Anti-torsion flexible supporting structure for space optical instrument

Abstract

The invention relates to the technical field of flexible supporting, in particular to an anti-torsion flexible supporting structure for a space optical instrument, which comprises a supporting flexible joint, a first connecting seat, a second connecting seat, a first elastic membrane and a second elastic membrane, the two ends of the supporting flexible joint are connected with the first connecting base and the second connecting base correspondingly. The first elastic membrane is arranged between the supporting flexible joint and the first connecting seat; the second elastic membrane is arranged between the supporting flexible joint and the second connecting seat; the first elastic membrane and the second elastic membrane achieve the anti-torsion function through high rigidity in the planes where the first elastic membrane and the second elastic membrane are located, and flexible supporting is achieved through low rigidity perpendicular to the planes. The flexible supporting structure has the advantages that through the supporting flexible joint, the first elastic membrane and the second elastic membrane, on the premise that radial flexible supporting of the flexible supporting structure is guaranteed, the torsional property is achieved, the use range of the flexible supporting structure is widened, and more use requirements are met.

Description

Technical Field

[0001] The invention relates to the technical field of flexible supports, and in particular to an anti-torsion flexible support structure for space optical instruments. Background Art

[0002] Space optical instruments use flexible joints to release the deformation of the supporting structure caused by external force changes. Currently, there are generally two types of performances of flexible joints in use: One is a flexible support structure with multi-directional flexibility but no torsion resistance. When the support structure is twisted, this flexible joint is easy to break. For example: The Chinese patent publication number is CN103792645A, the publication date is May 14, 2014, and the patent name is "A small mirror ultra-high thermal stability support structure" invention patent application, which discloses a flexible single-arm circumferentially uniformly distributed support structure with good flexibility but poor torsional resistance.

[0003] The Chinese patent publication number is CN102073123A, the publication date is May 25, 2011, and the patent name is "A single-point support flexible node for a small-aperture reflector of a space optical remote sensor". It discloses a support structure with radial unloading grooves and radial unloading grooves. Although it has good flexibility, its torsion resistance is insufficient.

[0004] The second is a flexible structure that has a certain degree of torsion resistance but can only release structural deformation in a specified direction. For example: The Chinese patent publication number is CN105259634A, and the publication date is January 20, 2016. The patent name is "A two-degree-of-freedom flexible node in a whiffletree support structure of a large-aperture reflector". The invention patent application discloses a flexible node structure composed of an orthogonal arrangement of an upper thin sheet and a lower thin sheet, which has a certain anti-torsion performance, but can only release structural deformation in a specified direction. Summary of the invention

[0005] In view of this, the present invention aims to provide a torsion-resistant flexible support structure for space optical instruments. Through the synergistic effect of the supporting flexible joint, the first elastic diaphragm and the second elastic diaphragm, the radial flexibility of the flexible support structure is ensured while also having torsion-resistant performance.

[0006] To achieve the above-mentioned purpose, the technical solution created by the present invention is implemented as follows: a torsion-resistant flexible support structure for space optical instruments, comprising: a supporting flexible node, a first connecting seat, a second connecting seat, a first elastic diaphragm and a second elastic diaphragm; one end of the supporting flexible node is connected to the first connecting seat, and the other end of the supporting flexible node is connected to the second connecting seat; the first elastic diaphragm is arranged between the supporting flexible node and the first connecting seat, and is connected to the supporting flexible node and the first connecting seat; the second elastic diaphragm is arranged between the supporting flexible node and the second connecting seat, and is connected to the supporting flexible node and the second connecting seat; the first elastic diaphragm and the second elastic diaphragm realize the torsion-resistant function through the high stiffness in their respective planes, and realize flexible support through the low stiffness perpendicular to the planes.

[0007] Furthermore, the first connecting seat and the second connecting seat have the same structure; the first connecting seat includes a first flexible sleeve and a first adapter plate, and the first flexible sleeve is detachably connected to the first adapter plate; the second connecting seat includes a second flexible sleeve and a second adapter plate, and the second flexible sleeve is detachably connected to the second adapter plate.

