Space camera on-orbit servicing mechanism

Abstract

This invention relates to the field of on-orbit maintenance mechanisms, specifically providing an on-orbit maintenance mechanism for a space camera. The mechanism includes: a base, a moving block, roller blocks, a guide block, a magnet, and a Hall effect device. The base is connected to the main optical engine structure and has a square inner cavity. Four roller blocks are fixed to the four surfaces of the square inner cavity of the base with screws. The moving block is disposed within the square inner cavity through an interference fit with the roller blocks. The guide block is disposed at the front end of the base and serves to guide the moving block and roller blocks during docking. The magnet is disposed at the front end of the moving block, and a Hall effect device is correspondingly disposed at the front end of the base. The relative positional relationship between the moving block and the base is fed back through the interaction of the magnet and the Hall effect device. This invention achieves bidirectional high load-bearing capacity and unidirectional release degree of freedom, and has advantages such as high positioning accuracy, high reassembly repeatability, strong operability, simple structure, and low cost. It is particularly suitable for applications requiring high reset accuracy, high load-bearing capacity, and unidirectional release degree of freedom.

Description

Technical Field

[0001] This invention relates to the field of on-orbit maintenance mechanisms, and specifically provides an on-orbit maintenance mechanism for a space camera. Background Technology

[0002] The main function of the on-orbit maintenance mechanism for the space camera is to provide structural support for the back-end module. The specific support requirements include four aspects: First, reducing the thermal deformation coupling effect between the main optical engine structure and the back-end module structure during on-orbit operation; second, enabling on-orbit maintenance of the back-end module; third, having sufficient static stiffness and stability during ground assembly and testing to ensure the position of the back-end module relative to the main optical engine system under standard gravity (1g); and fourth, having sufficient dynamic stiffness and strength during the launch phase to provide stable and reliable structural support for the back-end module to resist the mechanical environment during the launch phase.

[0003] Existing on-orbit maintenance mechanisms for space cameras are unable to meet the above requirements, especially due to their low strength, poor stability, low reset accuracy, complex assembly and adjustment, and poor operability. Therefore, there is an urgent need for a motion mechanism with high reset accuracy and high load-bearing capacity suitable for on-orbit maintenance of the back-end modules of space cameras. Summary of the Invention

[0004] To address the aforementioned problems, this invention provides a detachable linear motion mechanism for on-orbit maintenance of a space camera with bidirectional high load-bearing capacity and unidirectional degree of freedom release. This mechanism has advantages such as simple structure, strong load-bearing capacity, good stability, and high motion accuracy.

[0005] The space camera on-orbit maintenance mechanism provided by the present invention includes: a base, a moving block, a roller rolling block, a guide block, a magnet, and a Hall effect device;

[0006] The base is used to connect with the main optical engine structure, and a square inner cavity is opened at its center. The roller rolling block is connected to the inner wall of the square inner cavity.

[0007] The moving block includes a circular flange and a square high-precision mating surface. The circular flange of the moving block is used to connect with the part being maintained, and its square high-precision mating surface is set in the square inner cavity by a roller rolling block. The square high-precision mating surface of the moving block is interference-fitted with the roller rolling block.

[0008] The guide block is located at the front end of the base and surrounds the square inner cavity. It is used to guide the moving block and the roller block when they are mating and to prevent the moving block from colliding with the roller block.

[0009] The magnet is mounted on the circular flange of the moving block, and a Hall effect device is correspondingly mounted at the front end of the base. The position of the moving block is fed back through the cooperation of the magnet and the Hall effect device.

[0010] Preferably, the base is connected to the main optical engine structure via a component adjustment pad, and the relative positional relationship between the moving block and the base is adjusted via the component adjustment pad.

[0011] Preferably, there are four roller blocks, and the fit accuracy between them and the moving block is adjusted by the roller block adjustment pad.

[0012] Preferably, it also includes a base end cap, which is installed at the rear end of the base to close the square inner cavity.

[0013] Preferably, the moving block and the roller rolling block are subjected to quenching and tempering processes to ensure that the Rockwell hardness of the moving block and the roller rolling block is not less than 60.

[0014] Preferably, the roller rolling block is composed of a first cage, a roller, a positioning block, and a second cage. The roller rolls on the surface of the positioning block, and the first cage and the second cage cooperate to fix the roller and the positioning block.

[0015] Compared with the prior art, the present invention can achieve the following beneficial effects:

[0016] This invention primarily achieves bidirectional high load-bearing capacity and unidirectional release degree of freedom through the interference fit of the square high-precision mating surfaces of the roller blocks and the square moving blocks. It is designed as a separable mechanism, allowing for easy disassembly and reassembly, high positioning accuracy, high reassembly repeatability, and strong operability. The roller blocks employ a self-circulating mechanism, saving space and providing strong load capacity. The guide block design facilitates docking between the moving block and the roller blocks, enabling operation even when not visible during on-orbit maintenance, and preventing the moving block from colliding with the roller block cage during coarse positioning. The combination of the Hall effect sensor and the magnet allows for position feedback during on-orbit maintenance.

