Reflector assembly applied to space remote sensor and assembling method thereof

Abstract

The invention relates to the technical field of space remote sensing, in particular to a reflector assembly applied to a space remote sensor and an assembling method thereof, and the reflector assembly comprises a reflector and a supporting structure. The back of the reflector is provided with a plurality of mounting holes, and the supporting parts are arranged in the mounting holes. The supporting component comprises a taper sleeve structure, the taper sleeve structure comprises a bottom end portion, a straight cylinder portion and a top end portion, the bottom end portion is connected to one end of the straight cylinder portion, the straight cylinder portion extends in the first direction, and the other end of the straight cylinder portion is connected to the top end portion. The top end part extends outwards from the other end of the straight cylinder part in the second direction. Wherein the first direction is perpendicular to the second direction. The taper sleeve structure is located in the mounting hole, a gap is formed between the straight cylinder part and the mounting hole, and the top end part is bonded to the outer edge of the mounting hole. The taper sleeve structure can be bonded after the reflector is coated with a film, so that the phenomenon that a glue layer between the taper sleeve structure and the reflector is damaged and fails due to the high temperature of the reflector during film coating is effectively avoided.

Description

Technical Field

[0001] The 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 one of the important optical components of space remote sensors, the reflector should have stable support performance to ensure good imaging quality of the system. According to the different support forms, the reflector mainly has three support modes: passive support, gravity unloading support and active support. Among the passive support forms, the back support is currently more widely used, such as the back three-point support.

[0003] In the processing and assembly of a reflector with three-point back support, the coating of the reflector is often carried out after the cone sleeve structure of the support structure is bonded. However, for reflectors that need to prepare thicker film layers, higher coating temperatures are required. High temperatures will damage the glue layer between the reflector and the cone sleeve structure. This method of "bonding the cone sleeve structure first and then coating the mirror body" is obviously no longer applicable. 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 glue layer between the cone sleeve structure and the reflector from being damaged and failing 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: A reflector assembly for use in a space remote sensor, the reflector assembly comprising a reflector and a supporting 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, 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 cone sleeve structure is located in the mounting hole, there is a gap between the straight tube portion and the mounting hole, and the top end portion is bonded to the outer edge of the mounting hole.

[0006] 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.

[0007] Furthermore, the bottom end portion, the straight tube portion and the top end portion of the cone sleeve structure are an integrated structure.

[0008] Furthermore, the material of the cone sleeve structure is Invar material having the same linear expansion coefficient as that of the reflector.

[0009] Furthermore, the plurality of mounting holes are arranged evenly spaced along the circumference of the reflector with the optical axis of the reflector as the axis. A method for assembling a reflector assembly for a space remote sensor is used for assembling the reflector assembly, wherein the reflector assembly comprises a reflector and a support structure; the support structure comprises a plurality of support components, and a plurality of mounting holes are arranged on the back of the reflector; the support component comprises a cone sleeve structure, the cone sleeve structure comprises 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 assembling method comprises: S1: Optically process the mirror surface of the reflector, and coat the mirror surface of the reflector at a set temperature; S2: Place the cone sleeve structure in the mounting hole, and use a fixing glue to bond the top end of the cone sleeve structure to the outer edge of the mounting hole.

[0010] Furthermore, 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.

[0011] Furthermore, 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.

[0012] 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.

[0013] 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.

[0014] Compared with the prior art, the invention can achieve the following beneficial effects: This embodiment provides a reflector assembly for use in a space remote sensor. 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, so that the cone sleeve structure can be bonded after the reflector is coated, thereby effectively avoiding 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, and can be applied to reflectors with thicker film layers. On the other hand, due to the change in the bonding position between the cone sleeve structure and the reflector, 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 direction of the reflector, thereby optimizing the transmission path of the bonding stress, and the bonding position is far away from the mirror surface of the reflector, so that the mirror surface shape of the reflector is insensitive to the bonding stress, and the sensitivity of the mirror surface shape to the assembly process is greatly reduced. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] The drawings constituting part of the present invention are used to provide a further understanding of the present invention. The exemplary embodiments and descriptions of the present invention are used to explain the present invention and do not constitute an improper limitation on the present invention. In the drawings: Figure 1 A schematic diagram of a reflector assembly according to an embodiment of the present invention; Figure 2 A schematic diagram of a cone sleeve structure of a reflector assembly according to an embodiment of the present invention; Figure 3 A flow chart of a method for assembling a reflector assembly according to an embodiment of the present invention.

