Closed composite structure substrate applied to space camera

Abstract

The invention provides a closed composite structure substrate applied to a space camera, an optical substrate comprises a central high-stability area, a bearing cylinder and a carbon fiber frame plate which are sequentially arranged from inside to outside, and the enveloping area of the optical substrate is covered with a skin to form a closed shell structure substrate; the center high-stability area comprises a metal matrix composite center cylinder, and a metal matrix composite main supporting framework, an auxiliary supporting framework and a carbon fiber auxiliary supporting framework are arranged on the outer ring face of the center cylinder. And the central high-stability area and the carbon fiber frame plate are filled with hexagonal flanged carbon honeycombs which are arranged in an isotropic manner. The central high-stability area made of the metal matrix composite is matched with the framework plate of the carbon fiber material structure and the honeycomb layout design, so that high rigidity and high stability of the base plate are guaranteed, meanwhile, the weight reduction advantage is remarkable, and the material cost is reduced; and the size and the precision stability of the whole substrate are optimized through the embedded layout of the special-shaped heat pipe, the supporting structure and the force bearing cylinder.

Description

Technical Field

[0001] The present invention relates to the field of optical remote sensing technology, and in particular to a closed composite structure substrate applied to a space camera. Background Art

[0002] The optical substrate of a space camera is an important platform for the optical remote sensing system to carry a single machine payload. Its weight, rigidity bearing capacity, dimensional stability, precision stability and other structural performance indicators will directly determine the accuracy and performance of the optical system. As the development of optical remote sensing systems tends to telephoto, wide format and high resolution, the development of substrate structures also tends to be large in size, lightweight, high in rigidity and high in stability.

[0003] Compared with the structure of previous optical substrates, the size is conventional and metal materials are often used with hollowing to reduce weight; or traditional honeycomb panel structures are used. However, when faced with the need to carry large camera payloads and high operating precision, the substrate is upgraded to a large scale. From the perspective of material selection and preparation, weight and structural design, and the control of size and precision stability, the original structural design technology no longer meets the requirements. The corresponding patent comparison is as follows:

[0004] For example, patent document CN 113970867 B discloses a tower camera structure used in a coaxial four-mirror optical system, in which the optical substrate structure is hexagonal, lightweighted by polygonal hollowing, and the material is beryllium aluminum alloy. This kind of substrate using metal material with topological lightweight design cannot meet the size requirements in the design of large-scale substrates, and there is a weight tolerance problem.

[0005] Patent document CN 105466470 A discloses a large-scale space optical remote sensor composite light-blocking board, which uses carbon fiber material to make the light-blocking board substrate lightweight. However, the structure is a non-load-bearing structure and cannot carry loads through mechanical tests.

[0006] Therefore, it is necessary to provide a closed composite structure substrate for use in space cameras that meets the requirements of large size, light weight, high rigidity and high stability. Summary of the invention

[0007] In view of the defects in the prior art, an object of the present invention is to provide a closed composite structure substrate for use in a space camera.

[0008] According to a closed composite structure substrate for a space camera provided by the present invention, the optical substrate comprises a central high stability area, a load-bearing cylinder and a carbon fiber frame plate arranged in sequence from the inside to the outside, and the envelope area of ​​the optical substrate is covered with a skin to form a closed shell structure substrate;

[0009] The two sides of the optical substrate are respectively: an optical substrate camera surface and an optical substrate stand-alone surface, a carbon fiber ring belt is provided at the light shield mounting interface of the optical substrate camera surface, and a discrete metal matrix composite material patch is inlaid on the carbon fiber ring belt;

[0010] The central high stability area comprises a metal matrix composite central tube, and the outer annular surface of the metal matrix composite central tube is uniformly provided with 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 along the circumferential direction;

[0011] The carbon fiber frame plate includes 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 respectively arranged in the extension direction of the force transmission path of the support frame of the central high stability area;

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

[0013] Preferably, the skin comprises an integrated carbon fiber skin without splicing, and the two pieces of the skin are respectively glued and covered on the camera surface of the optical substrate and the single machine surface of the optical substrate, and the outer edge of the skin matches the outer edge of the carbon fiber frame plate. The skin only does not cover the central tube area of ​​the metal matrix composite material, and a hole is opened on the skin at the connection with the single machine.

