A distributed omnidirectional stress decoupling flexible support structure for a super-large aperture mirror

Abstract

The present application relates to the technical field of space optical remote sensing, and specifically provides a distributed omnidirectional stress decoupling flexible support structure of an ultralarge-aperture mirror, wherein a plurality of XY flexible blade mechanisms and an upper end interface are arranged in a top cover plate, a rigid cylinder wall is sequentially provided from top to bottom with a flexible blade mechanism rotating around an X axis, a flexible blade mechanism rotating around a Y axis and a Z-direction flexible blade mechanism, an installation seat is arranged on the rigid cylinder, and a lower end interface for connecting the base is arranged on the installation seat; the structure can withstand the severe mechanical environment in the emission stage, can effectively adapt to various deformations during on-orbit operation, has the advantages of high reliability, large deformation capacity and stress concentration avoidance. Three groups of supports constitute a kinematic support system, which is suitable for high-precision support of an ultralarge-aperture mirror.

Description

Technical Field

[0001] This invention belongs to the field of space optical remote sensing technology, and particularly relates to a distributed omnidirectional stress decoupling flexible support structure for ultra-large aperture reflectors. Background Technology

[0002] As a core component of high-resolution space optical systems, the surface accuracy of ultra-large aperture mirrors directly determines the imaging quality of the system. However, the severe impacts and vibrations experienced during launch, as well as temperature changes, gravity release, and assembly stress during on-orbit operation, all lead to complex relative displacements between the mirror and its supporting base. If a rigid connection is used, these displacements will inevitably be converted into internal stresses acting on the mirror body, thereby causing mirror surface deformation and severely degrading the optical performance of the system.

[0003] To alleviate the aforementioned problems, existing technologies typically incorporate flexible support structures, such as various forms of flexible hinges or spring support systems. However, these conventional flexible support solutions still have several inherent limitations, making it difficult to meet the stringent requirements of high precision, high reliability, and long lifespan for ultra-large aperture mirrors. Specifically: Incomplete stress decoupling: Traditional structures struggle to achieve balanced and complete stress decoupling across all six degrees of freedom (three translational and three rotational) connecting the mirror and the base. Often, excessive constraints remain in specific directions, causing stress concentration at those points and failing to completely isolate the effects of base deformation on the mirror surface.

[0004] The contradiction between load-bearing capacity and flexibility requirements: To ensure the load-bearing capacity and structural stability of the mechanical environment during launch, the supporting structure must have sufficient stiffness, but this will weaken its ability to adapt to thermal deformation and deformation caused by gravity release in orbit; conversely, if stiffness is excessively reduced to improve on-orbit compliance, it will endanger the mechanical safety and on-orbit attitude stability during launch. This contradiction has become the core challenge of the design.

[0005] Long-term reliability and fatigue risk: Local stress concentration caused by incomplete stress decoupling can significantly reduce the fatigue life of critical components. Under long-term on-orbit missions or extreme mechanical environments, there is a potential risk of failure, which affects the mission reliability of the entire optical system.

[0006] Limited adaptability to multidimensional complex deformations: For large-aperture mirrors, which undergo multidimensional and minute-level complex displacements due to factors such as gravity changes and assembly errors, the adaptive adjustment capability of traditional flexible structures is limited, making it difficult to achieve precise and smooth following and compensation.

[0007] Therefore, there is an urgent need in this field to overcome the existing technological bottlenecks and provide a novel flexible support structure for ultra-large aperture mirrors. This structure needs to be able to achieve multi-degree-of-freedom and complete stress decoupling during the on-orbit phase, while ensuring mechanical strength and stability during the launch phase. It should effectively adapt to complex deformations caused by the coupling of multiple physical fields such as heat and force, thereby fundamentally ensuring the surface accuracy of the mirror and the long-term imaging quality of the system. Summary of the Invention

[0008] In view of this, the purpose of this invention is to provide a distributed omnidirectional stress decoupling flexible support structure for ultra-large aperture mirrors to overcome the shortcomings of existing technologies. This structure is specifically designed for the support and positioning of ultra-large aperture mirrors in space cameras. It can achieve complete and balanced decoupling of stress in all six degrees of freedom (three translational and three rotational degrees of freedom) while ensuring the overall stiffness and strength required during launch and on-orbit phases. Through its unique distributed and omnidirectional flexible design, this structure can efficiently absorb and release the complex strain energy between the base and the mirror caused by changes in gravity, temperature, and assembly errors. This maximizes the isolation of the mirror's surface shape from external loads and environmental disturbances, fundamentally ensuring its surface accuracy and imaging quality during on-orbit operation.

