Closed composite structure substrate for space camera

Abstract

The application provides a closed composite structure substrate applied to a space camera, and the optical substrate comprises a central high-stability area, a force-bearing cylinder and a carbon fiber frame plate which are sequentially arranged from inside to outside, and an envelope area of the optical substrate is covered with a skin to form a closed shell structure substrate; the central high-stability area comprises a metal matrix composite central cylinder, and an outer annular surface of the central cylinder is provided with a metal matrix composite main support framework, an auxiliary support framework and a carbon fiber auxiliary support framework; the central high-stability area and the carbon fiber frame plate are both internally filled with isotropic hexagonal flange carbon honeycombs. The central high-stability area composed of the metal matrix composite, the frame plate with the carbon fiber material structure and the honeycomb layout design can guarantee high rigidity and high stability of the substrate, and the weight reduction advantage is remarkable, and the material cost is reduced; the inlay layout of the special-shaped heat pipe, the support structure and the force-bearing cylinder optimizes the size and the precision stability of the whole substrate.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of optical remote sensing, in particular to a closed composite structure substrate applied to a space camera. BACKGROUND

[0002] The optical substrate of a space camera is an important platform for a single machine load of an optical remote sensing system. The structural performance indicators such as weight, stiffness bearing capacity, dimensional stability, and precision stability of the optical substrate will directly determine the precision and performance of the optical system carried. With the development trend of long focal length, wide width, and high resolution of optical remote sensing systems, there is a demand for large size, lightweight, high stiffness, and high stability of the substrate structure.

[0003] Compared with the structure of the previous optical substrate, the size is conventional and metal materials are often used in combination with hollowing to reduce weight; or a traditional honeycomb plate structure is used. However, when a large camera load is carried and the running precision requirement is high, the substrate is upgraded to a large scale, and from the aspects of material selection and preparation, weight and structure design, size and precision stability, the original structure design technology cannot meet the requirements. The following patents are compared:

[0004] As disclosed in patent document CN 113970867 B, a tower type camera structure applied to a coaxial four-mirror optical system is disclosed, wherein the optical substrate structure is hexagonal, lightened by polygonal hollowing, and the material is beryllium aluminum alloy. The substrate using metal materials in combination with topological lightweight design has problems of size demand not met by the preparation of raw materials and weight out-of-tolerance in large scale substrate design.

[0005] Patent document CN 105466470 A discloses a large space optical remote sensor composite light barrier plate, which uses carbon fiber material to realize lightweight of the light barrier substrate. However, the structure is a non-bearing structure and cannot carry the load for mechanical examination.

[0006] Therefore, it is necessary to provide a closed composite structure substrate applied to a space camera to meet the demand for large size, lightweight, high stiffness, and high stability. SUMMARY

[0007] In view of the defects in the prior art, the purpose of the present application is to provide a closed composite structure substrate applied to a space camera.

[0008] According to the closed composite structure substrate applied to a space camera provided by the present application, the optical substrate comprises a central high stability area, a force bearing cylinder, and a carbon fiber frame plate arranged from inside to outside, and the envelope area of the optical substrate is covered with a skin to form a closed shell structure substrate.

[0009] Two sides of the optical substrate are respectively: an optical substrate camera surface and an optical substrate single machine surface, a carbon fiber ring belt is arranged at a light shield cover mounting interface of the optical substrate camera surface, and discrete metal matrix composite patches are inlaid on the carbon fiber ring belt.

[0010] The central high-stability region comprises a metal matrix composite central cylinder, and a plurality of metal matrix composite main support skeletons, a plurality of metal matrix composite auxiliary support skeletons and a plurality of carbon fiber auxiliary support skeletons are uniformly arranged on the outer ring surface of the metal matrix composite central cylinder in the circumferential direction.

[0011] The carbon fiber frame plate comprises a plurality of rectangular frame tubes on the inner side and a closed frame tube on the outer side, and the plurality of rectangular frame tubes are arranged in the force transmission path extension direction of the support skeletons of the central high-stability region.

[0012] The central high-stability region and the carbon fiber frame plate are both filled with isotropically arranged hexagonal flange carbon honeycombs.

[0013] Preferably, the skin comprises an integral carbon fiber skin without splicing, two pieces of the skin are respectively glued to cover the optical substrate camera surface and the optical substrate single machine surface, the outer edge of the skin matches the outer edge of the carbon fiber frame plate, the skin is not covered only in the metal matrix composite central cylinder region, and the skin is perforated at the single machine connection position.