[0014] Preferably, the load-bearing cylinder is a circular carbon fiber cylinder, and the load-bearing cylinder includes a load-bearing inner cylinder skin, an aluminum honeycomb core interlayer and a load-bearing outer cylinder skin which are arranged in sequence from the inside to the outside, and the upper and lower ends of the load-bearing inner cylinder skin are extended inward to form skin flanges, and the upper and lower ends of the load-bearing outer cylinder skin are extended outward to form skin flanges, and the skin flanges are parallel to the skin and glued together, and a second carbon fiber circular ring belt is arranged on the outer side of the skin of the single-machine surface of the optical substrate, and the second carbon fiber circular ring belt is arranged corresponding to the aluminum honeycomb core interlayer.

[0015] Preferably, the carbon fiber ring band is arranged corresponding to the aluminum honeycomb core interlayer, a protrusion is formed on one side of the metal-based composite material patch, the metal-based composite material patch is embedded in the carbon fiber ring band through the protrusion and is glued to the carbon fiber ring band, and the angle distribution and arc length of the metal-based composite material patch and the sunshade mounting interface are consistent.

[0016] Preferably, the metal matrix composite central tube is two radial rib-shaped closed hollow circular disk structures welded up and down, the metal matrix composite main support frame is two cross-shaped rib-shaped hollow rectangular frames welded up and down, a single-machine mounting boss is provided on the metal matrix composite main support frame, the metal matrix composite auxiliary support frame is an I-shaped rib-shaped hollow rectangular frame structure, and the carbon fiber auxiliary support frame is a rectangular tube structure;

[0017] Three main supporting frames of the metal matrix composite materials and three auxiliary supporting frames of the metal matrix composite materials are evenly arranged on the circumferential side of the central tube of the metal matrix composite material, and the main supporting frames of the metal matrix composite materials and the auxiliary supporting frames of the metal matrix composite materials are arranged at intervals, and the carbon fiber auxiliary supporting frame is arranged between two adjacent main supporting frames of the metal matrix composite materials and the auxiliary supporting frames of the metal matrix composite materials.

[0018] Preferably, the carbon fiber frame plate is a centrally symmetrical structure, and a plurality of auxiliary supporting rectangular frame tubes are further arranged inside the carbon fiber frame plate. The two ends of the auxiliary supporting rectangular frame tubes are respectively connected to the load-bearing cylinder and the closed frame tube. The rectangular frame tube, the closed frame tube and the auxiliary supporting rectangular frame tube are integrally formed. A plurality of joints are connected to the circumferential side of the load-bearing cylinder, and the load-bearing cylinder is fastened to the carbon fiber frame plate through the joints.

[0019] Preferably, the carbon fiber auxiliary support skeleton, the rectangular frame tube and the auxiliary support rectangular frame tube are all provided with Type heat pipe, the The upper and lower fins of the heat pipe are glued to the inner wall of the tube cavity;

[0020] The outer wall of the load-bearing tube is circumferentially provided with a plurality of spatial S-shaped heat pipes, which are staggeredly arranged in a ring from bottom to top, and the upper and lower fins of the spatial S-shaped heat pipes are respectively glued to the skin flanges at the upper and lower ends of the load-bearing outer tube skin.

[0021] Preferably, the diameter of the circumscribed circle of the honeycomb core cell of the hexagonal flanged carbon honeycomb is 1 / 3 of the height, and the upper and lower parts of the honeycomb core cell are provided with flanges extending inwards, the flange width is 5% of the height, and the flange thickness is consistent with the honeycomb wall. The honeycomb wall plying direction of the hexagonal flanged carbon honeycomb is quasi-invariant of the thickness of the honeycomb core cell, and the arrangement of the hexagonal flanged carbon honeycomb is divergent in the normal direction of each side face of the honeycomb core cell, and arranged back to back one by one.