[0009] To achieve the above objectives, the technical solution of the present invention is implemented as follows: A distributed omnidirectional stress decoupling flexible support structure for an ultra-large aperture reflector, disposed between the reflector and the base, includes: The supporting structure body is a hollow cylinder with an open bottom, including a top cover plate and a rigid cylinder. The top cover plate is provided with multiple XY flexible blade mechanisms and an upper interface. The XY flexible blade mechanisms are configured to provide flexibility in the X-axis translation, Y-axis translation, and rotation around the Z-axis. The upper interface is used to connect the reflector. The rigid cylinder wall is provided with a flexible blade mechanism rotating around the X-axis, a flexible blade mechanism rotating around the Y-axis, and a flexible blade mechanism in the Z-direction from top to bottom. The flexible blade mechanism rotating around the X-axis is configured to provide flexibility in the rotational direction around the X-axis; the flexible blade mechanism rotating around the Y-axis is configured to provide flexibility in the rotational direction around the Y-axis; and the flexible blade mechanism in the Z-direction is configured to provide flexibility in the translational direction in the Z-direction. The rigid cylinder has a mounting base on its bottom outer wall, and the mounting base has a lower end interface for connecting to the base.

[0010] The XY flexible blade mechanism includes an inner L-shaped narrow groove, an outer L-shaped narrow groove, an arc-shaped through groove, and an L-shaped thin-walled flexible blade formed in the top cover plate. The inner L-shaped narrow groove is located inside the outer L-shaped narrow groove, and both are L-shaped through grooves. The solid portion between the two grooves forms the L-shaped thin-walled flexible blade. The outer L-shaped narrow groove and the inner L-shaped narrow groove of two adjacent XY flexible blade mechanisms are connected by the arc-shaped through groove.

[0011] The flexible blade mechanism that rotates around the X-axis includes symmetrically arranged downward L-shaped narrow slots, wherein the solid portion between the two slots forms a thin-walled flexible blade.

[0012] The downward L-shaped narrow groove includes a downward strip-shaped narrow groove and an arc-shaped through groove II. The arc-shaped through groove II has downward strip-shaped narrow grooves at both ends, and the solid portion between the two downward L-shaped narrow grooves forms a thin-walled flexible blade I.

[0013] The flexible blade mechanism that rotates around the Y-axis includes symmetrically arranged upward L-shaped narrow slots, wherein the solid portion between the two slots forms a thin-walled flexible blade II.

[0014] The upward L-shaped narrow groove includes an upward strip-shaped narrow groove and an arc-shaped through groove three. The arc-shaped through groove three has an upward strip-shaped narrow groove above each of its two ends, and the solid portion between the two upward L-shaped narrow grooves forms a thin-walled flexible blade two.

[0015] The Z-axis flexible blade mechanism includes a symmetrically arranged left arc-shaped narrow groove and a right arc-shaped narrow groove, as well as a flexible portion formed by the solid portion between the two grooves.

[0016] The support structure is made of titanium alloy material in one piece.

[0017] An ultra-large aperture reflector assembly includes a reflector, a base, and at least one set of distributed omnidirectional stress decoupling flexible support structures for the ultra-large aperture reflector; the upper interface of the support structure is connected to the reflector, and the lower interface is connected to the base.

[0018] The ultra-large aperture reflector assembly includes three sets of flexible support structures. The back of the reflector is provided with three inlays, and the inlays are connected to the upper interfaces of the three sets of support structures one by one.

[0019] A space optical remote sensing device, comprising an ultra-large aperture mirror assembly.

[0020] Compared with the prior art, the present invention can achieve the following beneficial effects: Omnidirectional stress decoupling: Through the synergistic action of the XY flexible blade mechanism, the flexible blade mechanism rotating around the X-axis, the flexible blade mechanism rotating around the Y-axis, and the Z-axis flexible blade mechanism, specific degrees of freedom are released in two directions respectively, thus achieving motion and stress decoupling of all six degrees of freedom and fundamentally preventing stress from being transmitted to the reflector.

[0021] High reliability: The flexible blade mechanism avoids stress concentration and improves the fatigue life of the structure, enabling it to withstand high-intensity impacts and vibrations during launch and to work stably in orbit for a long time.