[0014] Preferably, the load-bearing cylinder is a circular carbon fiber cylinder, the load-bearing cylinder comprises a load-bearing inner cylinder skin, an aluminum honeycomb core sandwich and a load-bearing outer cylinder skin arranged in sequence from inside to outside, the upper and lower ends of the load-bearing inner cylinder skin are both inwardly extended to form skin flanges, the upper and lower ends of the load-bearing outer cylinder skin are both outwardly extended to form skin flanges, the skin flanges are parallel to and glued to the skin, the outer side of the skin of the optical substrate single machine surface is provided with a second carbon fiber ring belt, and the second carbon fiber ring belt is arranged correspondingly to the aluminum honeycomb core sandwich.

[0015] Preferably, the carbon fiber ring belt is arranged correspondingly to the aluminum honeycomb core sandwich, one side of the metal matrix composite patch is formed with a protruding platform, the metal matrix composite patch is embedded in the carbon fiber ring belt through the protruding platform and is glued to the carbon fiber ring belt, and the angle distribution and arc length of the metal matrix composite patch and the light shield cover mounting interface are consistent.

[0016] Preferably, the metal matrix composite center cylinder is a two-radiused closed hollow annular disc structure of upper and lower butt welding, the metal matrix composite main support framework is a two-crossed hollow rectangular frame structure of upper and lower butt welding, a single machine installation protruding platform is arranged on the metal matrix composite main support framework, the metal matrix composite auxiliary support framework is a I-shaped hollow rectangular frame structure, and the carbon fiber auxiliary support framework is a rectangular tube structure.

[0017] The metal matrix composite center cylinder is uniformly provided with three metal matrix composite main support frameworks and three metal matrix composite auxiliary support frameworks on the circumferential side, and the metal matrix composite main support frameworks and the metal matrix composite auxiliary support frameworks are arranged at intervals, and the carbon fiber auxiliary support framework is arranged between adjacent two metal matrix composite main support frameworks and metal matrix composite auxiliary support frameworks.

[0018] Preferably, the carbon fiber frame plate is a central symmetric structure, and a plurality of auxiliary support rectangular frame tubes are further arranged in the carbon fiber frame plate, two ends of the auxiliary support rectangular frame tubes are connected with the load bearing cylinder and the closed frame tube respectively, the rectangular frame tube, the closed frame tube and the auxiliary support rectangular frame tube are integrally formed, the load bearing cylinder is connected with a plurality of joints on the circumferential side, and the load bearing cylinder is fastened and connected with the carbon fiber frame plate through the joints.

[0019] Preferably, a plurality of type heat pipes are arranged in the cavities of the carbon fiber auxiliary support framework, the rectangular frame tube and the auxiliary support rectangular frame tube. The upper and lower fins of the type heat pipe are glued to the inner wall of the cavity.

[0020] The outer side wall of the load bearing cylinder is circumferentially provided with a plurality of space S type heat pipes, the plurality of space S type heat pipes are arranged in an annular staggered manner from bottom to top, and the upper and lower fins of the space S type heat pipe are respectively glued to the skin turn-ups at the upper and lower ends of the load bearing outer cylinder skin.

[0021] Preferably, the circumscribed circle diameter of the honeycomb core cell of the hexagonal turn-up carbon honeycomb is 1 / 3 of the height, the upper and lower parts of the honeycomb core cell are provided with inwardly extending turn-ups, the turn-up width is 5% of the height, the turn-up thickness is consistent with the honeycomb wall, the honeycomb wall of the hexagonal turn-up carbon honeycomb is in a quasi-isotropic direction of the thickness of the honeycomb core cell, and the arrangement mode of the hexagonal turn-up carbon honeycomb is to diverge in the normal direction of each edge surface of the honeycomb core cell and arrange one by one back to back.

[0022] Preferably, a plurality of carbon fiber inserts are arranged at the single-machine installation interface of the single-machine surface of the optical substrate, the carbon fiber inserts are in an equilateral triangular configuration, each vertex of the triangle is a flat section, a through slot is formed longitudinally and connected with the hexagonal flange carbon honeycomb, and the carbon fiber inserts are bonded to the inner wall or node of the honeycomb core cell;

[0023] The single-machine surface of the optical substrate is provided with a plurality of circular discrete metal matrix composite patches, and a through hole is formed at the single-machine installation interface of the metal matrix composite patch.