[0016] Description of reference numerals: 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

[0017] In order to make the purpose, technical scheme and advantages of the invention clearer, the 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 invention and do not constitute a limitation to the invention. Similar components in different embodiments use associated similar component numbers. In the following embodiments, many detailed descriptions are to enable the 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 components, materials, and methods. In some cases, some operations related to the invention are not shown or described in the specification, in order to avoid the core part of the invention being overwhelmed by too much description, and for those skilled in the art, it is not necessary to describe these related operations in detail, and they can fully understand the related operations according to the description in the specification and the general technical knowledge in the art.

[0018] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features in the embodiments 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 sequences in the specification and the drawings are only for the purpose of clearly describing a certain embodiment and are not meant to be a necessary sequence, unless otherwise specified that a certain sequence must be followed.

[0019] In the description of the 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", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the drawings, and are only for the convenience of describing the 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 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 technical features indicated. Therefore, the features defined as "first", "second", etc. may explicitly or implicitly include one or more of the features. In the description of the invention, unless otherwise specified, the meaning of "multiple" is two or more.

[0020] In the description of the invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installation", "connection" and "connection" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the invention can be understood according to specific circumstances.

[0021] The present invention will be described in detail below with reference to the accompanying drawings and in combination with embodiments.

[0022] See also Figure 1 and Figure 2 As shown, the embodiment of the invention provides a reflector assembly 10 for space remote sensors, and the reflector assembly 10 includes a reflector 11 and a support structure 12. The support structure 12 can be used to achieve stable support for the reflector 11. The support structure 12 includes a plurality of support components 13. In this embodiment, the number of the support components 13 is three, and the three support components 13 are arranged evenly spaced along the circumference of the reflector 11 with the optical axis of the reflector 11 as the axis. A plurality of mounting holes 14 are provided on the back of the reflector 11, and the support components 13 are arranged in the mounting holes 14. Among them, one support component 13 is provided corresponding to one mounting hole 14. The mounting hole 14 is used to realize the installation of the support component 13. In one embodiment, the plurality of mounting holes 14 are arranged evenly spaced along the circumference of the reflector 11 with the optical axis of the reflector 11 as the axis. In this embodiment, the number of the mounting holes 14 is three, and the three mounting holes 14 are arranged evenly spaced along the circumference of the reflector 11 with the optical axis of the reflector 11 as the axis, so that a reflector assembly 10 with three-point support on the back can be formed.

[0023] The support component 13 includes a cone sleeve structure 15, and the cone sleeve structure 15 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, and the top end 18 is bonded to the outer edge of the mounting hole 14. The mounting hole 14 includes a hole bottom wall and a hole side wall. The outer edge of the mounting hole 14 refers to the surface connected to one end of the hole side wall away from the hole bottom wall, which is the end face of the back of the reflector 11.

[0024] This embodiment provides a reflector assembly 10 for 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. Since the bonding position is far away from the mirror surface of the reflector 11, the bonding stress has little effect on the mirror surface shape of the reflector 11, so that the cone sleeve structure 15 can be bonded after the reflector 11 is coated, thereby effectively avoiding the adhesive layer between the cone sleeve structure 15 and the reflector 11 from being damaged and failed due to the high temperature of the reflector 11 during coating, and can be applied to reflectors 11 with thicker film layers. On the other hand, since the bonding position between the cone sleeve structure 15 and the reflector 11 changes, the top end 18 of the cone sleeve structure 15 is bonded to the outer edge of the mounting hole 14, and the bonding stress can be transmitted and released along the optical axis direction of the reflector 11, thereby optimizing the transmission path of the bonding stress, and the bonding position is far away from the mirror surface of the reflector 11, so that the mirror surface shape of the reflector 11 is insensitive to the bonding stress, and the sensitivity of the mirror surface shape to the assembly process is greatly reduced.