[0022] Large deformation capacity: This flexible design allows the supporting structure to undergo large elastic deformation, thereby effectively absorbing thermal expansion deformation caused by temperature changes and displacement caused by changes in gravity attitude.

[0023] Kinematic support: The distributed arrangement of three sets of supports forms a defined kinematic constraint, which ensures the stability of the support while releasing unnecessary constraints to the maximum extent, thus ensuring the stability of the reflector surface shape.

[0024] Parametric design: By adjusting key structural parameters (such as T1, L1, T2, L2, H, T3, L4), the adaptability of the support structure to different factors such as gravity and assembly errors can be precisely optimized, thus achieving customized design. Attached Figure Description

[0025] The accompanying drawings, which form part of this invention, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings: Figure 1 This is a schematic diagram of the structure of the present invention.

[0026] Figure 2 This is a cross-sectional view of the present invention.

[0027] Figure 3 This is a cross-sectional view of the invention from another direction.

[0028] Figure 4 This is a top view of the present invention.

[0029] Figure 5 for Figure 2 A sectional view along the AA direction.

[0030] Figure 6 This is a schematic diagram of the XY flexible blade mechanism structure of the present invention.

[0031] Figure 7 This is a schematic diagram of the flexible blade mechanism rotating around the X-axis according to the present invention. Figure 8This is a schematic diagram of the flexible blade mechanism that rotates around the Y-axis according to the present invention.

[0032] Figure 9 This is a schematic diagram of the Z-axis flexible blade mechanism of the present invention.

[0033] Figure 10 This is a schematic diagram of the parameters of the XY flexible blade mechanism of the present invention.

[0034] Figure 11 This is a schematic diagram of the parameters of the Z-axis flexible blade mechanism of the present invention.

[0035] Figure 12 This is a schematic diagram illustrating the usage state of the present invention.

[0036] Figure 13 This is a schematic diagram of the key design parameters of the present invention.

[0037] Wherein: 1-Upper interface; 2-XY flexible blade mechanism; 3-Flexible blade mechanism rotating around the X-axis; 4-Flexible blade mechanism rotating around the Y-axis; 5-Z-Flexible blade mechanism; 6-Rigid cylinder; 7-Lower interface; 8-Reflector; 201-Inner L-shaped narrow groove; 202-Outer L-shaped narrow groove; 203-L-shaped thin-walled flexible blade; 301-Arc-shaped through groove II; 302-Downward strip-shaped narrow groove; 303-Thin-walled flexible blade I; 401-Arc-shaped through groove three; 402-Upward strip-shaped narrow groove; 403-Thin-walled flexible blade two; 501 - Left arc-shaped narrow groove; 502 - Right arc-shaped narrow groove; 503 - Flexible part. Detailed Implementation

[0038] 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. Similar elements in different embodiments are referred to by associated similar element reference numerals. In the following embodiments, many details are described to facilitate a better understanding of the invention. However, those skilled in the art will readily recognize that some features may be omitted in different situations, or may be replaced by other elements, materials, or methods. In some cases, certain operations related to the invention are not shown or described in the specification. This is to avoid obscuring the core parts of the invention with excessive description. For those skilled in the art, detailed description of these related operations is not necessary; they can fully understand the related operations based on the description in the specification and general technical knowledge in the art.

[0039] It should be noted that, unless otherwise specified, the embodiments and features described in this invention can be combined to form various implementations. Furthermore, the order of the steps or actions in the method description can be changed or adjusted in a manner readily apparent to those skilled in the art. Therefore, the various orders in the specification and drawings are merely for the clear description of a particular embodiment and do not imply a mandatory order, unless otherwise stated that a particular order must be followed.

[0040] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," and "counterclockwise," etc., indicating orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, are only for the convenience of describing the invention 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, and therefore should not be construed as a limitation of the invention. Furthermore, the terms "first," "second," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined with "first," "second," etc., may explicitly or implicitly include one or more of that feature. In the description of this invention, unless otherwise stated, "a plurality of" means two or more.

[0041] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art will understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0042] The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0043] Example 1: Please see Figure 1-9 As shown, in one embodiment of the present invention, a distributed omnidirectional stress decoupling flexible support structure for an ultra-large aperture reflector is disposed between the reflector 8 and the base, wherein a three-dimensional coordinate system is established with the center of the top surface of the hollow cylinder, i.e., the top surface of the top cover plate, as the origin, as follows: Figure 10 As shown, the horizontal direction is the X-axis, the vertical direction is the Y-axis, and the Z-axis is determined by the right-hand rule. Accordingly, the X-axis direction is the X-direction, the Y-axis direction is the Y-direction, and the Z-axis direction is the Z-direction.

