Reflector assembly for space remote sensor and assembly method thereof

Abstract

The present invention relates to the field of space remote sensing technology, and in particular to a reflector assembly used in a space remote sensor and an assembly method thereof, wherein the reflector assembly comprises a reflector and a support structure. A plurality of mounting holes are provided on the back of the reflector, and a support component is provided in the mounting hole. The support component comprises a cone sleeve structure, which comprises a bottom end, a straight tube portion and a top end portion, wherein the bottom end portion is connected to one end of the straight tube portion, the straight tube portion extends along a first direction, and the other end of the straight tube portion is connected to the top end portion. The top end portion extends outward from the other end of the straight tube portion along a second direction. The first direction is perpendicular to the second direction. The cone sleeve structure is located in the mounting hole, a gap is provided between the straight tube portion and the mounting hole, and the top end portion is bonded to the outer edge of the mounting hole. This allows the cone sleeve structure to be bonded after the reflector is coated, thereby effectively preventing the adhesive layer between the cone sleeve structure and the reflector from being damaged and failing due to the high temperature of the reflector during coating.

Description

Technical Field

[0001] The present invention belongs to the technical field of space remote sensing, and in particular relates to a reflector assembly applied to a space remote sensor and an assembling method thereof. Background Art

[0002] As a key optical component in space remote sensing, reflectors must possess stable support to ensure excellent imaging quality. Depending on the support method, reflectors can be supported in three main ways: passive, gravity-unloaded, and active. Among passive support methods, back support, such as three-point back support, is currently the most commonly used.

[0003] During the assembly and processing of mirrors with three-point back support, the mirror coating is often performed after the support structure's cone sleeve is bonded. However, for mirrors requiring thicker coatings, higher coating temperatures are required. High temperatures can damage the adhesive layer between the mirror and the cone sleeve, making the "bonding the cone sleeve first, then coating the mirror" approach unsuitable. Summary of the Invention

[0004] In view of this, the present invention aims to provide a reflector assembly and an assembly method thereof for use in space remote sensors. The bonding position of the cone sleeve structure is far away from the mirror surface, which reduces the sensitivity of the mirror surface shape to assembly stress, so that the cone sleeve structure can be bonded after the reflector is coated, thereby effectively avoiding the damage and failure of the adhesive layer between the cone sleeve structure and the reflector due to the high temperature of the reflector during coating.

[0005] To achieve the above object, the technical solution created by the present invention is implemented as follows:

[0006] A reflector assembly for use in a space remote sensor, the reflector assembly comprising a reflector and a supporting structure;

[0007] The supporting structure includes multiple supporting components, and multiple mounting holes are provided on the back of the reflector, and the supporting components are arranged in the mounting holes; the supporting components include a cone sleeve structure, and the cone sleeve structure includes a bottom end, a straight tube part and a top end part, the bottom end part is connected to one end of the straight tube part, the straight tube part extends along a first direction, and the other end of the straight tube part is connected to the top end part; the top end part extends outward from the other end of the straight tube part along a second direction; wherein the first direction is perpendicular to the second direction; the cone sleeve structure is located in the mounting hole, there is a gap between the straight tube part and the mounting hole, and the top end part is bonded to the outer edge of the mounting hole.

[0008] Furthermore, the supporting component also includes a flexible joint and a grinding pad, one end of the flexible joint is fixedly connected to the bottom end of the cone sleeve structure through a connecting piece, and the other end of the flexible joint is fixedly connected to the grinding pad through a connecting piece.

[0009] Furthermore, the bottom end portion, the straight tube portion and the top end portion of the cone sleeve structure are an integrated structure.

[0010] Furthermore, the material of the cone sleeve structure is Invar material having the same linear expansion coefficient as that of the reflector.

[0011] Furthermore, the plurality of mounting holes are arranged at even intervals along the circumference of the reflector with the optical axis of the reflector as the axis.

[0012] A method for assembling a reflector assembly for a space remote sensor is disclosed. The method is used to assemble the reflector assembly, wherein the reflector assembly includes a reflector and a support structure; the support structure includes multiple support components, and the back of the reflector is provided with multiple mounting holes; the support component includes a cone sleeve structure, the cone sleeve structure includes a bottom end, a straight tube portion, and a top end portion, the bottom end portion is connected to one end of the straight tube portion, the straight tube portion extends along a first direction, and the other end of the straight tube portion is connected to the top end portion; the top end portion extends outward from the other end of the straight tube portion along a second direction; wherein the first direction is perpendicular to the second direction; the assembly method comprises:

[0013] S1: Perform optical processing on the mirror surface of the reflector and coat the mirror surface of the reflector at a set temperature;

[0014] S2: Place the cone sleeve structure in the mounting hole, and use fixing glue to adhere the top end of the cone sleeve structure to the outer edge of the mounting hole.