[0024] Preferably, a plurality of tool lifting points are symmetrically and equidistantly arranged on the circumferential side of the closed frame tube, a tool lifting point insert of the tool lifting point is fastened and connected in the inner cavity of the closed frame tube, and a tool lifting point patch of the tool lifting point is glued on the outer side of the closed frame tube.

[0025] Compared with the prior art, the present application has the following beneficial effects:

[0026] The present application has a central high-stability region composed of a metal matrix composite material, which meets the conditions for high-precision operation of a single machine, and the remaining parts cooperate with the frame plate and the honeycomb layout design of the carbon fiber material to ensure high stiffness and stability of the structure while greatly reducing the weight and material cost, solving the problems of material preparation and processing scale of traditional single SiCal for large-scale substrates; the hexagonal flange carbon honeycomb structure fills the substrate, and the single-cell back-to-back arrangement improves the problem of in-plane mechanical anisotropy caused by the original traditional honeycomb core strip distribution; the inlaid layout of the special-shaped heat pipe, the supporting structure and the load-bearing cylinder optimizes the size and precision stability of the overall substrate. BRIEF DESCRIPTION OF DRAWINGS

[0027] Other features, objects and advantages of the present application will become more apparent from the following detailed description of non-limiting embodiments, which should be read in conjunction with the accompanying drawings:

[0028] Figure 1 The structure diagram mainly embodying the camera surface of the optical substrate of the present application;

[0029] Figure 2 The structure diagram mainly embodying the single-machine surface of the optical substrate of the present application;

[0030] Figure 3 The cross-sectional view of the optical substrate of the present application;

[0031] Figure 4 The structure diagram mainly embodying the carbon fiber frame plate of the present application;

[0032] Figure 5 The structure diagram mainly embodying the load-bearing cylinder of the present application;

[0033] Figure 6 Structure diagram of the metal matrix composite patch according to the present application;

[0034] Figure 7 Structure diagram of the joint according to the present application;

[0035] Figure 8 Structure diagram of the joint according to the present application;

[0036] Figure 9 Structure diagram of the joint according to the present application;

[0037] Figure 10 Structure diagram of the heat pipe according to the present application; Structure diagram of the heat pipe according to the present application;

[0038] Figure 11 Structure diagram of the heat pipe according to the present application;

[0039] Figure 12 Structure diagram of the honeycomb core cell according to the present application;

[0040] Figure 13 Structure diagram of the carbon fiber insert according to the present application;

[0041] Figure 14 Structure diagram of the tooling lifting point insert according to the present application;

[0042] Figure 15 Structure diagram of the tooling lifting point patch according to the present application.

[0043] The figure shows:

[0044] Optical substrate 1 Camera face 101 of optical substrate

[0045] Single machine face 102 of optical substrate Center high stability area 2

[0046] Metal matrix composite center cylinder 21 Main support framework 23 of metal matrix composite

[0047] Auxiliary support framework 24 of metal matrix composite Carbon fiber auxiliary support framework 25

[0048] Load bearing cylinder 3 Load bearing inner cylinder skin 31

[0049] Aluminum honeycomb core sandwich 32 Load bearing outer cylinder skin 33

[0050] Second carbon fiber ring belt 34 Carbon fiber ring belt 4

[0051] Metal matrix composite patch 42 Carbon fiber frame plate 5

[0052] joint 51 rectangular frame tube 52

[0053] closed frame tube 53 auxiliary support rectangular frame tube 54

[0054] hexagonal flange carbon honeycomb 6 honeycomb cell 61

[0055] skin 7 carbon fiber insert 8

[0056] discrete metal matrix composite patch 9 type heat pipe 1001

[0057] space S type heat pipe 1002 tooling lifting point 11

[0058] tooling lifting point insert 111 tooling lifting point patch 112 DETAILED DESCRIPTION

[0059] The application will be described in detail below with specific embodiments. The following examples will help those skilled in the art to further understand the application, but do not limit the application in any form. It should be noted that for those skilled in the art, without departing from the concept of the present application, a number of changes and improvements can be made. These are within the scope of the present application.