[0044] The supporting structure includes: The supporting structure body is a hollow cylinder with an open bottom, including a top cover plate and a rigid cylinder 6. The top cover plate is provided with multiple XY flexible blade mechanisms 2 and an upper interface 1. The XY flexible blade mechanisms 2 are configured to provide flexibility in the X-axis translation, Y-axis translation and rotation around the Z-axis. The upper interface 1 is used to connect the reflector 8. The rigid cylinder 6 has, from top to bottom, a flexible blade mechanism 3 rotating around the X-axis, a flexible blade mechanism 4 rotating around the Y-axis, and a flexible blade mechanism 5 in the Z-direction. The flexible blade mechanism 3 rotating around the X-axis is configured to provide flexibility in the rotational direction around the X-axis; the flexible blade mechanism 4 rotating around the Y-axis is configured to provide flexibility in the rotational direction around the Y-axis; and the flexible blade mechanism 5 in the Z-direction is configured to provide flexibility in the translational direction in the Z-direction. The rigid cylinder 6 has a mounting base on its bottom outer wall, and the mounting base has a lower end interface 7 for connecting to the base.

[0045] The XY flexible blade mechanism 2 includes an inner L-shaped narrow groove 201, an outer L-shaped narrow groove 202, an arc-shaped through groove 1, and an L-shaped thin-walled flexible blade 203 formed in the top cover plate. The inner L-shaped narrow groove 201 is located inside the outer L-shaped narrow groove 202. Both are L-shaped through grooves, that is, they are arranged vertically through the top cover plate. At the same time, they are parallel to each other, that is, their two sides are parallel respectively. The solid part between the two grooves forms the L-shaped thin-walled flexible blade 203. The outer L-shaped narrow groove 202 and the inner L-shaped narrow groove 201 of two adjacent XY flexible blade mechanisms 2 are connected by the arc-shaped through groove 1.

[0046] The inner L-shaped narrow groove 201, the outer L-shaped narrow groove 202, and the arc-shaped through groove are the material removal parts on the top cover plate, while the L-shaped thin-walled flexible blade 203 is the material retention part on the top cover plate.

[0047] The flexible blade mechanism 3 that rotates around the X-axis includes symmetrically arranged downward L-shaped narrow slots, wherein the solid portion between the two slots forms a thin-walled flexible blade 303.

[0048] The downward L-shaped narrow groove includes a downward strip-shaped narrow groove 302 and an arc-shaped through groove 301. The arc-shaped through groove 301 has downward strip-shaped narrow grooves 302 at both ends, and the solid portion between the two downward L-shaped narrow grooves forms a thin-walled flexible blade 303.

[0049] The flexible blade mechanism 4 that rotates around the Y-axis includes symmetrically arranged upward L-shaped narrow slots, wherein the solid portion between the two slots forms a thin-walled flexible blade 403.

[0050] The downward-facing narrow strip 302 and the arc-shaped through groove 301 are the material removal parts, while the thin-walled flexible blade 303 is the material retention part.

[0051] The upward L-shaped narrow groove includes an upward strip-shaped narrow groove 402 and an arc-shaped through groove 401. The arc-shaped through groove 401 has an upward strip-shaped narrow groove 402 above both ends, and the solid portion between the two upward L-shaped narrow grooves forms a thin-walled flexible blade 403.

[0052] The upward-facing narrow strip 402 and the arc-shaped through groove 401 are the material removal parts, while the thin-walled flexible blade 403 is the material retention part.

[0053] The Z-axis flexible blade mechanism 5 includes a symmetrically arranged left arc-shaped narrow groove 501 and a right arc-shaped narrow groove 502, as well as a flexible portion 503 formed by the solid portion between the two grooves.

[0054] The left arc-shaped narrow groove 501 and the right arc-shaped narrow groove 502 are the material removal parts, and the flexible part 503 is the material retention part.

[0055] The supporting structure body is integrally formed from titanium alloy material (such as TC4) to ensure structural integrity and consistency.

[0056] When using, such as Figure 12 As shown, three sets of flexible support structures are employed, which are distributed on the back of the reflector 8 to form a kinematic support system. Furthermore, the three sets of support structures are symmetrically distributed around the center of the reflector 8.