[0022] Preferably, a plurality of carbon fiber embedded parts are provided at the single-machine installation interface of the single-machine surface of the optical substrate, the carbon fiber embedded parts are triangular equilateral configurations, each vertex of the triangle is a straight section, and a through slot opening connected to the hexagonal flanging carbon honeycomb is formed in the longitudinal direction, and the carbon fiber embedded parts are bonded to the inner wall or node of the honeycomb core cell;

[0023] A plurality of circular discrete metal-based composite material patches are arranged on a single surface of the optical substrate, and through holes are provided at the single installation joints on the discrete metal-based composite material patches.

[0024] Preferably, a plurality of tooling hanging points are symmetrically and evenly spaced around the closed frame tube, the tooling hanging point embedded parts are fastened in the inner cavity of the closed frame tube, and the tooling hanging point patches are glued to the outer surface of the closed frame tube.

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

[0026] The present invention uses a central high-stability area composed of a metal-based composite material to meet the condition of high-precision operation of a single machine, and the remaining parts are matched with a load-bearing cylinder, a frame plate of a carbon fiber material and a honeycomb layout design to ensure high rigidity and high stability of the structure while having great advantages in weight reduction, reducing material costs, and solving the difficult problems of material preparation and processing scale for large-scale substrates using traditional single SiCAl; the substrate is filled with a hexagonal flanged carbon honeycomb structure, and the problem of in-plane mechanical anisotropy caused by the anisotropic distribution of the original traditional honeycomb core strips is improved from the perspective of a back-to-back arrangement of single cells; the inlaid layout of the special-shaped heat pipe, the support structure and the load-bearing cylinder optimizes the size and precision stability of the overall substrate. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Other features, objects and advantages of the present invention will become more apparent from the detailed description of non-limiting embodiments made with reference to the following drawings:

[0028] Figure 1 This is a schematic diagram of the structure of the camera surface of the optical substrate mainly embodied in the present invention;

[0029] Figure 2 This is a schematic diagram of the structure of a single optical substrate surface of the present invention;

[0030] Figure 3 It is a cross-sectional view of an optical substrate mainly embodied in the present invention;

[0031] Figure 4 This is a schematic diagram of the structure of a carbon fiber frame plate mainly embodied in the present invention;

[0032] Figure 5 This is a schematic diagram of the structure of the load-bearing cylinder mainly embodied in the present invention;

[0033] Figure 6 This is a schematic diagram of the structure of a metal matrix composite material patch mainly embodied in the present invention;

[0034] Figure 7 This is a structural schematic diagram of a joint mainly embodied in the present invention;

[0035] Figure 8 This is a structural schematic diagram of a joint mainly embodied in the present invention;

[0036] Fig. 9 This is a structural schematic diagram of a joint mainly embodied in the present invention;

[0037] Fig.10 The present invention mainly embodies Schematic diagram of the structure of the heat pipe;

[0038] Fig.11 This is a schematic diagram of the structure of a spatial S-shaped heat pipe mainly embodied in the present invention;

[0039] Fig.12 This is a schematic diagram of the structure of the honeycomb core cell mainly embodied in the present invention;

[0040] Fig.13 This is a schematic diagram of the structure of the carbon fiber embedded part mainly embodied in the present invention;

[0041] Fig.14 This is a schematic diagram of the structure of the embedded parts of the tooling lifting points mainly embodied in the present invention;

[0042] Fig.15 The present invention mainly embodies the structural schematic diagram of the tooling hanging point patch.

[0043] As shown in the figure:

[0044] Optical substrate 1 Optical substrate camera surface 101

[0045] Optical substrate single machine surface 102 Central high stability area 2

[0046] Metal matrix composite central tube 21 Metal matrix composite main support frame 23

[0047] Metal matrix composite material auxiliary support frame 24 Carbon fiber auxiliary support frame 25

[0048] Load-bearing tube 3 Load-bearing inner tube skin 31

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

[0050] Second carbon fiber annular belt 34 Carbon fiber annular 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 Flanged Carbon Honeycomb 6 Honeycomb Core Cell 61

[0055] Skin 7 Carbon fiber embedded parts 8

[0056] Discrete metal matrix composite patch 9 Heat pipe 1001

[0057] Spatial S-type heat pipe 1002 Tooling hanging point 11

[0058] Tooling lifting point embedded parts 111 Tooling lifting point patch 112 DETAILED DESCRIPTION