[0015] Furthermore, the supporting component further includes a flexible joint and a connecting piece; after step S2, the assembly method further includes:

[0016] S3: Place the flexible joint in the cone sleeve structure, so that one end of the flexible joint is fixedly connected to the bottom end of the cone sleeve structure through a connecting piece.

[0017] Furthermore, the support component further includes a grinding pad; after step S3, the assembly method further includes:

[0018] S4: The grinding pad is fixedly connected to the other end of the flexible joint through a connecting piece.

[0019] Furthermore, the flatness of the inner surface of the bottom end portion and the surface where the flexible joint contacts the bottom end portion is less than or equal to 0.005 mm.

[0020] Furthermore, the flatness of the back end surface of the reflector and the surface where the top end of the cone sleeve structure contacts the back end surface of the reflector is less than or equal to 0.005 mm.

[0021] Compared with the prior art, the present invention can achieve the following beneficial effects:

[0022] This embodiment provides a reflector assembly for use in space remote sensors. On the one hand, the top end of the cone sleeve structure is bonded to the outer edge of the mounting hole, and the bonding stress has little effect on the mirror surface shape of the reflector. This allows the cone sleeve structure to be bonded after the reflector is coated, effectively preventing the adhesive layer between the cone sleeve structure and the reflector from being damaged and failing due to the high temperature of the reflector during coating. This makes it suitable for reflectors with thicker film layers. On the other hand, because the bonding position between the cone sleeve structure and the reflector changes, the top end of the cone sleeve structure is bonded to the outer edge of the mounting hole, and the bonding stress can be transmitted and released along the optical axis of the reflector, optimizing the bonding stress transmission path. Furthermore, the bonding position is relatively far from the mirror surface of the reflector, making the mirror surface shape insensitive to the bonding stress and significantly reducing the sensitivity of the mirror surface shape to the assembly process. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] The accompanying drawings, which constitute part of the present invention, are intended to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are intended to explain the present invention and do not constitute an undue limitation of the present invention. In the accompanying drawings:

[0024] Figure 1 A schematic diagram of a reflector assembly according to an embodiment of the present invention;

[0025] Figure 2 A schematic diagram of a cone sleeve structure of a reflector assembly according to an embodiment of the present invention;

[0026] Figure 3 The present invention provides a flowchart of a method for assembling a reflector assembly according to an embodiment of the present invention.

[0027] Description of reference numerals:

[0028] 10. Reflector assembly; 11. Reflector; 12. Support structure; 13. Support component; 14. Mounting hole; 15. Cone sleeve structure; 16. Bottom end; 17. Straight tube; 18. Top end; 19. Flexible joint; 20. Grinding pad. DETAILED DESCRIPTION

[0029] In order to make the purpose, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below in conjunction with the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and do not constitute a limitation to the present invention. Similar elements in different embodiments use associated similar element numbers. In the following embodiments, many detailed descriptions are intended to enable the present invention to be better understood. However, those skilled in the art can easily recognize that some of the features can be omitted in different situations, or can be replaced by other elements, materials, or methods. In some cases, some operations related to the present invention are not shown or described in the specification. This is to avoid the core part of the present invention being overwhelmed by too much description. For those skilled in the art, it is not necessary to describe these related operations in detail. They can fully understand the related operations based on the description in the specification and the general technical knowledge in the art.

[0030] It should be noted that, in the absence of conflict, the embodiments and features of the embodiments of the present invention can be combined with each other to form various implementation methods. At the same time, the steps or actions in the method description can also be interchanged or adjusted in a manner that is obvious to those skilled in the art. Therefore, the various orders in the description and the drawings are only for the purpose of clearly describing a certain embodiment and are not intended to be a required order, unless otherwise specified that a certain order must be followed.

[0031] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention. In addition, the terms "first", "second", etc. are only used for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, features defined as "first", "second", etc. may explicitly or implicitly include one or more of the features. In the description of the present invention, unless otherwise specified, "multiple" means two or more.

