CN115016095A - Large-caliber space reflector with novel Bipod flexible supporting structure - Google Patents
Large-caliber space reflector with novel Bipod flexible supporting structure Download PDFInfo
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- CN115016095A CN115016095A CN202210744936.XA CN202210744936A CN115016095A CN 115016095 A CN115016095 A CN 115016095A CN 202210744936 A CN202210744936 A CN 202210744936A CN 115016095 A CN115016095 A CN 115016095A
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- 239000003292 glue Substances 0.000 claims description 26
- 238000002347 injection Methods 0.000 claims description 15
- 239000007924 injection Substances 0.000 claims description 15
- 239000000463 material Substances 0.000 claims description 13
- 239000003822 epoxy resin Substances 0.000 claims description 6
- 239000011229 interlayer Substances 0.000 claims description 6
- 229920000647 polyepoxide Polymers 0.000 claims description 6
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims description 3
- 239000005350 fused silica glass Substances 0.000 claims description 3
- 230000007935 neutral effect Effects 0.000 claims description 3
- 238000012545 processing Methods 0.000 claims description 3
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 claims description 3
- 229910010271 silicon carbide Inorganic materials 0.000 claims description 3
- 238000003466 welding Methods 0.000 claims description 3
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 2
- 229910052782 aluminium Inorganic materials 0.000 claims description 2
- 230000005484 gravity Effects 0.000 description 6
- 230000003287 optical effect Effects 0.000 description 6
- 238000001514 detection method Methods 0.000 description 4
- 230000035882 stress Effects 0.000 description 4
- 238000013461 design Methods 0.000 description 3
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- 238000012360 testing method Methods 0.000 description 3
- 229910001374 Invar Inorganic materials 0.000 description 2
- 230000015556 catabolic process Effects 0.000 description 2
- 238000006731 degradation reaction Methods 0.000 description 2
- 238000003384 imaging method Methods 0.000 description 2
- 238000005457 optimization Methods 0.000 description 2
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- 229910001069 Ti alloy Inorganic materials 0.000 description 1
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- G—PHYSICS
- G02—OPTICS
- G02B—OPTICAL ELEMENTS, SYSTEMS OR APPARATUS
- G02B7/00—Mountings, adjusting means, or light-tight connections, for optical elements
- G02B7/18—Mountings, adjusting means, or light-tight connections, for optical elements for prisms; for mirrors
- G02B7/182—Mountings, adjusting means, or light-tight connections, for optical elements for prisms; for mirrors for mirrors
- G02B7/183—Mountings, adjusting means, or light-tight connections, for optical elements for prisms; for mirrors for mirrors specially adapted for very large mirrors, e.g. for astronomy, or solar concentrators
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- G—PHYSICS
- G02—OPTICS
- G02B—OPTICAL ELEMENTS, SYSTEMS OR APPARATUS
- G02B7/00—Mountings, adjusting means, or light-tight connections, for optical elements
- G02B7/18—Mountings, adjusting means, or light-tight connections, for optical elements for prisms; for mirrors
- G02B7/182—Mountings, adjusting means, or light-tight connections, for optical elements for prisms; for mirrors for mirrors
- G02B7/198—Mountings, adjusting means, or light-tight connections, for optical elements for prisms; for mirrors for mirrors with means for adjusting the mirror relative to its support
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/40—Solar thermal energy, e.g. solar towers
- Y02E10/47—Mountings or tracking
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- Physics & Mathematics (AREA)
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- Optics & Photonics (AREA)
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- Astronomy & Astrophysics (AREA)
- Sustainable Development (AREA)
- Aerials With Secondary Devices (AREA)
- Optical Elements Other Than Lenses (AREA)
Abstract
The invention discloses a large-caliber space reflector with a novel Bipod flexible supporting structure, which solves the problems that the existing traditional Bipod supporting structure has low rigidity, large structure size, poor designability and how to obtain high position precision and surface type precision aiming at the large-caliber reflector, and comprises the following steps: the reflector with the closed hexagonal lightweight structure, three rectangular sections processed on the side wall of the large-aperture reflector, a rectangular boss connected with the rectangular sections, a Bipod flexible supporting assembly connected with the rectangular boss and a reflector supporting plate connected with the Bipod flexible supporting assembly; the novel Bipod flexible supporting assembly comprises a bottom plate, two double-shaft flexible supporting legs which are fixedly connected with the bottom plate and provided with notches in parallel in the axial direction, and a rectangular connecting frame connected with the tops of the flexible supporting legs. The space reflector has the advantages of good designability, high rigidity and good stability, can resist large mechanical interference, and can meet the technical requirements of high surface shape precision and position power of a large-aperture reflector.