[0025] In one embodiment, the support component 13 further includes a flexible joint 19, a grinding pad 20 and a connecting piece (not shown in the figure), and the cone sleeve structure 15 is used to connect the reflector 11 and 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 connecting piece, 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 connecting piece, wherein the connecting piece 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.

[0026] In one embodiment, the material of the cone sleeve structure 15 is an Invar material having the same linear expansion coefficient as the material of the reflector 11. The material of the reflector 11 may be silicon carbide (SiC), and the material of the cone sleeve structure 15 is an Invar material, so that the linear expansion coefficient of the material of the reflector 11 is the same as that of the material of the cone sleeve structure 15, so that the expansion conditions of the reflector 11 and the cone sleeve structure 15 under the influence of temperature are consistent, and thermal stress caused by uneven expansion under temperature load can be avoided, thereby preventing the reflector 11 from deforming.

[0027] See also Figure 3 As shown, the embodiment of the 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 comprises the following steps: 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 the cleanliness of the assembly environment, and the parts with the same geometric structure and size can be marked for subsequent tracking and maintenance.

[0028] S2: Place the cone sleeve structure 15 in the mounting hole 14, and use a fixing glue to bond the top end 18 of the cone sleeve structure 15 to the outer edge of the mounting hole 14. The fixing glue may 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 bond the top end 18 of the cone sleeve structure 15 to the outer edge of the mounting hole 14. The epoxy resin glue may 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 set time may 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.

[0029] In one embodiment, after step S2, the assembly method further includes: S3: placing the flexible joint 19 in the cone sleeve structure 15, so that one end of the flexible joint 19 is fixedly connected to the bottom end 16 of the cone sleeve structure 15 through 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, and the screws can be used to apply 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. Among them, 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.

[0030] 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 through a connecting piece. The grinding pad 20 can be fixedly connected to the other end of the flexible joint 19 by screws, and 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.

[0031] 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.

[0032] The embodiment of the invention provides a reflector assembly 10 for space remote sensors. Different from the assembly process in the prior art in which the reflector 11 is first bonded to the cone sleeve structure 15 and then coated, the cone sleeve structure 15 of the embodiment of the invention is different from the prior art, and the top end 18 of the cone sleeve structure 15 is bonded to the outer edge of the mounting hole 14, so that the bonding time of the cone sleeve structure 15 can be adjusted to after the reflector 11 is coated, effectively avoiding the influence of the temperature during the coating process of the reflector 11 on the bonding effect of the cone sleeve structure 15 and the reflector 11, and preventing the glue layer between the reflector 11 and the cone sleeve structure 15 from failing due to high temperature during the coating. The cone sleeve structure 15 is bonded to the outer edge of the mounting hole 14 of the reflector 11 through the top end 18, and the bonding position is far away from the mirror surface of the reflector 11. The bonding stress is transmitted along the optical axis direction of the reflector 11, reducing the sensitivity of the mirror surface shape to the assembly stress.

[0033] It should be understood that the various forms of processes shown above can be used to reorder, add or delete steps. For example, the steps described in the disclosure of the present invention can be performed in parallel, sequentially or in different orders, as long as the desired results of the technical solution disclosed in the present invention can be achieved, and this document does not limit this.

[0034] The above specific implementations do not constitute a limitation on the protection scope of the present invention. It should be understood by those skilled in the art that various modifications, combinations, sub-combinations and substitutions can be made according to design requirements and other factors. Any modification, equivalent substitution and improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A reflector assembly for use in a space remote sensor, characterized in that: The reflector assembly comprises a reflector and a supporting structure; The supporting structure comprises 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 comprise a cone sleeve structure, the cone sleeve structure comprises a bottom end portion, 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 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.

2. The reflector assembly for space remote sensor according to claim 1, characterized in that: The support 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.

3. The reflector assembly for space remote sensor 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 sensor according to claim 1, characterized in that: The plurality of mounting holes are arranged evenly spaced 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 end portion extends outwardly 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 comprises: S1: optically processing 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 bond 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, characterized in that: The support 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, characterized in that: 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, characterized in that: 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, characterized in that: 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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