[0032] In the description of the present invention, it should be noted that, unless otherwise expressly specified or limited, the terms "installed," "connected," and "connected" should be understood in a broad sense. For example, they can refer to fixed connections, detachable connections, or integral connections; they can refer to mechanical connections or electrical connections; they can refer to direct connections or indirect connections through an intermediate medium; and they can refer to internal connections between two components. Those skilled in the art can understand the specific meanings of the above terms in the present invention based on specific circumstances.

[0033] The present invention will be described in detail below with reference to the accompanying drawings and in combination with embodiments.

[0034] See also Figure 1 and Figure 2 As shown, an embodiment of the present invention provides a reflector assembly 10 for use in a space remote sensor. The reflector assembly 10 includes a reflector 11 and a support structure 12. The support structure 12 provides stable support for the reflector 11. The support structure 12 includes a plurality of support components 13. In this embodiment, there are three support components 13, which are evenly spaced about the optical axis of the reflector 11 and arranged circumferentially. The back of the reflector 11 is provided with a plurality of mounting holes 14, within which the support components 13 are disposed. Each support component 13 corresponds to a mounting hole 14. The mounting holes 14 are used to mount the support components 13. In one embodiment, the plurality of mounting holes 14 are evenly spaced about the optical axis of the reflector 11 and arranged circumferentially. In this embodiment, there are three mounting holes 14, which are evenly spaced about the optical axis of the reflector 11 and arranged circumferentially, thereby forming a reflector assembly 10 with three points of back support.

[0035] The support component 13 includes a cone sleeve structure 15, which includes a bottom end 16, a straight tube portion 17 and a top end 18. In one embodiment, the bottom end 16, the straight tube portion 17 and the top end 18 are an integrated structure, so that the structural design of the cone sleeve structure 15 is simpler. The bottom end 16 is connected to one end of the straight tube portion 17, the straight tube portion 17 extends along a first direction, and the other end of the straight tube portion 17 is connected to the top end 18. The top end 18 extends outward from the other end of the straight tube portion 17 along a second direction. The first direction is perpendicular to the second direction. The cone sleeve structure 15 is located in the mounting hole 14, and there is a gap between the straight tube portion 17 and the mounting hole 14. The top end 18 is bonded to the outer edge of the mounting hole 14. The mounting hole 14 includes a bottom wall and a side wall. The outer edge of the mounting hole 14 refers to the surface connected to one end of the side wall away from the bottom wall, which is the end face of the back of the reflector 11.

[0036] This embodiment provides a reflector assembly 10 for use in a space remote sensor. On the one hand, the top end 18 of the cone sleeve structure 15 is bonded to the outer edge of the mounting hole 14. Because the bonding position is relatively far from the mirror surface of the reflector 11, the bonding stress has a minimal effect on the mirror surface shape of the reflector 11. This allows the cone sleeve structure 15 to be bonded after the reflector 11 is coated, effectively preventing damage and failure of the adhesive layer between the cone sleeve structure 15 and the reflector 11 due to the high temperature of the reflector 11 during coating. This makes it suitable for reflectors 11 with thicker coatings. On the other hand, because the bonding position between the cone sleeve structure 15 and the reflector 11 is changed, the top end 18 of the cone sleeve structure 15 is bonded to the outer edge of the mounting hole 14, allowing the bonding stress to be transferred and released along the optical axis of the reflector 11, thus optimizing the bonding stress transfer path. Furthermore, the bonding position is relatively far from the mirror surface of the reflector 11, making the mirror surface shape of the reflector 11 insensitive to the bonding stress and significantly reducing the sensitivity of the mirror surface shape to the assembly process.

[0037] In one embodiment, the support component 13 further includes a flexible joint 19, a grinding pad 20, and a connector (not shown in the figure), and the cone sleeve structure 15 is used to connect the reflector 11 to the flexible joint 19. The flexible joint 19 can improve the environmental adaptability of the reflector 11 under the influence of gravity load, temperature load, and assembly error. The grinding pad 20 can be used to ensure the flatness of the mounting surface of the support component 13. One end of the flexible joint 19 is fixedly connected to the bottom end 16 of the cone sleeve structure 15 through a connector, and one end of the flexible joint 19 can be fixedly connected to the bottom end 16 of the cone sleeve structure 15 by a screw. The other end of the flexible joint 19 is fixedly connected to the grinding pad 20 through a connector, wherein the connector can be a screw, and the other end of the flexible joint 19 can be fixedly connected to the grinding pad 20 by a screw.