Description
Technical Field
The invention belongs to the field of light weight design of a space reflector and a flexible supporting structure thereof, and particularly relates to a large-caliber space reflector with a novel Bipod flexible supporting structure.
Background
With the rapid development of the space technology, in order to meet the requirements of high-resolution and long-distance space detection, a space optical system is required to meet the requirements of large caliber, long focal length and high resolution. The large-aperture reflector is used as an important optical element of an optical machine structure of the space telescope, and the surface shape precision and the position precision of the large-aperture reflector determine the imaging quality of the whole optical system. Before launching, the space telescope needs to be subjected to installation and adjustment detection, temperature test and vibration test on the ground to ensure the optical support performance and structural stability in orbit. During ground test, the main mirror assembly is influenced by gravity, assembly error and temperature, and is mainly influenced by gravity release and temperature nonuniformity during on-orbit. The support isolates the transmission of external load to the mirror surface through self elastic deformation, and the frequency of the mirror assembly is ensured through self rigidity. Therefore, the design of the flexible support of the space reflector must consider the severe environmental conditions such as gravity, temperature, ground installation and adjustment, emission vibration, overload and the like, so as to ensure the surface shape precision of the reflector and the imaging quality of the telescope.
At present, a three-point supporting structure is often adopted for a space large-caliber reflector, and the three-point supporting structure is simple in supporting structure, easy to machine, small in mass and highest in ground installation, adjustment and detection reliability. The side three-point support is a support mode which takes the side wall of the reflector as a positioning reference and is used for supporting the reflector with the detection state of the horizontal optical axis. Through reasonable flexible link design, the side three-point support can effectively eliminate the assembly stress and the thermal stress generated by temperature change. The Bipod flexible support is a common side support mode, and has two flexible rods which are symmetrically distributed at a certain angle, as shown in fig. 1. However, when the orthogonal blade type structure is applied to the support of a large-aperture reflector, the following problems are faced in the flexible link:
1) when three-point side support is adopted, under the working condition that the space reflector is subjected to radial gravity and temperature change, in order to keep the position precision and the surface type precision of the reflector, the deformation of a flexible link of an orthogonal blade is needed to reduce the surface type degradation and the thermal stress, but when the orthogonal blade Bipod parameter is optimized, the thickness of the whole blade is always uniformly changed, so that the radial rigidity is weaker, the fundamental frequency is lower, and the damage risk is increased under the condition of vibration or overload;
2) the orthogonal blade type Bipod support is adopted, chamfering treatment must be carried out on intersecting root parts to reduce stress concentration, at least two pairs of orthogonal blades are required to realize radial and axial rotation, and when the caliber of the reflector is increased, the size and the weight of the flexible support are increased.
3) Although the orthogonal blade type Bipod support is simple in structure, the change of the structural parameters of the orthogonal blade type Bipod support has little change on the structural performance and poor designability, and the structural form also determines the upper limit of the support rigidity and the support flexibility of the orthogonal blade type Bipod support.
Disclosure of Invention
The invention provides a space reflector with a novel Bipod flexible supporting structure, aiming at solving the problems of large structural size, low structural rigidity, low designability and high surface shape precision and position precision of a reflector supporting structure in the background technology.
In order to achieve the purpose, the invention adopts the following technical scheme:
a large-caliber space reflector with a novel Bipod flexible supporting structure comprises a reflector body (1), wherein the side wall of the reflector body (1) is provided with three rectangular sections (14), rectangular bosses (2) are arranged on the rectangular sections (14), the space reflector further comprises a Bipod flexible supporting assembly (3) connected with the rectangular bosses (2), and a reflector supporting plate (4) connected with the Bipod flexible supporting assembly (3);
the three rectangular sections (14) are uniformly distributed along the circumferential direction of the reflector body (1), and the sectional size of each rectangular section (14) is slightly larger than the size of the mounting surface of each rectangular boss (2);
bipod flexible support subassembly includes bottom plate (33), links firmly two biax flexible support legs (32) on bottom plate (33), and with rectangular connection frame (31) that two biax flexible support leg tops are connected, biax flexible support leg (32) have the axial and juxtapose the incision, bottom plate (33) fix on reflector backup pad (4).
Further, the reflector body (1) is of a closed hexagonal lightweight structure; the reflector body (1) is circular, is made of fused quartz materials, and has a diameter larger than 600 mm.
Furthermore, the reflector body (1) comprises a reflector front panel (11), a reflector honeycomb interlayer (12) and a reflector rear panel (13), and the reflector front panel (11), the reflector honeycomb interlayer (12) and the reflector rear panel (13) are connected in a welding mode.
Furthermore, circular glue injection grooves (21) with the groove depth of 0.2mm are uniformly distributed on the rear end face of the rectangular boss (2), and glue injection holes (22) with the diameter of 2mm and glue overflow holes (23) with the diameter of 1.5mm are processed on the glue injection grooves; the rectangular boss (2) is bonded with the rectangular section (14) through epoxy resin, and bonding positions are uniformly distributed.
