrated ring structure with an approximately h-shaped cross-section, as shown... Figure 7 As shown, it is equipped with three rings of mounting holes, which are installed between the lower end frame 7 of the load-bearing cylinder and the lower flange of the load 2 inside the cylinder, and are also connected to the satellite-rocket connection ring; the bottom load-bearing ring 4 serves as the main force transmission component, which plays a force transmission role between the large mass load and the load-bearing cylinder 1, and finally transmits the force to the satellite-rocket connection ring.

[0055] For example Figure 10 , Figure 11As shown, the bottom bearing ring 4 is internally equipped with a guide positioning pin 8 and a precision reset pin 9. When the load 2 is installed into the bearing cylinder 1, and the lower flange of the load 2 is less than 50mm from the bottom bearing ring 4, it is guided downward by the guide positioning pin 8, and the precision reset pin 9 ensures the accuracy required for load installation and repeated disassembly / reassembly. Therefore, this invention solves the problems of installation accuracy control and disassembly / reset in the interface structure design for double flange installation of large-mass loads within a cylinder. It has three characteristics: high installation accuracy, easy disassembly / reset, and strong load-bearing capacity, meeting the requirements for installation of large-mass loads within a cylinder. It also features a novel structural form and relatively light weight.

[0056] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are 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.

[0057] The working principle of the present invention will be explained in more detail below.

[0058] When the present invention is in operation, firstly, the lower flange formed by the bottom bearing ring 4 and the lower end frame 7 of the bearing cylinder 1 is installed in place by screw connection; then, the internal load 2 is vertically hoisted from the top of the bearing cylinder 1 into the cylinder body of the bearing cylinder 1. After the installation accuracy is adjusted in place by the guide positioning pin 8 and the precision reset pin 9, the internal load 2 is screwed to the bottom bearing ring 4.

[0059] Next, the top pressure ring 3 is installed. If there is a dimensional accuracy deviation in the vertical direction of the top pressure ring 3, it can be repaired or shims can be added. The load-bearing cylinder 1, as the main load-bearing structure, plays the main load-bearing role. The bottom load-bearing ring 4 serves two purposes: firstly, as the main force transmission structure, it transfers the force of the load 2 inside the cylinder and the load-bearing cylinder 1 to the satellite-rocket connection ring; secondly, it serves as an installation reference, ensuring that the load is consistent with the satellite reference accuracy during installation. The top pressure ring 3 serves two purposes: firstly, as an auxiliary support structure, it transfers the force of the flange on the load 2 inside the cylinder to the load-bearing cylinder 1; secondly, it is used to adjust the installation accuracy of the load. Due to the reasonable structural and connection design of the entire device, the device has sufficient strength, rigidity, and accuracy stability, while also being relatively lightweight.

[0060] In summary, this invention innovatively adopts a dual-flange installation accuracy control design. Based on this, it solves the problems of installation accuracy control and disassembly / reset in the design of the installation interface structure for large-mass payloads inside the cylinder. It has three characteristics: high installation accuracy, easy disassembly / reset, and strong load-bearing capacity, which meets the requirements for installation of large-mass payloads inside the cylinder. At the same time, it has the characteristics of simple structure and light weight, thereby ensuring the satellite's on-orbit operation effect and improving its on-orbit stability.