[0038] In one embodiment, the material of the cone sleeve structure 15 is Invar, which has the same linear expansion coefficient as the material of the reflector 11. The reflector 11 can be made of silicon carbide (SiC), and the cone sleeve structure 15 is made of Invar. This ensures that the linear expansion coefficients of the reflector 11 and the cone sleeve structure 15 are the same. This allows the reflector 11 and the cone sleeve structure 15 to expand in unison under temperature, thus avoiding thermal stress caused by uneven expansion under temperature loads and preventing deformation of the reflector 11.

[0039] See also Figure 3 As shown, the embodiment of the present invention also provides an assembly method of a reflector assembly 10 for a space remote sensor, which is used for assembling the reflector assembly 10. The assembly method includes the following steps:

[0040] S1: Optically process the mirror surface of the reflector 11, and coat the mirror surface of the reflector 11 at a set temperature. A film structure is formed on the mirror surface of the reflector 11, which can protect the mirror surface and prevent damage to the mirror surface or performance degradation of the mirror surface under adverse conditions. The film structure can also improve the reflectivity of the mirror surface of the reflector 11, making the imaging of the space remote sensor clearer. Before step S1, the reflector 11, the cone sleeve structure 15, the flexible joint 19, the grinding pad 20 and other parts can be cleaned. The cleaning method can be used to ensure that the assembly environment is clean, and the parts with the same geometric structure and size can be marked for subsequent tracking and maintenance.

[0041] S2: Place the cone sleeve structure 15 in the mounting hole 14, and use a fixing glue to adhere the top end 18 of the cone sleeve structure 15 to the outer edge of the mounting hole 14. The fixing glue can be an epoxy resin glue. After the reflector 11 is coated, place the cone sleeve structure 15 in the mounting hole 14, and use an epoxy resin glue to adhere the top end 18 of the cone sleeve structure 15 to the outer edge of the mounting hole 14. The epoxy resin glue can be injected between the top end 18 of the cone sleeve structure 15 and the outer edge of the mounting hole 14, and then the top end 18 of the cone sleeve structure 15 and the outer edge of the mounting hole 14 are pressed tightly, and the curing is continued for a set time to ensure full contact of the bonding surface. The setting time can be two weeks. The flatness of the back end face of the reflector 11 and the surface where the top end 18 of the cone sleeve structure 15 contacts the back end face of the reflector 11 is less than or equal to 0.005 mm.

[0042] In one embodiment, after step S2, the assembly method further includes: S3: placing the flexible joint 19 within the cone sleeve structure 15, such that one end of the flexible joint 19 is fixedly connected to the bottom end 16 of the cone sleeve structure 15 via a connector. The bottom end 16 of the cone sleeve structure 15 and one end of the flexible joint 19 can be fixedly connected by screws. The screws can be glued with GD414 glue (GD414 glue is used as anti-loosening glue) to fix the bottom end 16 of the cone sleeve structure 15 and one end of the flexible joint 19. After the anti-loosening glue is cured, the flexible joint 19 and the corresponding cone sleeve structure 15 can be marked. The flatness of the inner surface of the bottom end 16 and the surface of the flexible joint 19 in contact with the bottom end 16 is less than or equal to 0.005 mm.

[0043] In one embodiment, after step S3, the assembly method further includes: S4: fixing the grinding pad 20 to the other end of the flexible joint 19 via a connector. The grinding pad 20 can be fixed to the other end of the flexible joint 19 via screws. The screws can be used to apply GD414 glue (GD414 glue is used as anti-loosening glue) to fix the grinding pad 20 and the other end of the flexible joint 19. After the anti-loosening glue is cured, the flexible joint 19 and the corresponding grinding pad 20 can be marked.

[0044] After step S4 , the assembly method may further include: checking the connection status between the various parts of the reflector assembly 10 to ensure that the installation is correct.

[0045] The present invention provides a reflector assembly 10 for use in space remote sensors. Unlike the prior art assembly process in which the reflector 11 is first bonded to a cone sleeve structure 15 and then coated, the cone sleeve structure 15 in the present invention is different from the prior art. The top end 18 of the cone sleeve structure 15 is bonded to the outer edge of the mounting hole 14, allowing the cone sleeve structure 15 to be bonded after the reflector 11 is coated. This effectively prevents the temperature during the coating process of the reflector 11 from affecting the bonding effect between the cone sleeve structure 15 and the reflector 11, and prevents the adhesive layer between the reflector 11 and the cone sleeve structure 15 from failing due to high temperature during coating. Furthermore, the cone sleeve structure 15 is bonded to the outer edge of the mounting hole 14 of the reflector 11 via the top end 18. The bonding position is relatively far from the mirror surface of the reflector 11, and the bonding stress is transmitted along the optical axis of the reflector 11, reducing the sensitivity of the mirror surface to assembly stress.