[0008] Furthermore, the supporting flexible joint includes a flexible shaft, a connecting plate and two connecting flanges; the two ends of the flexible shaft are respectively connected to the two connecting flanges; the connecting plate is sleeved on the outside of the flexible shaft; wherein, one connecting flange is located in the first flexible joint sleeve and is detachably connected to the first adapter plate; the other connecting flange is located in the second flexible joint sleeve and is detachably connected to the second adapter plate.

[0009] Furthermore, the supporting flexible joint is integrally formed.

[0010] Furthermore, the material of the supporting flexible joint is titanium alloy.

[0011] Furthermore, the material of the supporting flexible joint is TC17 titanium alloy.

[0012] Furthermore, the anti-torsion flexible support structure also includes a pad group, which includes three first pads, three second pads, three third pads and three fourth pads; wherein, the three first pads are evenly distributed along the circumference of the first elastic diaphragm on one side; the three second pads are evenly distributed along the circumference of the first elastic diaphragm on the other side; the three first pads and the three second pads are staggered in the circumferential direction of the first elastic diaphragm; the three third pads are evenly distributed along the circumference of the second elastic diaphragm on one side; the three fourth pads are evenly distributed along the circumference of the second elastic diaphragm on the other side; the three third pads and the three fourth pads are staggered in the circumferential direction of the second elastic diaphragm.

[0013] Furthermore, the first elastic diaphragm and the second elastic diaphragm are both annular plate structures.

[0014] Furthermore, the thickness of the first elastic membrane and the second elastic membrane are both 2 mm to 3 mm.

[0015] Furthermore, the materials of the first elastic diaphragm and the second elastic diaphragm are both 65Mn.

[0016] The invention can achieve the following beneficial effects: 1) The present invention ensures radial flexibility of the flexible support structure and also has torsion resistance through the synergistic effect of the supporting flexible joint, the first elastic diaphragm and the second elastic diaphragm. This not only expands the application scope of the flexible support structure, but also meets more diverse usage requirements.

[0017] 2) According to actual work requirements, different sizes of the first elastic diaphragm, the second elastic diaphragm and pads of different heights can be selected to optimize their adaptability to the supporting flexible joint, thereby improving the flexibility of the anti-torsion flexible support structure and reducing the use cost.

[0018] 3) The first elastic diaphragm, the second elastic diaphragm and the pad have a simple structure and are arranged between the first connecting seat and the second connecting seat. The size can be adjusted according to actual work requirements, so that the shape of the anti-torsion flexible support structure is regular and compact, the demand for installation space is low, and the flexibility is high.

[0019] 4) Through the staggered three-point connection of the first elastic diaphragm, the connecting plate and the first flexible sleeve, and the staggered three-point connection of the second elastic diaphragm, the connecting plate and the second flexible sleeve, the supporting flexible joint achieves flexible deformation and radial fixation within an axial range of 360°, thereby making the multi-directional flexible support structure anti-torsion and further expanding its scope of use. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] 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 is a cross-sectional view of an anti-torsion flexible support structure for a space optical instrument provided according to an embodiment of the present invention along its axis; Figure 2 is a schematic structural diagram of a first connecting socket provided according to an embodiment of the present invention; Figure 3 is a schematic structural diagram of a second connecting socket provided according to an embodiment of the present invention; Figure 4 Schematic diagram of the structure of a supporting flexible joint provided according to an embodiment of the present invention.

[0021] The accompanying drawings include: 1. first connecting seat; 11. first flexible sleeve; 111. first sleeve body; 112. first sleeve connecting part; 12. first adapter plate; 2. supporting flexible joint; 21. flexible shaft; 22. connecting plate; 221. connecting part; 222. connecting body; 23. connecting flange; 3. second connecting seat; 31. second flexible sleeve; 311. second sleeve body; 312. second sleeve connecting part; 32. second adapter plate; 33. second sleeve connecting part; 4. first elastic diaphragm; 5. second elastic diaphragm; 6. first pad; 7. second pad; 8. third pad; 9. fourth pad. DETAILED DESCRIPTION

[0022] In order to make the purpose, technical solution and advantages of the invention more clear, 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 here are only used to explain the invention and do not constitute a limitation of the invention.