[0060] As Figures 1-4 shown, according to the closed composite structure substrate applied to the space camera provided by the application, the optical substrate 1 includes a central high stability area 2, a force bearing cylinder 3 and a carbon fiber frame plate 5 arranged in turn from inside to outside, and the envelope area of the optical substrate 1 is covered with a skin 7 to form a closed shell structure substrate; the two sides of the optical substrate 1 are respectively an optical substrate camera face 101 and an optical substrate single machine face 102, and a carbon fiber ring belt 4 is arranged at the light shield mounting interface of the optical substrate camera face 101, and the carbon fiber ring belt 4 is inlaid with discrete metal matrix composite patches 42; the central high stability area 2 includes a metal matrix composite center cylinder 21, and the outer ring surface of the metal matrix composite center cylinder 21 is uniformly provided with a plurality of metal matrix composite main support skeletons 23, a plurality of metal matrix composite auxiliary support skeletons 24 and a plurality of carbon fiber auxiliary support skeletons 25 in the circumferential direction; the carbon fiber frame plate 5 includes a plurality of rectangular frame tubes 52 on the inside and a closed frame tube 53 on the outside, and the plurality of rectangular frame tubes 52 are arranged in the force transmission path extension direction of the support skeletons of the central high stability area 2; the interiors of the central high stability area 2 and the carbon fiber frame plate 5 are both filled with isotropic arrangement of hexagonal flange carbon honeycomb 6.

[0061] The application is applied to a large-scale, light-weight and high-stiffness space camera mounting substrate. The central high-stability area 2 comprises a metal matrix composite central cylinder 21 and a support framework connected with the outer ring surface of the metal matrix composite central cylinder 21 by glue screwing, and each support framework of the three types of functions is distributed at an average circumferential angle around the metal matrix composite central cylinder 21; the circular load-bearing cylinder 3 is externally clamped on the outer support frameworks of the high-stability base; and the skin 7 is provided with a carbon fiber circular ring belt 4 inlaid with discrete equal-arc-length-section metal matrix composite patches 42 on the camera light shield mounting interface directly above the load-bearing cylinder 3, and the skin 7 is connected with the carbon fiber circular ring belt 4, thereby defining that the camera light shield mounting side is the negative direction of the substrate, that is, the optical substrate camera side 101 is in the negative direction, and the other side of the thickness direction of the substrate is the positive direction, that is, the optical substrate single machine side 102 is in the positive direction. The metal matrix composite of the application is preferably SiCAl.

[0062] The metal matrix composite central cylinder 21 is a closed hollow circular ring disc structure with two radius rib shapes welded together, the circular ring disc takes the rib side as the welding surface, the reinforcing ribs designed in the radial direction are consistent with the height of the circular ring disc and are welded to form a concave-convex matching, and ultrasonic composite brazing is used. The metal matrix composite main support framework 23 is a cross-shaped rib-shaped hollow rectangular frame welded together, the cross-shaped rib-shaped hollow rectangular frame is welded to form a whole, the reinforcing ribs designed inside the frame are lower than the height of the framework, the welding butt surfaces on the two sides are welded to form a concave-convex matching, and ultrasonic composite brazing is used. The metal matrix composite main support framework 23 is provided with a single machine installation protruding table at the installation position with high-stability precision requirements. The metal matrix composite auxiliary support framework 24 is a I-shaped rib-shaped hollow rectangular frame structure and is directly machined. The carbon fiber auxiliary support framework 25 is a rectangular tube structure. All the support frameworks are connected with the outer ring surface of the metal matrix composite central cylinder 21 by glueing and screwing, and the connecting flanges for connection are designed at the connection positions of the support frameworks. Preferably, the support frameworks of the three types of functions are distributed at an average circumferential angle, the metal matrix composite central cylinder 21 is uniformly provided with three metal matrix composite main support frameworks 23 and three metal matrix composite auxiliary support frameworks 24 on the circumference, and the metal matrix composite main support frameworks 23 and the metal matrix composite auxiliary support frameworks 24 are arranged at intervals, and the carbon fiber auxiliary support framework 25 is arranged between the adjacent two metal matrix composite main support frameworks 23 and the metal matrix composite auxiliary support frameworks 24.