[0059] The present invention is described in detail below in conjunction with specific embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those of ordinary skill in the art, several changes and improvements can also be made without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0060] like Figure 1-4 As shown, according to a closed composite structure substrate for a space camera provided by the present invention, the optical substrate 1 includes a central high stability area 2, a bearing cylinder 3 and a carbon fiber frame plate 5 arranged in sequence from the inside to the 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 surface 101 and an optical substrate single machine surface 102, and a carbon fiber ring belt 4 is arranged at the light shield installation interface of the optical substrate camera surface 101, and a discrete metal matrix composite material patch 42 is inlaid on the carbon fiber ring belt 4; the central high stability area 2 includes a metal The metal matrix composite center tube 21, the outer ring surface of the metal matrix composite center tube 21 is evenly arranged with multiple metal matrix composite main support skeletons 23, multiple metal matrix composite auxiliary support skeletons 24 and multiple carbon fiber auxiliary support skeletons 25 along the circumferential direction; the carbon fiber frame plate 5 includes multiple rectangular frame tubes 52 on the inside and closed frame tubes 53 on the outside, and the multiple rectangular frame tubes 52 are respectively arranged in the extension direction of the force transmission path of the support skeleton of the central high stability area 2; both the central high stability area 2 and the carbon fiber frame plate 5 are filled with isotropically arranged hexagonal flanged carbon honeycombs 6.

[0061] The present application is applied to a large-scale, light-weight and high-rigidity space camera mounting substrate. The central high-stability area 2 includes a metal-based composite central tube 21 and a supporting frame connected to its outer ring surface by rubber screws. The supporting frames of the three types of functions are distributed around the metal-based composite central tube 21 at an average circumferential angle; the circular load-bearing tube 3 is hooped outside the multiple supporting frames of the high-stability base; and the spacer skin 7 is provided with a carbon fiber annular belt 4 inlaid with discrete equal-arc length metal-based composite patches 42 for the camera hood mounting interface directly above the load-bearing tube 3 and connected to the skin 7, thereby defining the camera hood mounting side as the negative direction of the substrate, that is, the optical substrate camera surface 101 side is in the negative direction, and the other side of the substrate thickness direction is the positive direction, that is, the optical substrate single machine surface 102 side is in the positive direction. The metal-based composite material of the present application is preferably SiCAl.

[0062] The metal matrix composite center tube 21 is a structure of two radial rib-shaped closed hollow circular disks welded up and down. The circular disk uses the rib side as the welding surface. The reinforcing ribs designed in the radial direction are consistent with the height of the circular disk and the welding surface is matched with concave and convex, and ultrasonic composite brazing is used. The metal matrix composite main support skeleton 23 is two cross-shaped rib-shaped hollow rectangular frames welded up and down. The cross-shaped rib-shaped hollow rectangular frames are welded to form a whole. The reinforcing ribs designed inside the frame are lower than the frame height. The welding butt surfaces on both sides are matched with concave and convex, and ultrasonic composite brazing is used. The installation position of the metal matrix composite main support skeleton 23 with high stability and precision requirements for single-machine installation is provided with a single-machine installation boss. The metal matrix composite auxiliary support skeleton 24 is an I-shaped rib-shaped hollow rectangular frame structure, which directly adopts a machining process. The carbon fiber auxiliary support skeleton 25 is a rectangular tube structure. All support skeletons are connected to the outer ring surface of the metal matrix composite center tube 21 by adhesive bonding and screwing, and the connection of the support skeleton is designed with a process flange for connection. Preferably, the three types of functional support skeletons are distributed at an average circumferential angle, and three metal matrix composite material main support skeletons 23 and three metal matrix composite material auxiliary support skeletons 24 are evenly arranged on the circumferential side of the metal matrix composite material center tube 21, and the metal matrix composite material main support skeletons 23 and the metal matrix composite material auxiliary support skeletons 24 are arranged at intervals, and a carbon fiber auxiliary support skeleton 25 is arranged between two adjacent metal matrix composite material main support skeletons 23 and metal matrix composite material auxiliary support skeletons 24.