[0057] The back of the reflector 8 is provided with three inlays, and the inlays are connected to the upper interfaces 1 of the three sets of support structures one by one by screws; the lower interfaces 7 of the three sets of support structures are fixedly connected to the camera platform or the base of the reflector 8 by screws.

[0058] The XY flexible blade mechanism 2, the flexible blade mechanism 3 rotating around the X-axis, the flexible blade mechanism 4 rotating around the Y-axis, and the Z-axis flexible blade mechanism 5 work together to enable the upper interface 1 to generate elastic displacement in all six degrees of freedom relative to the lower interface 7, thereby achieving decoupling of stress transmission from the lower interface 7 to the upper interface 1.

[0059] The flexibility of the XY flexible blade mechanism 2 is adjusted by its thickness T1 and length L1, where T1 is the distance between the inner L-shaped narrow groove 201 and the outer L-shaped narrow groove 202, and L1 is the length of any side of the outer L-shaped narrow groove 202, wherein the two sides of the outer L-shaped narrow groove 202 are of equal length, and the two sides of the inner L-shaped narrow groove 201 are of equal length.

[0060] The flexibility of the flexible blade mechanism 3 rotating around the X-axis is adjusted by its thickness T2 and length L2, where T2 is the distance between two adjacent downward strip-shaped narrow slots 302 and L2 is the length of the downward strip-shaped narrow slots 302.

[0061] The flexibility of the Z-axis flexible blade mechanism 5 is adjusted by its thickness T3 and length L3, where T3 is the distance between the arc-shaped through groove 401 and the left arc-shaped narrow groove 501, and L3 is the projected length of the right arc-shaped narrow groove 502 on the YOZ plane.

[0062] The adaptability of the support structure to gravity deformation is optimized by adjusting the center height H (center height of thin-walled flexible blade 303 or thin-walled flexible blade 403) of the flexible blade rotating around the X / Y axis in the vertical direction. Where H = (H1 + H2) / 2, H1 is the distance between the bottom of the arc-shaped through groove 301 and the top of the top cover plate, and H2 is the distance between the bottom of the downward-facing narrow strip groove 302 and the top of the top cover plate.

[0063] The height H is used to optimize the structure's adaptability to gravity deformation; T1, L1, T2, L2, T3, and L3 are used to optimize the structure's adaptability to thermal deformation and assembly errors.

[0064] See Figure 10 , Figure 11 and Figure 13 The key design parameters of the supporting structure are clearly identified. These parameters can be optimized through finite element analysis.

[0065] When the reflector 8 is displaced relative to the base, the XY flexible blade mechanism 2 and the Z flexible blade mechanism 5 undergo elastic deformation, causing the upper interface 1 to undergo three-dimensional translation and three-dimensional rotation relative to the lower interface 7, thereby absorbing strain energy and preventing stress from being transmitted from the lower interface 7 to the upper interface 1.

[0066] Working principle: During ground assembly and adjustment, and in-orbit operation, due to temperature field changes, the materials of the reflector 8 and the base have different coefficients of thermal expansion, causing relative displacement between them. At this time, the XY flexible blade mechanism 2 absorbs the translational motion in the X and Y directions and the rotation about the Z-axis through its in-plane bending deformation; simultaneously, the flexible blade mechanism 3 rotating about the X-axis absorbs the rotation about the X-axis through bending deformation, the flexible blade mechanism 4 rotating about the Y-axis absorbs the rotation about the Y-axis through bending deformation, and the Z-axis flexible blade mechanism 5 absorbs the translational motion in the Z-direction through its axial stretching / compression and bending deformation. This process stores the strain energy generated by the relative displacement in the elastic deformation of the flexible blades, rather than transferring it to the reflector 8, thus protecting the surface accuracy of the mirror.

[0067] In practical applications, the three sets of support structures are usually symmetrically distributed at 120° on the back of the circular reflector 8 and connected to the three inlays on the back of the mirror to form a complete kinematic support system, so as to achieve optimal support and protection for the ultra-large diameter reflector.

[0068] In summary, the above description is merely a preferred embodiment of this specification and is not intended to limit the scope of protection of this specification. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this specification should be included within the scope of protection of this specification.

[0069] The various embodiments in this specification are described in a progressive manner. Similar or identical parts between embodiments can be referred to interchangeably. Each embodiment focuses on describing the differences from other embodiments. In particular, the system embodiments are basically similar to the method embodiments, so the description is relatively simple; relevant parts can be referred to the descriptions in the method embodiments.