[0063] The skin 7 comprises an integral carbon fiber skin without splicing, two pieces of skin 7 are respectively glued and covered on the camera face 101 and the single machine face 102 of the optical substrate, the outer edge of the skin 7 matches the outer edge of the carbon fiber frame plate 5, the skin 7 is not covered in the area of the metal matrix composite central cylinder 21, and the skin 7 is perforated at the single machine connection. The skin 7 of a certain thickness covers the envelope area of the substrate, and the single machine protruding table on the metal matrix composite main support skeleton 23 of the central high stability area 2 is perforated to protrude outside the skin 7, the remaining carbon fiber components are perforated at the single machine mounting foot, and the whole substrate forms a closed shell structure.

[0064] As shown in Figure 5 The load-bearing cylinder 3 is a circular carbon fiber cylinder, which is wrapped around the central high stability area 2 and is connected to all the support skeletons by glue screws. The load-bearing cylinder 3 includes a load-bearing inner cylinder skin 31, an aluminum honeycomb core sandwich 32, and a load-bearing outer cylinder skin 33 arranged from inside to outside. The upper and lower ends of the load-bearing inner cylinder skin 31 are both inwardly extended to form a skin turn-up, and the upper and lower ends of the load-bearing outer cylinder skin 33 are both outwardly extended to form a skin turn-up. The skin turn-ups are parallel to and glued with the skin 7. The outer side of the skin 7 of the single machine face 102 of the optical substrate is provided with a second carbon fiber ring belt 34, which is arranged correspondingly to the aluminum honeycomb core sandwich 32. The width of the second carbon fiber ring belt 34 is the maximum value of the circumferences of the load-bearing inner cylinder skin 31 and the load-bearing outer cylinder skin 33.

[0065] As shown in Figure 6 The carbon fiber ring belt 4 is arranged correspondingly to the aluminum honeycomb core sandwich 32. One side of the metal matrix composite patch 42 is formed with a protruding table, and the metal matrix composite patch 42 is embedded in the carbon fiber ring belt 4 through the protruding table and is glued with the carbon fiber ring belt 4. The angle distribution and arc length of the metal matrix composite patch 42 are consistent with the mounting interface of the light shield. The mounting interface of the light shield is designed as a discrete metal matrix composite patch 42 inlaid in the carbon fiber ring belt 4, which is located directly above the load-bearing cylinder 3 on the side of the light shield, i.e. in the negative direction of the substrate, with the skin 7 covered by the substrate in between. One side of the metal matrix composite patch 42 is designed with a protruding table inlaid in the carbon fiber ring belt 4 for gluing, and the angle distribution and arc length specifications are consistent with the mounting interface of the camera light shield. The patch is designed with a through hole.

[0066] As shown in Figures 7-9As shown, the carbon fiber frame plate 5 is a central symmetric structure, and a plurality of auxiliary support rectangular frame pipes 54 are further arranged inside the carbon fiber frame plate 5, the two ends of the auxiliary support rectangular frame pipes 54 are respectively connected with the load-bearing cylinder 3 and the closed frame pipe 53, the rectangular frame pipe 52, the closed frame pipe 53 and the auxiliary support rectangular frame pipe 54 are integrally formed, a plurality of joints 51 are connected to the circumferential side of the load-bearing cylinder 3, and the load-bearing cylinder 3 is tightly connected with the carbon fiber frame plate 5 through the plurality of joints 51. The carbon fiber frame plate 5 is arranged outside the circular load-bearing cylinder 3, the pipe section is rectangular, and the layout is extended along the force transmission path of the metal matrix composite main support skeleton 23, the metal matrix composite auxiliary support skeleton 24 and the carbon fiber auxiliary support skeleton 25 in the load-bearing cylinder 3, the auxiliary support rectangular frame pipes 54 are added at the intersection of the rectangular pipe and the load-bearing cylinder 3 to support the long side direction and the outer two sides of the load-bearing cylinder 3 for stiffness improvement, and the closed frame pipe 53 enveloped at the outermost side uses a carbon fiber rectangular pipe frame full-closed plane structure. The end of the rectangular support pipe intersecting with the outside of the load-bearing cylinder 3 of the carbon fiber frame plate 5 uses a plurality of joint 51 splicing, and the flange of the joint 51 is connected with the load-bearing cylinder 3 by glue screwing. The carbon fiber frame plate 5 keeps continuous with the central high-stability area 2, and the truss layout needs to form axial symmetry, i.e. up-down and left-right axial symmetry, and the pre-embedded parts are designed in the truss of the carbon fiber frame plate 5 corresponding to the single machine installation position.