[0023] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features in the embodiments may be combined with each other.

[0024] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" 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 technical features indicated. Thus, 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.

[0025] 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.

[0026] The present invention will be described in detail below with reference to the embodiments.

[0027] like Figures 1 to 4 As shown, an embodiment of the present invention provides an anti-torsion flexible support structure for a space optical instrument, comprising: a first connecting seat 1, a supporting flexible joint 2, a second connecting seat 3, a first elastic diaphragm 4, a second elastic diaphragm 5 and a pad group.

[0028] The first connection seat 1 has the same structure as the second connection seat 3. The first connection seat 1 includes a first flexible sleeve 11 and a first adapter plate 12, and the first flexible sleeve 11 is connected to the first adapter plate 12 by bolts. The second connection seat 3 includes a second flexible sleeve 31 and a second adapter plate 32, and the second flexible sleeve 31 is connected to the second adapter plate 32 by bolts.

[0029] The first flexible sleeve 11 includes a first sleeve body 111 and three first sleeve connecting parts 112. The three first sleeve connecting parts 112 are formed by the first sleeve body 111 extending radially outward and are evenly distributed. A first avoidance space is formed between two adjacent first sleeve connecting parts 112, and a weight reduction effect is achieved.

[0030] The second flexible sleeve 31 includes a second sleeve body 311 and three second sleeve connecting parts 312. The three second sleeve connecting parts 312 are formed by the second sleeve body 311 extending radially outward and are evenly distributed. A second avoidance space is formed between two adjacent second sleeve connecting parts 312, and a weight reduction effect is achieved.

[0031] In this embodiment, in order to facilitate the assembly of the anti-torsion flexible support structure, the first flexible sleeve 11, the first adapter plate 12, the second flexible sleeve 31 and the second adapter plate 32 are all independently processed and formed. Among them, the first connecting seat 1 and the first flexible sleeve 11 are connected to the first adapter plate 12 by bolts. The second flexible sleeve 31 is connected to the second adapter plate 32 by.

[0032] The support flexible joint 2 includes a flexible shaft 21, a connecting plate 22 and two connecting flanges 23. The two ends of the flexible shaft 21 are connected to the two connecting flanges 23 respectively. The connecting plate 22 is sleeved on the outside of the flexible shaft 21 and is located in the middle of the flexible shaft 21. Among them, one connecting flange 23 is located in the first flexible joint sleeve 11 and is connected to the first adapter plate 12 by bolts. The other connecting flange 23 is located in the second flexible joint sleeve 31 and is connected to the second adapter plate 32 by bolts. The coaxiality of the flexible shaft 21 with the first flexible joint sleeve 11 and the second flexible joint sleeve 31 is 0.01mm.

[0033] In this embodiment, the support flexible joint 2 is made of TC17 titanium alloy material and is formed by one-piece processing. TC17 not only has high strength, but also has good toughness and corrosion resistance. The connecting plate 22 includes a connecting body 222 and three connecting parts 221. The three connecting parts 221 are formed by the connecting body 222 extending radially outward and are evenly distributed. An avoidance space is formed between two adjacent connecting parts 221, and a weight reduction effect is achieved at the same time. Specifically, the three connecting parts 221, the three first sleeve connecting parts 112 and the three second sleeve connecting parts 312 are arranged in a staggered manner along the circumference of the supporting flexible joint 2. The three first sleeve connecting parts 112 and the three second sleeve connecting parts 312 are arranged one by one along the circumference of the supporting flexible joint 2.

[0034] The first elastic diaphragm 4 and the second elastic diaphragm 5 are both annular plate structures, and the thickness is 2mm to 3mm. The first elastic diaphragm 4 and the second elastic diaphragm 5 are sleeved on the outside of the flexible shaft 21 and are respectively located on both sides of the connecting plate 22. Specifically, the first elastic diaphragm 4 is arranged between the connecting plate 22 and the first flexible sleeve 11. The second elastic diaphragm 5 is arranged between the connecting plate 22 and the second flexible sleeve 31. In this embodiment, the material of the two elastic diaphragms is 65Mn. The thickness of the first elastic diaphragm 4 and the second elastic diaphragm 5 is 2.5mm.