[0046] It should be understood that the various forms of the processes shown above can be used to reorder, add, or delete steps. For example, the steps described in the present disclosure can be performed in parallel, sequentially, or in a different order, as long as the desired results of the technical solutions disclosed in the present disclosure can be achieved. This is not limited herein.

[0047] The above specific embodiments do not limit the scope of protection of the present invention. Those skilled in the art will appreciate that various modifications, combinations, sub-combinations, and substitutions may be made based on design requirements and other factors. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention are intended to be included within the scope of protection of the present invention.

Claims

1. A reflector assembly for a space remote sensor, characterized in that: The reflector assembly includes a reflector and a support structure; The supporting structure includes a plurality of supporting components, a plurality of mounting holes are provided on the back of the reflector, and the supporting components are arranged in the mounting holes; the supporting components include a cone sleeve structure, and the cone sleeve structure includes a bottom end, a straight cylinder part and a top end part, the bottom end part is connected to one end of the straight cylinder part, the straight cylinder part extends along a first direction, and the other end of the straight cylinder part is connected to the top end part; the top end part extends outward from the other end of the straight cylinder part along a second direction; wherein, the first direction is perpendicular to the second direction; the cone sleeve structure is located in the mounting hole, there is a gap between the straight cylinder part and the mounting hole, and the top end part is bonded to the outer edge of the mounting hole.

2. The reflector assembly for space remote sensors according to claim 1, characterized in that: The support component further includes a flexible joint and a grinding pad. One end of the flexible joint is fixedly connected to the bottom end of the cone sleeve structure through a connecting piece, and the other end of the flexible joint is fixedly connected to the grinding pad through a connecting piece.

3. The reflector assembly for space remote sensors according to claim 1, characterized in that: The bottom end portion, the straight tube portion and the top end portion of the cone sleeve structure are an integrated structure.

4. The reflector assembly for space remote sensors according to claim 1, characterized in that: The material of the cone sleeve structure is Invar material having the same linear expansion coefficient as that of the reflector.

5. The reflector assembly for space remote sensors according to claim 1, characterized in that: The plurality of mounting holes are arranged at even intervals along the circumference of the reflector with the optical axis of the reflector as an axis.

6. A method for assembling a reflector assembly for a space remote sensor, characterized in that: Used for assembling a reflector assembly, the reflector assembly includes a reflector and a support structure; the support structure includes a plurality of support components, and a plurality of mounting holes are provided on the back of the reflector; the support component includes a cone sleeve structure, the cone sleeve structure includes a bottom end, a straight tube portion, and a top end portion, the bottom end portion is connected to one end of the straight tube portion, the straight tube portion extends along a first direction, and the other end of the straight tube portion is connected to the top end portion; The top portion extends outward from the other end of the straight tube portion along a second direction; wherein the first direction is perpendicular to the second direction; and the assembly method includes: S1: performing optical processing on the mirror surface of the reflector, and coating the mirror surface of the reflector at a set temperature; S2: placing the cone sleeve structure in the mounting hole, and using fixing glue to adhere the top end of the cone sleeve structure to the outer edge of the mounting hole.

7. The method for assembling a reflector assembly for a space remote sensor according to claim 6, wherein: The supporting component further includes a flexible joint and a connecting piece; after step S2, the assembly method further includes: S3: Place the flexible joint in the cone sleeve structure, so that one end of the flexible joint is fixedly connected to the bottom end of the cone sleeve structure through a connecting piece.

8. The method for assembling a reflector assembly for a space remote sensor according to claim 7, wherein: The support component further includes a grinding pad; after step S3, the assembly method further includes: S4: The grinding pad is fixedly connected to the other end of the flexible joint through a connecting piece.

9. The method for assembling a reflector assembly for a space remote sensor according to claim 7, wherein: The flatness of the inner surface of the bottom end portion and the surface of the flexible joint in contact with the bottom end portion is less than or equal to 0.005 mm.

10. The method for assembling a reflector assembly for a space remote sensor according to claim 6, wherein: The flatness of the back end surface of the reflector and the surface where the top end of the cone sleeve structure contacts the back end surface of the reflector is less than or equal to 0.005 mm.

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