[0063] The skin 7 includes an integrated non-spliced ​​carbon fiber skin. Two pieces of skin 7 are glued and covered on the optical substrate camera surface 101 and the optical substrate single machine surface 102 respectively. The outer edge of the skin 7 matches the outer edge of the carbon fiber frame plate 5. The skin 7 does not cover only the area of ​​the metal matrix composite central tube 21. The skin 7 is connected to the single machine with a hole. The skin 7 with a certain thickness is fully covered and glued up and down on the substrate envelope area. The single machine protrusion mounting surface on the main support frame 23 of the metal matrix composite material in the central high stability area 2 is opened to make the protrusion protrude from the skin 7. The single machine mounting feet on the other carbon fiber components are opened, and the entire substrate forms a closed shell structure.

[0064] like Figure 5 As shown, the load-bearing tube 3 is a circular carbon fiber tube, which is hooped in the central high stability area 2 and connected with all its supporting frames by glue screws. The embedded parts for connecting and positioning the supporting frames are arranged in the wall thickness of the load-bearing tube 3. The load-bearing tube 3 includes a load-bearing inner tube skin 31, an aluminum honeycomb core sandwich 32 and a load-bearing outer tube skin 33 arranged in sequence from the inside to the outside. The upper and lower ends of the load-bearing inner tube skin 31 extend inward to form a skin flange, and the upper and lower ends of the load-bearing outer tube skin 33 extend outward to form a skin flange. The skin flange is parallel to the skin 7 and is glued. The outer side of the skin 7 of the optical substrate single machine surface 102 is provided with a second carbon fiber annular belt 34, and the second carbon fiber annular belt 34 is arranged corresponding to the aluminum honeycomb core sandwich 32. The width of the second carbon fiber annular belt 34 is taken as the maximum value of the circumference of the load-bearing inner tube skin 31 and the load-bearing outer tube skin 33.

[0065] like Figure 6 As shown, the carbon fiber band 4 is arranged corresponding to the aluminum honeycomb core sandwich 32, and a protrusion is formed on one side of the metal matrix composite patch 42. The metal matrix composite patch 42 is embedded in the carbon fiber band 4 through the protrusion and is glued to the carbon fiber band 4. The angle distribution and arc length of the metal matrix composite patch 42 are consistent with those of the light shield installation interface. The substrate light shield installation interface is designed as a discrete metal matrix composite patch 42 embedded in the carbon fiber band 4, located just above the light shield installation side of the bearing cylinder 3, that is, in the negative direction of the substrate, wherein the skin 7 covered by the interval substrate, the metal matrix composite patch 42 is designed with a protrusion on one side and is reversely embedded in the carbon fiber band 4 and glued, and its angle distribution is consistent with the camera light shield installation interface, and the arc length specifications are equally divided and consistent, and a through hole is designed on the patch.

[0066] like Figure 7-9As shown, the carbon fiber frame plate 5 is a centrally symmetrical structure, and a plurality of auxiliary supporting rectangular frame tubes 54 are also arranged inside the carbon fiber frame plate 5. The two ends of the auxiliary supporting rectangular frame tubes 54 are connected to the bearing cylinder 3 and the closed frame tube 53 respectively. The rectangular frame tube 52, the closed frame tube 53 and the auxiliary supporting rectangular frame tube 54 are integrally formed, and the peripheral side of the bearing cylinder 3 is connected with a plurality of joints 51, and the bearing cylinder 3 is fastened to the carbon fiber frame plate 5 through a plurality of joints 51. The carbon fiber frame plate 5 is placed outside the circular bearing cylinder 3, and the cross section of the tube is rectangular. The layout is an extension of the force transmission path of the main support skeleton 23 of the metal matrix composite material, the auxiliary support skeleton 24 of the metal matrix composite material, and the auxiliary support skeleton 25 of the carbon fiber. At the intersection of the rectangular tube and the bearing cylinder 3, a transverse and oblique auxiliary supporting rectangular frame tube 54 is added to the auxiliary support in the long side direction and on both sides outside the bearing cylinder 3 to improve the rigidity. The outermost enveloping closed frame tube 53 uses a carbon fiber rectangular tube frame fully enclosed plane structure. The ends of the rectangular support tubes intersecting the carbon fiber frame plate 5 and the outer sides of the bearing tube 3 are connected by various joints 51, and the flanges of the joints 51 are connected to the bearing tube 3 by rubber screws. The carbon fiber frame plate 5 is continuous with the central high stability area 2, and the rod system layout needs to form axisymmetry, that is, vertical and horizontal axisymmetry. Embedded parts are designed in the rod system of the carbon fiber frame plate 5 corresponding to the installation position of the single machine.