[0035] The block group includes three first blocks 6 , three second blocks 7 , three third blocks 8 and three fourth blocks 9 .

[0036] The three first pads 6 are evenly distributed along the circumference of the first elastic diaphragm 4 between the first flexible sleeve 11 and the first elastic diaphragm 4 (on one side of the first elastic diaphragm 4 ), and the first elastic diaphragm 4 is connected to the three first sleeve connecting parts 112 via the three first pads 6 .

[0037] The three second pads 7 are evenly arranged between the first elastic diaphragm 4 and the connecting plate 22 (on the other side of the first elastic diaphragm 4 ) along the circumference of the first elastic diaphragm 4 . The three first pads 6 and the three second pads 7 are staggered in the circumferential direction of the first elastic diaphragm 4 .

[0038] The three third cushion blocks 8 are evenly distributed along the circumference of the second elastic diaphragm 5 and disposed between the connecting plate 22 and the second elastic diaphragm 5 (on one side of the second elastic diaphragm 5 ).

[0039] The bolts pass through the third cushion block 8 , the connecting portion 221 and the second cushion block 7 in sequence, connecting the second elastic diaphragm 5 , the first elastic diaphragm 4 and the connecting plate 22 together.

[0040] The three fourth pads 9 are evenly distributed along the circumference of the second elastic diaphragm 5 and are arranged between the second elastic diaphragm 5 and the second flexible sleeve 31 (the other side of the second elastic diaphragm 5). The second elastic diaphragm 5 is connected to the three second sleeve connecting parts 312 through the three fourth pads 9. The three third pads 8 and the three fourth pads 9 are staggered in the circumferential direction of the second elastic diaphragm 5.

[0041] The pad group is used to adjust the gap between the first flexible sleeve 11 and the first elastic diaphragm 4, between the first elastic diaphragm 4 and the connecting plate 22, between the connecting plate 22 and the second elastic diaphragm 5, and between the second elastic diaphragm 5 and the second flexible sleeve 31. According to the actual working conditions, pads of different heights are used for adjustment.

[0042] The first elastic diaphragm 4 is connected to the connection part 221 and the first flexible sleeve 11 by three-point connection, and the second elastic diaphragm 5 is connected to the connection part 221 and the second flexible sleeve 31 by three-point connection. The three-point connection avoids excessive constraints on the first elastic diaphragm 4 and the second elastic diaphragm 5, making the first elastic diaphragm 4 and the second elastic diaphragm 5 more evenly stressed and avoiding local stress concentration. At the same time, through the staggered three-point connection of the first elastic diaphragm 4, the connecting plate 22 and the first flexible sleeve 11, and the staggered three-point connection of the second elastic diaphragm 5, the connecting plate 22 and the second flexible sleeve 31, the support flexible joint 2 achieves flexible deformation and radial fixation within the axial range of 360°, so that the multi-directional flexible support structure has anti-torsion performance and further expands its scope of use.

[0043] The first elastic diaphragm 4 and the second elastic diaphragm 5 have high rigidity in their respective planes and are not easily deformed. When the anti-torsion flexible support structure is subjected to a torsional force, the force is transmitted to the first elastic diaphragm 4 and the second elastic diaphragm 5 through the support flexible joint 2, so that the first elastic diaphragm 4 and the second elastic diaphragm 5 will undergo slight elastic deformation in the plane. Due to their high rigidity characteristics, the first elastic diaphragm 4 and the second elastic diaphragm 5 can resist the torsional force and maintain the stability of the structure.