Furthermore, the intersection point of the extension lines of the two biaxial flexible support legs (32) of each Bipod flexible support assembly is positioned on the neutral plane of the reflector body (1); the axial juxtaposition cuts are parabolic profile cuts which are juxtaposed to the upper shaft part and the lower shaft part of the biaxial flexible supporting leg.
Furthermore, the rectangular boss (2) comprises a thin-wall frame, and three threaded holes are respectively formed in the upper side, the left side and the right side of the thin-wall frame and are fixedly connected with the rectangular connecting frame (31); the bottom plate (33) is fixedly connected with the reflector support plate (4) through screws.
Furthermore, a mounting boss (41) with the thickness of 0.5mm is processed on the mounting surface of the reflector support plate (4).
Furthermore, the material of the rectangular boss (2) is matched with the linear expansion coefficient of the material of the reflector body (1), and is made of an invar material.
Further, the Bipod flexible supporting component (3) is made of TC 4; the reflector supporting plate is prepared by processing aluminum-based silicon carbide material (SiC/Al).
Further, the epoxy resin is DP 460.
The beneficial effects of the invention are:
1. the invention discloses a large-caliber space reflector with a novel Bipod flexible support structure, which adopts three Bipod flexible supports uniformly distributed on the side edge, adopts a double-shaft flexible unit with two axially juxtaposed notches connected in series for each flexible supporting leg of the Bipod support, has compact structure and strong designability, can ensure high rigidity of a reflector component through optimization of integrated parameters, and ensures that a lightweight reflector has higher surface shape precision and position precision.
2. According to the invention, by designing the shape and thickness of the glue injection groove reasonably, the glue joint area and the glue joint thickness are strictly controlled, the tensile strength and the shear strength of a glue joint mode can be effectively ensured, and the local stress generated during curing shrinkage of glue joint can be reduced.
Drawings
FIG. 1 is a schematic view of a three-point support hook on the side of a space reflector in the background art;
FIG. 2 is a top view of a large aperture spatial mirror of the present invention;
FIG. 3 is a front view of a large aperture spatial mirror of the present invention;
FIG. 4 is a 3/4 three-dimensional solid diagram of the light-weighted structure of the large-aperture space reflector of the present invention;
FIG. 5 is an enlarged view of a portion of the hidden mirror of FIG. 3;
FIG. 6 is a partial schematic view of FIG. 3;
wherein the reference numerals include:
the reflector comprises a reflector body 1, a rectangular boss 2, a Bipod flexible supporting assembly 3, a reflector supporting plate 4, a front panel 11, a honeycomb interlayer 12, a rear panel 13, a rectangular section 14, a circular glue injection groove 21, a glue injection hole 22, a glue overflow hole 23, a rectangular connecting frame 31, flexible supporting legs 32, a bottom plate 33 and a mounting boss 41.
Detailed Description
For the purpose of clearly explaining the objects, technical solutions and structural advantages of the present invention, the present invention will be described in detail below with reference to the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not to be construed as limiting the invention.
The following describes a large-aperture space mirror with a novel Bipod flexible supporting structure according to an embodiment of the present invention with reference to the accompanying drawings.
As shown in fig. 2 and fig. 3, the large-aperture space reflector with the novel Bipod flexible supporting structure of the present invention includes a reflector body 1, the side wall of the reflector body 1 has three rectangular facets 14, and the rectangular facets 14 are connected to form rectangular bosses 2, the space reflector further includes a Bipod flexible supporting component 3 connected to the rectangular bosses 2, and a reflector supporting plate 4 connected to the Bipod flexible supporting component 3. The reflector body 1 realizes statically determinate support by processing a rectangular tangent surface 14 on the side wall of the reflector 1. In the implementation case of the invention, three rectangular sections are uniformly distributed on the side wall of the large reflector body 1, specifically, the three rectangular sections are uniformly distributed along the circumferential direction of the side wall of the reflector body 1 at an angle of 120 degrees, and each rectangular section corresponds to one rectangular boss and one novel Bipod flexible supporting component. The rectangular bosses are fixed at the rectangular section by gluing, and the mounting axial positions of the three rectangular bosses are the same. The Bipod flexible supporting component 3 is fixedly connected with the reflector 1 through the rectangular boss 2 and is fixed on the reflector supporting plate 4, and finally three-point side edge kinematic support of the reflector is achieved. Circular lightening holes are processed on three side walls of the reflector supporting plate, the back of the reflector supporting plate is of an open structure, and radiation type reinforcing ribs are arranged, so that sufficient assembly rigidity is guaranteed while lightening.