[0017] The invention has a clear principle and simple structure, and is less expensive than existing equipment. It can be applied to different occasions through different base configurations and interfaces, thus increasing its scope of use. Attached Figure Description

[0018] Figure 1 This is a top view of the on-orbit maintenance mechanism for a space camera provided according to an embodiment of the present invention;

[0019] Figure 2 This is a cross-sectional view of an on-orbit maintenance mechanism for a space camera provided according to an embodiment of the present invention;

[0020] Figure 3 This is an axonometric view of an on-orbit maintenance mechanism for a space camera according to an embodiment of the present invention;

[0021] Figure 4 This is a simplified exploded view of the on-orbit maintenance mechanism for a space camera provided according to an embodiment of the present invention;

[0022] Figure 5 This is an exploded view of the roller block provided according to an embodiment of the present invention.

[0023] The reference numerals in the figures include:

[0024] 1. Base end cap, 2. Base, 3. Guide block, 4. Hall bracket, 5. Hall device, 6. Magnet, 7. Magnet seat, 8. Component adjustment pad, 9. Roller block, 10. Moving block, 11. Ball block adjustment pad;

[0025] First cage 9-1, roller 9-2, positioning block 9-3, second cage 9-4. Detailed Implementation

[0026] In the following description, embodiments of the invention will be described with reference to the accompanying drawings. In the description below, the same modules are denoted by the same reference numerals. Where the same reference numerals are used, their names and functions are also the same. Therefore, their detailed description will not be repeated.

[0027] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and do not constitute a limitation thereof.

[0028] like Figure 1 , Figure 2 , Figure 3 and Figure 4 As shown, the space camera on-orbit maintenance mechanism provided in this embodiment of the invention is mainly used for the bidirectional high load-bearing and unidirectional release linear motion of the space camera back-end module on-orbit maintenance. It includes components such as base end cover 1, base 2, guide block 3, Hall bracket 4, Hall device 5, magnet 6, magnet seat 7, component adjustment pad 8, roller rolling block 9, moving block 10 and ball rolling block adjustment pad 11.

[0029] The base 2 serves as the mounting frame for the entire device. It is arched and made of titanium alloy. A square inner cavity is located at the center of the base 2, the shape of which matches the moving block 10, but is larger in size. The bottom of the base 2 is connected to the main optical engine structure via an assembly adjustment pad 8. The relative position of the moving block 10 and the optical engine structure can be adjusted by adjusting the assembly adjustment pad 8. A base end cap 1 is installed at the rear end of the square inner cavity of the base 2 to seal the cavity and prevent contamination of the inner cavity of the roller block 9 after solid lubrication during the ground stage.

[0030] There are four roller blocks 9, all made of bearing steel. These four roller blocks 9 are fixed to the four inner wall surfaces of the square cavity of the base 2 by screws and ball bearing adjustment shims 11, forming a guide rail with unidirectional freedom of release. The fitting accuracy between the roller 9-2 and the moving block 10 can be changed by adjusting the ball bearing adjustment shims 11. The roller block 9 consists of a first cage 9-1, rollers 9-2, a positioning block 9-3, and a second cage 9-4. Both the first cage 9-1 and the second cage 9-4 are made of tin bronze, which has good ductility. Alternatively, materials with similar properties can be used as substitutes. The roller 9-2 can roll on the surface of the positioning block 9-3. The rolling plane includes two flat and smooth surfaces at the top and bottom and arc-shaped transition surfaces on the left and right sides. The two ends of the roller 9-2 are rolling sections with a larger diameter, and the middle is a limiting section with a smaller diameter. The first cage 9-1 and the second cage 9-4 are set according to the roller 9-2. The positions corresponding to the rolling sections are openings, and the positions corresponding to the limiting sections are limiting strips to prevent the roller 9-2 from detaching. The roller 9-2 and the positioning block 9-3 are fixed by the cooperation of the first cage 9-1 and the second cage 9-4. The roller 9-2 performs self-circulating motion within the first cage 9-1 and the second cage 9-4. Compared with linear guides, the roller rolling block 9 effectively saves space and is more convenient to detach and install.

[0031] The moving block 10 is made of bearing steel and includes a circular flange and a square high-precision mating surface. The square high-precision mating surface of the moving block 10 is installed in the square inner cavity via a guide rail composed of four rollers 9. The circular flange of the moving block 10 is used to connect to the rear-end module of the space camera for module maintenance and replacement. The circular flange of the moving block 10 is equipped with pins for resetting after on-orbit replacement. Its rear end is a regular square prism with rounded corners, allowing for bidirectional operation (e.g., ...). Figure 1 The moving block 10, with its high load-bearing capacity in the X and Y axes, moves linearly (Z-axis direction) along the square inner cavity of the roller block 9 on its square mating surface. The moving block 10 and the roller block 9 form a rolling friction sliding pair. A 0.005mm interference fit is used between the roller 9-2 and the moving block 10; the interference can be adjusted according to load, stiffness, and whether disengagement is required. Both the roller 9-2 and the moving block 10 surfaces are lubricated with solid lubricant to improve smooth movement and prevent cold welding of the contact surfaces. This is done to improve contact stiffness and to account for the disengagement and installation forces during on-orbit maintenance.