[0067] As shown in Figure 10 and 11 As shown, the carbon fiber auxiliary support skeleton 25, the rectangular frame pipe 52 and the auxiliary support rectangular frame pipe 54 are all arranged with type heat pipes 1001 in the pipe cavities The upper and lower fins of the type heat pipes 1001 are glued to the inner wall of the pipe cavity. The outer wall of the load-bearing cylinder 3 is provided with a plurality of space S type heat pipes 1002 along the circumference, the space S type heat pipes 1002 are arranged in a ring shape and staggered from bottom to top, and the upper and lower fins of the space S type heat pipes 1002 are respectively glued to the skin flanges at the upper and lower ends of the load-bearing outer cylinder skin 33. Preferably, the space S type heat pipes 1002 are evenly divided into four quadrants by the outer ring of the load-bearing cylinder 3, and are glued to the load-bearing outer cylinder skin 33 in a ring shape and staggered from bottom to top.

[0068] As shown in Figure 12As shown, the circumscribed circle diameter of the honeycomb core cell 61 of the hexagonal flange carbon honeycomb 6 is 1 / 3 of the height, and the upper and lower of the honeycomb core cell 61 are provided with inwardly extending short distance flanges, the flange width is 5% of the height, the flange thickness is consistent with the honeycomb wall, and the flange layer direction can be the fiber direction. The honeycomb wall layer direction of the hexagonal flange carbon honeycomb 6 is quasi-isotropic of the thickness of the honeycomb core cell 61. The arrangement mode of the hexagonal flange carbon honeycomb 6 is to diverge in the normal direction of each edge surface of the honeycomb core cell 61, and to arrange one by one back to back, and the same direction ensures the mechanical isotropy of each direction. The hexagonal flange carbon honeycomb 6 is filled in the carbon fiber frame plate 5, the support framework space area in the substrate. The honeycomb cores are glued, and the honeycomb cores, the framework, the frame and the panel are glued to form an integral structure.

[0069] The closed shell structure substrate includes covering and bonding the skin 7 which is multiplied by the thickness of the honeycomb core wall to the substrate envelope area including the carbon fiber frame plate 5, the support framework and the flange honeycomb core, and only the metal matrix composite central cylinder 21 area is not covered. The skin 7 adopts an integrated non-splicing to ensure the continuity of the carbon fiber. Preferably, the thickness of the skin 7 is six times the thickness of the wall of the hexagonal flange carbon honeycomb 6, and the quasi-isotropic layer is selected from high modulus M55J / cyanate ester carbon fiber composite material. The honeycomb core, the framework, the frame and the panel are glued to form an integral structure.

[0070] As shown in Figure 13 The optical substrate single machine face 102 is provided with a plurality of carbon fiber embedded parts 8 at the single machine mounting interface, the carbon fiber embedded part 8 is an equilateral triangle configuration, each vertex of the triangle is a flat section, and a through slot opening connected with the hexagonal flange carbon honeycomb 6 is formed longitudinally and bonded with the inner wall or node of the honeycomb core cell 61, that is, the edges of the triangular embedded part diverge at the intersection of the hexagonal flange carbon honeycomb 6. The embedded part hole corresponds to the single machine mounting hole position, and the adhesion reliability of the embedded part and the honeycomb is ensured to maintain the continuity of mechanical diffusion.

[0071] The optical substrate single machine face 102 is provided with a plurality of circular discrete metal matrix composite patches 9, which are only discretely arranged for the mounting foot position, and are bonded with the skin 7 using structural adhesive. After bonding, the overall flatness of the discrete metal matrix composite patch 9 meets the single machine mounting flatness standard, and a through hole is formed at the single machine mounting joint on the discrete metal matrix composite patch 9.

[0072] As shown in Figure 14 and 15As shown, the plurality of tooling lifting points 11 are symmetrically and equidistantly arranged on the circumferential side of the closed frame tube 53, i.e., the long edges and the short edges are symmetrically arranged and equidistantly spaced. The tooling lifting point embedded part 111 of the tooling lifting point 11 is fastened and connected in the inner cavity of the closed frame tube 53, and the tooling lifting point patch 112 of the tooling lifting point 11 is glued on the outer side of the closed frame tube 53. The tooling lifting point embedded part 111 is a lightweight structure, and the embedded part at the lifting point is a cylindrical whole body matched with the whole I-shaped closed rectangular shell to form a continuous whole body, is positioned and glued in the closed frame tube 53, and is glued on the outer side of the closed frame tube 53 corresponding to the tooling lifting point patch 112.