[0061] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A structure having an interface suitable for installation inside a load cell, characterized in that, include: Support cylinder (1), top pressure ring (3), bottom support ring (4); The top pressure ring (3) is set at the top of the load-bearing cylinder (1), and the bottom load-bearing ring (4) is set at the bottom of the load-bearing cylinder (1); The bottom bearing ring (4) is provided with a guide positioning pin (8) and / or a precision reset pin (9) extending upward along the axial direction; It also includes the load inside the cylinder (2); The internal load (2) is installed inside the load-bearing cylinder (1); The load-bearing cylinder (1) provides load-bearing capacity to the load (2) inside the cylinder through the top pressure ring (3); The bottom bearing ring (4) provides load-bearing capacity for the load (2) inside the cylinder; The load-bearing cylinder (1) includes a cylinder body, an upper frame (6) of the load-bearing cylinder, and a lower frame (7) of the load-bearing cylinder; The top pressure ring (3) is set at the top of the upper frame (6) of the load-bearing cylinder, and the bottom load-bearing ring (4) is set at the bottom of the lower frame (7) of the load-bearing cylinder; The top pressure ring (3) provides an installation interface for the upper flange of the internal load (2), and the bottom bearing ring (4) provides an installation interface for the lower flange of the internal load (2); the force of the internal load (2) is distributed to the bottom bearing ring (4) and the upper end frame (6) of the bearing cylinder; The top pressure ring (3) is an integrated ring structure, including a high horizontal part, a high and low connecting part, and a low horizontal part; The high horizontal part is an annular structure located above the load-bearing cylinder (1), and is connected to the load-bearing cylinder (1) through the upper end frame (6) of the load-bearing cylinder on the radially outer side; The low horizontal part is an annular structure located inside the load-bearing cylinder (1), and the load (2) inside the cylinder is connected to the radial inner side of the load-bearing cylinder (1); The high-low connection part is a ring structure, with the upper end connected to the inner edge of the high horizontal part and the lower end connected to the outer edge of the low horizontal part. A gasket is provided between the high horizontal part and the upper end frame (6) of the load-bearing cylinder.

2. The structure with an interface suitable for installation inside a load cell according to claim 1, characterized in that, The bottom bearing ring (4) is an integrated ring structure, installed between the lower end frame (7) of the bearing cylinder located on the outer wall of the bearing cylinder (1) and the lower flange of the load (2) inside the cylinder, and is also connected to the satellite-rocket connection ring.

3. The structure with an interface suitable for installation inside a load cell according to claim 1, characterized in that, The guide positioning pin (8) cooperates with the positioning hole at the bottom of the cylinder load (2) to guide the cylinder load (2) to move downward in the load-bearing cylinder (1); The precision reset pin (9) is connected to the pin hole at the bottom of the inner load (2); The top of the guide positioning pin (8) is higher than the top of the precision reset pin (9); when the load (2) inside the cylinder moves downward, it first contacts the guide positioning pin (8).

4. A satellite, characterized in that, The structure includes any one of claims 1 to 3, having an interface suitable for installation inside a load cell; The bottom bearing ring (4) is connected to the satellite-rocket connection ring.

5. An installation method for a structure having an interface suitable for installation inside a load cell, as described in any one of claims 1 to 3, characterized in that, include: The lower flange is formed by the lower end frame (7) of the load-bearing cylinder that connects the bottom load-bearing ring (4) and the load-bearing cylinder (1); The load (2) inside the cylinder is vertically hoisted from the top of the load-bearing cylinder (1) into the cylinder body of the load-bearing cylinder (1). After the installation accuracy is adjusted to the correct position by the guide positioning pin (8) and the precision reset pin (9), the load (2) inside the cylinder is connected to the bottom load-bearing ring (4) with screws. Install the top pressure ring (3) to connect the upper end frame (6) of the load-bearing cylinder to the load inside the cylinder (2), and transfer the force of the flange on the load inside the cylinder (2) to the load-bearing cylinder (1).

6. The installation method of the structure having an interface suitable for installation inside a load cell according to claim 5, characterized in that, If there is a dimensional accuracy deviation in the vertical direction of the top pressure ring (3), the top pressure ring (3) shall be repaired or a gasket shall be added.

7. The installation method of the structure having an interface suitable for installation inside a load cell according to claim 6, characterized in that, When the load (2) inside the cylinder is installed into the bearing cylinder (1), and the distance between the lower flange of the load (2) inside the cylinder and the bottom bearing ring (4) is less than or equal to 50 mm, it is guided to continue to descend by the guide positioning pin (8) and the precision reset pin (9) is used to ensure the accuracy of the load during installation and repeated disassembly and assembly.

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