[0032] Since this invention is applied to on-orbit maintenance, it is necessary to separate the roller rolling block 9 and the moving block 10, and the maintenance force is required to be no more than 40N. Therefore, this invention adopts a separable design, which can realize the detachment and reassembly of the moving block 9. In order to ensure sufficient hardness and load capacity, both the roller rolling block 9 and the moving block 10 are subjected to quenching and tempering processes. Quenching improves hardness, and tempering improves yield stress, ensuring that the Rockwell hardness of the moving block 10 and the roller rolling block 9 is not less than 60, avoiding damage to their contact surfaces under high load, and improving their service life. The specific hardness can be adjusted according to the load requirements and service life.

[0033] The guide block 3, made of titanium alloy, is located on the front end face of the base 2 and surrounds the square inner cavity. The guide block 3 has an inclined inlet, with its leading edge opening larger than the square inner cavity. During the reassembly of the moving block 10 and the roller block 9, the guide block 3 performs coarse positioning with an accuracy of ±1mm. After coarse positioning, the moving block 10 can be smoothly inserted into the square inner cavity, facilitating docking and reassembly during on-orbit maintenance when not visible. The guide block 3 serves both a guiding function and prevents the moving block 10 from directly impacting the first and second cages 9-1 and 9-4 of the roller block 10 during the coarse positioning stage.

[0034] Since the freedom of the moving block 10 in the maintenance direction is released, in order to ensure the initial positional relationship between the moving block 10 and the base 2, a magnet 6 is provided on the circular flange of the moving block 10 through a magnet seat 7. Correspondingly, a Hall bracket 4 is provided at the corresponding position at the front end of the base 2. A Hall device 5 and its circuit module are provided on the Hall bracket 4. The relative positional relationship between the moving block 10 and the base is fed back through the cooperation of the magnet 6 and the Hall device 5, so as to realize the positioning feedback.

[0035] In this invention, all components are fixed using M3 screws, with the specific screw specifications determined based on load-bearing capacity and spatial layout. This invention features a simple structure, high load capacity, and high stability, making it particularly suitable for scenarios requiring high reset accuracy, high load-bearing capacity, and unidirectional degree of freedom release. Furthermore, in addition to on-orbit maintenance, it can also be applied to other scenarios requiring the ability to detach from linear motion guideways.

[0036] Although embodiments of the present invention have been shown and described above, it is to be understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those skilled in the art can make changes, modifications, substitutions, and variations to the above embodiments within the scope of the present invention.

[0037] The specific embodiments of the present invention described above do not constitute a limitation on the scope of protection of the present invention. Any other corresponding changes and modifications made in accordance with the technical concept of the present invention should be included within the scope of protection of the claims of the present invention.

Claims

1. A space camera on-orbit maintenance mechanism, characterized in that, include: Base, moving block, roller block, guide block, magnet and Hall effect device; The base is used to connect with the main optical engine structure, and a square inner cavity is opened at its center, with the roller rolling block connected to the inner wall of the square inner cavity. The moving block includes a circular flange and a square high-precision mating surface. The circular flange of the moving block is used to connect with the part being maintained, and its square high-precision mating surface is set in the square inner cavity through the roller rolling block. The square high-precision mating surface of the moving block is interference-fitted with the roller rolling block. The circular flange of the moving block is equipped with a pin for resetting after on-rail replacement. Its rear end is a regular square prism with rounded corners. The roller rolling block is composed of a first cage, a roller, a positioning block, and a second cage. The roller rolls on the surface of the positioning block, and the first cage and the second cage cooperate to fix the roller and the positioning block. The moving block and the roller rolling block form a sliding pair with rolling friction, and the roller and the moving block adopt an interference fit. The guide block is disposed at the front end of the base and surrounds the square inner cavity. The guide block is an inclined inlet with an opening size at its front edge larger than the size of the square inner cavity. It is used to guide the moving block and the roller block when they are docking and to prevent the moving block from colliding with the roller block. The magnet is mounted on the circular flange of the moving block, and the Hall effect device is correspondingly mounted on the front end of the base. The position of the moving block is fed back through the cooperation of the magnet and the Hall effect device.

2. The space camera on-orbit maintenance mechanism as described in claim 1, characterized in that, The base is connected to the main optical engine structure via a component adjustment pad, and the relative position of the moving block is adjusted via the component adjustment pad.

3. The space camera on-orbit maintenance mechanism as described in claim 1, characterized in that, There are four roller blocks, and the fit accuracy between them and the moving block is adjusted by the roller block adjustment pad.

4. The space camera on-orbit maintenance mechanism as described in claim 1, characterized in that, It also includes a base end cap, which is installed at the rear end of the base to close the square inner cavity.

5. The space camera on-orbit maintenance mechanism as described in claim 1, characterized in that, The moving block and the rolling block are subjected to quenching and tempering processes to ensure that the Rockwell hardness of the moving block and the rolling block is not less than 60.

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