[0044] At the same time, the first elastic diaphragm 4 and the second elastic diaphragm 5 have low rigidity in the direction perpendicular to the plane (i.e., thickness direction), and are prone to deformation. When the anti-torsion flexible support structure is subjected to a force perpendicular to the plane where the first elastic diaphragm 4 and the second elastic diaphragm 5 are located, the force is transmitted to the first elastic diaphragm 4 and the second elastic diaphragm 5 through the support flexible joint 2, causing the first elastic diaphragm 4 and the second elastic diaphragm 5 to undergo a large elastic deformation in the vertical direction, thereby making the anti-torsion flexible support structure have good flexibility in the radial direction, and can adapt to changes in external loads and provide flexible support.

[0045] 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 torsion-resistant flexible support structure for a space optical instrument, characterized in that: include: Supporting flexible joint, first connecting seat, second connecting seat, first elastic diaphragm and second elastic diaphragm; One end of the supporting flexible joint is connected to the first connecting seat, and the other end of the supporting flexible joint is connected to the second connecting seat; The first elastic diaphragm is disposed between the supporting flexible joint and the first connecting seat, and is connected to the supporting flexible joint and the first connecting seat; the second elastic diaphragm is disposed between the supporting flexible joint and the second connecting seat, and is connected to the supporting flexible joint and the second connecting seat; The first elastic diaphragm and the second elastic diaphragm achieve anti-torsion function through high rigidity in the planes where they are located, and achieve flexible support through low rigidity perpendicular to the planes.

2. The torsion-resistant flexible support structure for a space optical instrument according to claim 1, characterized in that: The first connecting seat has the same structure as the second connecting seat; the first connecting seat includes a first flexible sleeve and a first adapter plate, and the first flexible sleeve is detachably connected to the first adapter plate; the second connecting seat includes a second flexible sleeve and a second adapter plate, and the second flexible sleeve is detachably connected to the second adapter plate.

3. The torsion-resistant flexible support structure for a space optical instrument according to claim 2, characterized in that: The supporting flexible joint comprises a flexible shaft, a connecting plate and two connecting flanges; the two ends of the flexible shaft are respectively connected to the two connecting flanges; the connecting plate is sleeved on the outside of the flexible shaft; Among them, one of the connecting flanges is located in the first flexible sleeve and is detachably connected to the first adapter plate; the other connecting flange is located in the second flexible sleeve and is detachably connected to the second adapter plate.

4. The torsion-resistant flexible support structure for a space optical instrument according to claim 3, characterized in that: The supporting flexible joint is integrally formed.

5. The torsion-resistant flexible support structure for a space optical instrument according to claim 1, characterized in that: The material of the supporting flexible joint is titanium alloy.

6. The torsion-resistant flexible support structure for a space optical instrument according to claim 5, characterized in that: The material of the supporting flexible joint is TC17 titanium alloy.

7. The torsion-resistant flexible support structure for a space optical instrument according to claim 1, characterized in that: The anti-torsion flexible support structure further includes a pad block group, wherein the pad block group includes three first pad blocks, three second pad blocks, three third pad blocks and three fourth pad blocks; Among them, three first pads are evenly arranged on one side of the first elastic diaphragm along the circumference of the first elastic diaphragm; three second pads are evenly arranged on the other side of the first elastic diaphragm along the circumference of the first elastic diaphragm; the three first pads and the three second pads are staggered in the circumferential direction of the first elastic diaphragm; The three third pads are evenly distributed on one side of the second elastic diaphragm along the circumference of the second elastic diaphragm; the three fourth pads are evenly distributed on the other side of the second elastic diaphragm along the circumference of the second elastic diaphragm; the three third pads and the three fourth pads are staggered in the circumferential direction of the second elastic diaphragm.

8. The torsion-resistant flexible support structure for a space optical instrument according to claim 1, characterized in that: The first elastic diaphragm and the second elastic diaphragm are both annular plate structures.

9. The torsion-resistant flexible support structure for a space optical instrument according to claim 1, characterized in that: The thickness of the first elastic membrane and the second elastic membrane are both 2 mm to 3 mm.

10. The torsion-resistant flexible support structure for a space optical instrument according to claim 1, characterized in that: The materials of the first elastic diaphragm and the second elastic diaphragm are both 65Mn.

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