[0067] like Fig.10 and 11 As shown, the carbon fiber auxiliary support skeleton 25, the rectangular frame tube 52 and the auxiliary support rectangular frame tube 54 are all centrally provided with Type heat pipe 1001, The upper and lower fins of the heat pipe 1001 are glued to the inner wall of the tube cavity. A plurality of spatial S-shaped heat pipes 1002 are arranged along the circumferential direction on the outer wall of the bearing tube 3. The plurality of spatial S-shaped heat pipes 1002 are arranged in a staggered manner in a ring from bottom to top. The upper and lower fins of the spatial S-shaped heat pipe 1002 are respectively glued to the skin flanges at the upper and lower ends of the bearing outer tube skin 33. Preferably, the outer ring of the bearing tube 3 is evenly divided into 4 quadrants and is arranged in a staggered manner in a ring from bottom to top and glued to the bearing outer tube skin 33.

[0068] like Fig.12As shown, the diameter of the circumscribed circle of the honeycomb core cell 61 of the hexagonal flanged carbon honeycomb 6 is 1 / 3 of the height, and the upper and lower parts of the honeycomb core cell 61 are provided with short flanges extending inward, the flange width is 5% of the height, the flange thickness is consistent with the honeycomb wall, the flange laying direction can be the fiber direction, and the honeycomb wall laying direction of the hexagonal flanged carbon honeycomb 6 is quasi-isotropic of the thickness of the honeycomb core cell 61. The arrangement of the hexagonal flanged carbon honeycomb 6 is to diverge in the normal direction of each side face of the honeycomb core cell 61, and to be arranged back to back one by one, with the same direction in each direction to ensure isotropic mechanical isotropy. The hexagonal flanged carbon honeycomb 6 is filled in the carbon fiber frame plate 5 and the supporting skeleton space area in the substrate. The honeycomb cores are glued together, and the honeycomb cores are glued to the skeleton, frame and panel to form an integral structure.

[0069] The closed shell structure substrate includes a skin 7 that is twice as thick as the honeycomb core wall, which covers and bonds the substrate envelope area including the carbon fiber frame plate 5, the support skeleton, and the flanging honeycomb core. Only the metal matrix composite central tube 21 area is not covered, and the single machine installation hole is opened. 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 wall thickness of the hexagonal flanging carbon honeycomb 6, and a high modulus M55J / cyanate carbon fiber composite material is selected, and the quasi-isotropic layer is laid. The honeycomb core, skeleton, frame and panel are bonded to form an integral structure.

[0070] like Fig.13 As shown, a plurality of carbon fiber embedded parts 8 are arranged at the single-machine installation interface of the single-machine surface 102 of the optical substrate. The carbon fiber embedded parts 8 are triangular equilateral configurations, and the vertices of the triangles are straight sections. Through slots connected to the hexagonal flanging carbon honeycombs 6 are formed in the longitudinal direction, and are bonded to the inner wall or node of the honeycomb core cell 61, that is, the edges of the triangular embedded parts and the hexagonal flanging carbon honeycombs 6 are plugged in at the intersection. The embedded part holes correspond to the position of the single-machine installation holes, and at the same time, the bonding reliability between the embedded parts and the honeycombs is ensured to maintain the continuation of mechanical diffusion.

[0071] The single-machine surface 102 of the optical substrate is provided with a plurality of circular discrete metal-matrix composite material patches 9, which are discretely arranged only for the mounting foot positions and bonded to the skin 7 using structural adhesive. After bonding, the overall flatness of the discrete metal-matrix composite material patches 9 meets the single-machine installation flatness standard, and through holes are provided at the single-machine installation joints on the discrete metal-matrix composite material patches 9.