[0073] The optical substrate 1 of the present application adopts a structure of carbon fiber and metal matrix composite, solves the size problem of using traditional single metal matrix composite material preparation and processing for large-scale substrates, and has a great design advantage in weight reduction by coupling carbon fiber.

[0074] The present application constructs a central high-stability area 2 mainly composed of metal matrix composite for the high-precision load carrying platform, reduces the material cost under the condition of meeting the high-precision operation of single machine, and the remaining part cooperates with the stable frame design of carbon fiber material structure.

[0075] The present application uses carbon fiber honeycomb structure to fill the substrate, solves the anisotropy problem of the original traditional honeycomb core strip distribution from the way of back-to-back arrangement of single cells, and improves the in-plane mechanical anisotropy performance of the substrate.

[0076] In the description of the present application, it should be understood that the orientations or positional relationships indicated by the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like are based on the orientations or positional relationships shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as limiting the present application.

[0077] The specific embodiments of the present application are described above. It should be understood that the present application is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which does not affect the essential content of the present application. In the case of no conflict, the embodiments of the present application and the features in the embodiments can be arbitrarily combined with each other.

Claims

1. A closed composite structure substrate applied to a space camera, characterized by, The optical substrate (1) comprises a central high-stability area (2), a force-bearing cylinder (3) and a carbon fiber frame plate (5) arranged in sequence from inside to outside, and the envelope area of the optical substrate (1) is covered with a skin (7) to form a closed shell structure substrate; The two sides of the optical substrate (1) are respectively an optical substrate camera face (101) and an optical substrate single-machine face (102), and a carbon fiber ring belt (4) is arranged at the light-shield cover mounting interface of the optical substrate camera face (101), and discrete metal matrix composite patches (42) are inlaid on the carbon fiber ring belt (4); The central high-stability area (2) comprises a metal matrix composite central cylinder (21), and the outer ring surface of the metal matrix composite central cylinder (21) is uniformly provided with a plurality of metal matrix composite main support skeletons (23), a plurality of metal matrix composite auxiliary support skeletons (24) and a plurality of carbon fiber auxiliary support skeletons (25) in the circumferential direction; The metal matrix composite main support skeleton (23) is a cross-shaped rib-shaped hollow rectangular frame with upper and lower butt joints, a single-machine mounting protruding table is arranged on the metal matrix composite main support skeleton (23), the metal matrix composite auxiliary support skeleton (24) is a I-shaped rib-shaped hollow rectangular frame structure, three metal matrix composite main support skeletons (23) and three metal matrix composite auxiliary support skeletons (24) are uniformly arranged on the circumferential side of the metal matrix composite central cylinder (21), and the metal matrix composite main support skeleton (23) and the metal matrix composite auxiliary support skeleton (24) are arranged at intervals, and the carbon fiber auxiliary support skeleton (25) is arranged between adjacent two metal matrix composite main support skeletons (23) and metal matrix composite auxiliary support skeletons (24); The carbon fiber frame plate (5) comprises a plurality of rectangular frame tubes (52) on the inner side and a closed frame tube (53) on the outer side, and the rectangular frame tubes (52) are arranged in the force transmission path extension direction of the support skeletons of the central high-stability area (2) respectively; The central high-stability area (2) and the carbon fiber frame plate (5) are both filled with isotropic hexagonal flange carbon honeycombs (6) inside.

2. The enclosed composite structural substrate for a space camera of claim 1, wherein, The skin (7) comprises an integral carbon fiber skin without splicing, two pieces of the skin (7) are respectively glued and covered on the optical substrate camera face (101) and the optical substrate single-machine face (102), the outer edge of the skin (7) matches the outer edge of the carbon fiber frame plate (5), the skin (7) is not covered in the area of the metal matrix composite central cylinder (21), and the skin (7) is holed at the single-machine connection.

3. The closed composite structure substrate for space cameras according to claim 1, wherein The force bearing cylinder (3) is a circular carbon fiber cylinder, which comprises a force bearing inner cylinder skin (31), an aluminum honeycomb core sandwich (32) and a force bearing outer cylinder skin (33) arranged in sequence from inside to outside, both upper and lower ends of the force bearing inner cylinder skin (31) extend inward to form skin flanges, both upper and lower ends of the force bearing outer cylinder skin (33) extend outward to form skin flanges, the skin flanges are parallel to and glued to the skin (7), the outer side of the skin (7) of the optical substrate single machine surface (102) is provided with a second carbon fiber circular ring belt (34), and the second carbon fiber circular ring belt (34) is arranged correspondingly to the aluminum honeycomb core sandwich (32).