Claims

1. A distributed omnidirectional stress decoupling flexible support structure for an ultra-large aperture reflector, disposed between the reflector and the base, characterized in that, include: The supporting structure body is a hollow cylinder with an open bottom, including a top cover plate and a rigid cylinder. The top cover plate is provided with multiple XY flexible blade mechanisms and an upper interface. The XY flexible blade mechanisms are configured to provide flexibility in the X-axis translation, Y-axis translation, and rotation around the Z-axis. The upper interface is used to connect the reflector. The rigid cylinder wall is provided with a flexible blade mechanism rotating around the X-axis, a flexible blade mechanism rotating around the Y-axis, and a flexible blade mechanism in the Z-direction from top to bottom. The flexible blade mechanism rotating around the X-axis is configured to provide flexibility in the rotational direction around the X-axis; the flexible blade mechanism rotating around the Y-axis is configured to provide flexibility in the rotational direction around the Y-axis; and the flexible blade mechanism in the Z-direction is configured to provide flexibility in the translational direction in the Z-direction. The rigid cylinder has a mounting base on its bottom outer wall, and the mounting base has a lower end interface for connecting to the base.

2. The distributed omnidirectional stress decoupling flexible support structure for an ultra-large aperture reflector according to claim 1, characterized in that, The XY flexible blade mechanism includes an inner L-shaped narrow groove, an outer L-shaped narrow groove, an arc-shaped through groove, and an L-shaped thin-walled flexible blade formed in the top cover plate. The inner L-shaped narrow groove is located inside the outer L-shaped narrow groove, and both are L-shaped through grooves. The solid portion between the two grooves forms the L-shaped thin-walled flexible blade. The outer L-shaped narrow groove and the inner L-shaped narrow groove of two adjacent XY flexible blade mechanisms are connected by the arc-shaped through groove.

3. The distributed omnidirectional stress decoupling flexible support structure for an ultra-large aperture reflector according to claim 1, characterized in that, The flexible blade mechanism that rotates around the X-axis includes symmetrically arranged downward L-shaped narrow slots, wherein the solid portion between the two slots forms a thin-walled flexible blade.

4. The distributed omnidirectional stress decoupling flexible support structure for an ultra-large aperture reflector according to claim 3, characterized in that, The downward L-shaped narrow groove includes a downward strip-shaped narrow groove and an arc-shaped through groove II. The arc-shaped through groove II has downward strip-shaped narrow grooves at both ends, and the solid portion between the two downward L-shaped narrow grooves forms a thin-walled flexible blade I.

5. The distributed omnidirectional stress decoupling flexible support structure for an ultra-large aperture reflector according to claim 1, characterized in that, The flexible blade mechanism that rotates around the Y-axis includes symmetrically arranged upward L-shaped narrow slots, wherein the solid portion between the two slots forms a thin-walled flexible blade II.

6. The distributed omnidirectional stress decoupling flexible support structure for an ultra-large aperture reflector according to claim 5, characterized in that, The upward L-shaped narrow groove includes an upward strip-shaped narrow groove and an arc-shaped through groove three. The arc-shaped through groove three has an upward strip-shaped narrow groove above each of its two ends, and the solid portion between the two upward L-shaped narrow grooves forms a thin-walled flexible blade two.

7. The distributed omnidirectional stress decoupling flexible support structure for an ultra-large aperture reflector according to claim 1, characterized in that, The Z-axis flexible blade mechanism includes a symmetrically arranged left arc-shaped narrow groove and a right arc-shaped narrow groove, as well as a flexible portion formed by the solid portion between the two grooves.

8. The distributed omnidirectional stress decoupling flexible support structure for an ultra-large aperture reflector according to claim 1, characterized in that, The support structure is made of titanium alloy material in one piece.

9. A large-aperture reflector assembly, characterized in that, It includes a reflector, a base, and at least one set of distributed omnidirectional stress decoupling flexible support structures for ultra-large aperture reflectors as described in any one of claims 1-8; the upper interface of the support structure is connected to the reflector, and the lower interface is connected to the base.

10. The ultra-large aperture reflector assembly according to claim 9, characterized in that, It includes three sets of flexible support structures, and the back of the reflector is provided with three inlays, which are connected to the upper interfaces of the three sets of support structures one by one.

11. A space optical remote sensing device, characterized in that, Includes the ultra-large aperture reflector assembly as described in claim 9 or 10.

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