[0072] like Fig.14 and 15As shown, a plurality of tooling hanging points 11 are symmetrically and evenly spaced around the closed frame tube 53, that is, the long sides and short sides are symmetrically arranged and equally spaced. The tooling hanging point embedded parts 111 of the tooling hanging point 11 are fastened to the inner cavity of the closed frame tube 53, and the tooling hanging point patches 112 of the tooling hanging point 11 are glued to the outer surface of the closed frame tube 53. The tooling hanging point embedded parts 111 are lightweight structures, and the hanging points are embedded cylindrical parts that cooperate with the overall I-shaped closed rectangular shell to form a continuous whole, which are positioned and glued inside the closed frame tube 53, and the tooling hanging point patches 112 are glued to the outside of the corresponding closed frame tube 53.

[0073] The optical substrate 1 of the present application adopts a composite structure of carbon fiber and metal-based composite materials, which solves the scale problem of large-scale substrates for the preparation and processing of traditional single metal-based composite materials, and the coupled carbon fiber has a greater design advantage in weight reduction.

[0074] The present application constructs a central high-stability area 2 mainly composed of metal-based composite materials for the carrying platform of high-precision loads. While meeting the condition of high-precision operation of a single machine, the remaining parts are designed with a stable frame of carbon fiber material structure, which reduces material costs.

[0075] The present application uses a carbon fiber honeycomb structure to fill the substrate, which solves the anisotropy problem of the original traditional honeycomb core strip distribution from the perspective 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 terms "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present application.

[0077] The above describes the specific embodiments of the present invention. It should be understood that the present invention 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 essence of the present invention. In the absence of conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims

1. A closed composite structure substrate for a space camera, characterized in that: The optical substrate (1) comprises a central high stability area (2), a load-bearing cylinder (3) and a carbon fiber frame plate (5) which are arranged in sequence from the inside to the 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 surface (101) and an optical substrate stand-alone surface (102); a carbon fiber ring belt (4) is provided at the light shield installation interface of the optical substrate camera surface (101); and discrete metal-based composite material patches (42) are inlaid on the carbon fiber ring belt (4); The central high stability region (2) comprises a metal matrix composite central tube (21), and the outer annular surface of the metal matrix composite central tube (21) is evenly 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) along the circumferential direction; 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, wherein the plurality of rectangular frame tubes (52) are respectively arranged in the extension direction of the force transmission path of the support frame of the central high stability area (2); The central high stability region (2) and the carbon fiber frame plate (5) are both filled with isotropically arranged hexagonal flanged carbon honeycombs (6).

2. The closed composite structure substrate for a space camera according to claim 1, characterized in that: The skin (7) comprises an integrated non-spliced ​​carbon fiber skin, wherein two pieces of the skin (7) are respectively glued and covered on the optical substrate camera surface (101) and the optical substrate single machine surface (102), and the outer edge of the skin (7) matches the outer edge of the carbon fiber frame plate (5). The skin (7) only does not cover the area of ​​the metal matrix composite material center tube (21), and a hole is opened on the skin (7) at the connection with the single machine.

3. The closed composite structure substrate for a space camera according to claim 1, characterized in that: The load-bearing cylinder (3) is a circular carbon fiber cylinder, and comprises a load-bearing inner cylinder skin (31), an aluminum honeycomb core sandwich (32), and a load-bearing outer cylinder skin (33) which are arranged in sequence from the inside to the outside. The upper and lower ends of the load-bearing inner cylinder skin (31) extend inward to form a skin flange, and the upper and lower ends of the load-bearing outer cylinder skin (33) extend outward to form a skin flange, and the skin flange is parallel to and glued to the skin (7). A second carbon fiber circular ring belt (34) is arranged on the outer side of the skin (7) of the optical substrate single machine surface (102), and the second carbon fiber circular ring belt (34) is arranged corresponding to the aluminum honeycomb core sandwich (32).

4. The closed composite structure substrate for a space camera according to claim 3, characterized in that: The carbon fiber ring band (4) is arranged corresponding to the aluminum honeycomb core sandwich (32); a protrusion is formed on one side of the metal-based composite material patch (42); the metal-based composite material patch (42) is embedded in the carbon fiber ring band (4) through the protrusion and is glued to the carbon fiber ring band (4); the metal-based composite material patch (42) and the sunshade installation interface have the same angle distribution and arc length.