4. The closed composite structure substrate for space cameras according to claim 3, wherein The carbon fiber ring belt (4) is arranged correspondingly to the aluminum honeycomb core sandwich (32), one side of the metal matrix composite patch (42) is formed with a protruding platform, the metal matrix composite patch (42) is embedded in the carbon fiber ring belt (4) through the protruding platform and is glued to the carbon fiber ring belt (4), and the metal matrix composite patch (42) is consistent with the angle distribution and arc length of the light shield cover mounting interface.

5. The closed composite structural substrate for space cameras of claim 3, wherein, The metal matrix composite center cylinder (21) is a two-radius closed hollow annular disc structure of butt welding, and the carbon fiber auxiliary support framework (25) is a rectangular tube structure.

6. The closed composite structure substrate for space cameras according to claim 5, wherein The carbon fiber frame plate (5) is a central symmetric structure, a plurality of auxiliary support rectangular frame tubes (54) are further arranged in the carbon fiber frame plate (5), both ends of the auxiliary support rectangular frame tube (54) are connected with the force bearing cylinder (3) and the closed frame tube (53) respectively, the rectangular frame tube (52), the closed frame tube (53) and the auxiliary support rectangular frame tube (54) are integrally formed, a plurality of joints (51) are connected to the circumferential side of the force bearing cylinder (3), and the force bearing cylinder (3) is fastened and connected with the carbon fiber frame plate (5) through the joints (51).

7. The closed composite structure substrate for space cameras according to claim 6, wherein The carbon fiber auxiliary support framework (25), the rectangular frame tube (52) and the auxiliary support rectangular frame tube (54) are all provided with The heat pipe (1001) is provided with The upper and lower fins of the heat pipe (1001) are glued to the inner wall of the tube cavity. The outer side wall of the force bearing cylinder (3) is provided with a plurality of space S-shaped heat pipes (1002) in the circumferential direction, a plurality of space S-shaped heat pipes (1002) are arranged in a ring shape in a staggered manner from bottom to top, and the upper and lower fins of the space S-shaped heat pipe (1002) are glued to the skin flanges at the upper and lower ends of the force bearing outer cylinder skin (33) respectively.

8. The enclosed composite structural substrate for space cameras of claim 1, wherein, The diameter of the circumscribed circle of the honeycomb core cell (61) of the hexagonal flange carbon honeycomb (6) is 1 / 3 of the height, inwardly extending flanges are arranged on the upper and lower sides of the honeycomb core cell (61), the flange width is 5% of the height, the flange thickness is consistent with the honeycomb wall, the honeycomb wall layer direction of the hexagonal flange carbon honeycomb (6) is the quasi-isotropic of the thickness of the honeycomb core cell (61), and the arrangement mode of the hexagonal flange carbon honeycomb (6) is to diverge in the normal direction of each edge surface of the honeycomb core cell (61) and arrange one by one back to back.

9. The closed composite structural substrate for space cameras of claim 8, wherein, The optical substrate single machine surface (102) is provided with a plurality of carbon fiber embedded parts (8) at the single machine mounting interface, the carbon fiber embedded parts (8) are equilateral triangle configurations, each vertex of the triangle is a flat section, a through slot is formed longitudinally and connected with the hexagonal flange carbon honeycomb (6), the carbon fiber embedded parts (8) are bonded with the inner wall or node of the honeycomb core cell (61); The optical substrate single machine surface (102) is provided with a plurality of circular discrete metal matrix composite patches (9), a through hole is formed at the single machine mounting interface of the discrete metal matrix composite patch (9).

10. The enclosed composite structural substrate for a space camera of claim 1, wherein, A plurality of tool lifting points (11) are symmetrically and equidistantly arranged on the circumferential side of the closed frame tube (53), a tool lifting point embedded part (111) of the tool lifting point (11) is fastened and connected in the inner cavity of the closed frame tube (53), and a tool lifting point patch (112) of the tool lifting point (11) is glued on the outer side of the closed frame tube (53).

Images