5. The closed composite structure substrate for a space camera according to claim 1, characterized in that: The metal matrix composite central tube (21) is a structure of two radial rib-shaped closed hollow circular disks welded up and down, the metal matrix composite main support frame (23) is a structure of two cross-shaped rib-shaped hollow rectangular frames welded up and down, a single-machine mounting boss is provided on the metal matrix composite main support frame (23), the metal matrix composite auxiliary support frame (24) is an I-shaped rib-shaped hollow rectangular frame structure, and the carbon fiber auxiliary support frame (25) is a rectangular tube structure; Three main support frames (23) of the metal matrix composite material and three auxiliary support frames (24) of the metal matrix composite material are evenly arranged on the circumferential side of the central tube (21) of the metal matrix composite material, and the main support frames (23) of the metal matrix composite material and the auxiliary support frames (24) of the metal matrix composite material are arranged at intervals, and the auxiliary support frames (25) of the carbon fiber are arranged between two adjacent main support frames (23) of the metal matrix composite material and the auxiliary support frames (24) of the metal matrix composite material.

6. The closed composite structure substrate for a space camera according to claim 5, characterized in that: The carbon fiber frame plate (5) is a centrally symmetrical structure. A plurality of auxiliary supporting rectangular frame tubes (54) are further arranged inside the carbon fiber frame plate (5). The two ends of the auxiliary supporting rectangular frame tubes (54) are respectively connected to the load-bearing cylinder (3) and the closed frame tube (53). The rectangular frame tube (52), the closed frame tube (53) and the auxiliary supporting rectangular frame tube (54) are integrally formed. The peripheral side of the load-bearing cylinder (3) is connected to a plurality of joints (51). The load-bearing cylinder (3) is fastened to the carbon fiber frame plate (5) via the joints (51).

7. The closed composite structure substrate for a space camera according to claim 6, characterized in that: The carbon fiber auxiliary support skeleton (25), the rectangular frame tube (52) and the auxiliary support rectangular frame tube (54) are all provided with a tube cavity Type heat pipe (1001), the The upper and lower fins of the heat pipe (1001) are glued to the inner wall of the tube cavity; The outer wall of the load-bearing tube (3) is provided with a plurality of spatial S-shaped heat pipes (1002) along the circumferential direction. The plurality of spatial S-shaped heat pipes (1002) are staggeredly arranged in a ring shape from bottom to top. The upper and lower fins of the spatial S-shaped heat pipes (1002) are respectively glued to the skin flanges at the upper and lower ends of the load-bearing outer tube skin (33).

8. The closed composite structure substrate for a space camera according to claim 1, characterized in that: The diameter of the circumscribed circle of the honeycomb core cell (61) of the hexagonal flanged carbon honeycomb (6) is 1 / 3 of the height; the upper and lower parts of the honeycomb core cell (61) are both provided with flanges extending inwards; the flange width is 5% of the height; the flange thickness is consistent with the honeycomb wall; the honeycomb wall plying direction of the hexagonal flanged carbon honeycomb (6) is quasi-invariant of the thickness of the honeycomb core cell (61); and the arrangement of the hexagonal flanged carbon honeycomb (6) is divergent in the normal direction of each side surface of the honeycomb core cell (61) and arranged back to back one by one.

9. The closed composite structure substrate for a space camera according to claim 8, characterized in that: A plurality of carbon fiber embedded parts (8) are arranged at the single-machine installation interface of the single-machine surface (102) of the optical substrate, the carbon fiber embedded parts (8) are triangular equilateral configurations, each vertex of the triangle is a straight section, and a through slot opening connected to the hexagonal flanged carbon honeycomb (6) is formed in the longitudinal direction, and the carbon fiber embedded parts (8) are bonded to 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 material patches (9), and through holes are provided at the single machine installation joints on the discrete metal matrix composite material patches (9).

10. The closed composite structure substrate for a space camera according to claim 1, characterized in that: A plurality of tooling hanging points (11) are symmetrically and evenly spaced around the circumference of the closed frame tube (53); tooling hanging point embedded parts (111) of the tooling hanging points (11) are fastened to the inner cavity of the closed frame tube (53); and tooling hanging point patches (112) of the tooling hanging points (11) are glued to the outer surface of the closed frame tube (53).

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