In the embodiment of the present invention, as shown in fig. 4, the reflector body 1 is made of fused silica material, and the diameter thereof is generally larger than 600 mm. As shown in fig. 4, the reflector front panel 11, the reflector honeycomb sandwich 12 and the reflector rear panel 13 are formed by welding; the reflector honeycomb interlayer 12 is processed into a hexagonal honeycomb lightweight structure in a cutting mode, so that the reflector body 1 is lightweight.
In the embodiment of the invention, in order to facilitate the high-precision positioning connection with the rectangular boss 3, three rectangular boss surfaces 11 are uniformly distributed and processed on the reflector body 1 along the circumferential direction at 120 degrees, and the size of the three rectangular section 11 is slightly larger than that of the rectangular boss 3.
In the embodiment of the present invention, as shown in fig. 5, the material of the rectangular projection 2 is made of an invar material having an expansion coefficient close to that of the material of the mirror body 1. The back end face of the rectangular boss 2 is provided with a circular glue injection groove 21, and the groove depth is 0.2 mm. A glue injection hole 22 with the diameter of 2mm and a glue overflow hole 23 with the diameter of 1.5mm are processed on the glue injection groove, so that a glue injector can conveniently perform glue injection operation and observe whether the glue injection groove is full; the area and the thickness of the glue spot can be effectively controlled through the circular glue injection groove, and on the basis of ensuring the bonding strength, the stress generated when the glue layer is cured and shrunk is reduced as much as possible, so that the surface shape precision of the reflector 1 is reduced. The rear end face of the rectangular boss 2 is bonded with the rectangular section of the side wall of the reflector through epoxy resin, and bonding positions are uniformly distributed; the epoxy resin is DP 460. The front end of the rectangular boss 2 is a thin-wall frame, and the upper, left and right sides of the thin-wall frame are respectively provided with three threaded holes for fixedly connecting with the rectangular connecting frame 31 of the Bipod flexible supporting component 3.
In the embodiment of the present invention, as shown in fig. 6, three novel Bipod flexible supporting assemblies 3 are processed from titanium alloy (TC4), and each Bipod flexible supporting assembly 3 includes a bottom plate 33, two biaxial flexible supporting legs 32 fixed to the bottom plate and having two axially juxtaposed notches, and a rectangular connecting frame 31 connected to the tops of the flexible supporting legs, wherein the axially juxtaposed notches are parabolic profile notches juxtaposed to the upper shaft portion and the lower shaft portion of the biaxial flexible supporting legs 32, thereby forming a flexible joint structure. In order to reduce the degradation of the mirror surface shape accuracy under radial gravity, the intersection point of the extension lines of the two flexible legs of each Bipod coincides with the neutral plane of the mirror. The bottom plate 33 is fixed on the reflector support plate 4; the mirror support 4 has a mounting boss 41 of 0.5mm on its mounting face, primarily to reduce the planar grinding area, thereby ensuring a coplanar accuracy of the mounting boss 41 of less than 1 mu with greater accuracy. Each double-shaft flexible supporting leg 32 of the novel Bipod support adopts a double-shaft flexible link, the flexible link can realize rotation in two directions, the occupied space is greatly reduced, and through reasonable integration and optimization, enough structural rigidity can be obtained, and the surface shape precision of the reflector in the temperature, gravity, impact and vibration environments can be met. In order to realize the precise assembly and adjustment of the rectangular boss and the novel Bipod flexible supporting assembly, threaded holes are processed at the top and two side edges of the rectangular boss for installing and fixing the Bipod flexible supporting assembly, and four sharp corners of a rectangular connecting frame of the Bipod flexible supporting assembly are convenient to assemble and adjust by adopting back chipping treatment; and the bottom plate of the Bipod flexible supporting assembly is fixedly connected with the reflector supporting plate by screws.
Although the above embodiment of the present invention has been described in detail, it should be understood that the above embodiment is illustrative, and not restrictive, and that various changes, combinations, substitutions, and alterations can be made herein without departing from the spirit and scope of the invention as defined by the appended claims.
The above detailed description of the present invention is not intended to be exhaustive or to limit the scope of the present invention. Any other various modifications and changes made according to the technical idea of the present invention should be included in the protection scope of the claims of the present invention.
Claims (10)
1. The large-aperture space reflector with the novel Bipod flexible supporting structure is characterized by comprising a reflector body (1), wherein the side wall of the reflector body (1) is provided with three rectangular tangent planes (14), a rectangular boss (2) is arranged on each rectangular tangent plane (14), the space reflector further comprises a Bipod flexible supporting assembly (3) connected with each rectangular boss (2) and a reflector supporting plate (4) connected with the Bipod flexible supporting assembly (3);
the three rectangular sections (14) are uniformly distributed along the circumferential direction of the reflector body (1), and the sectional size of each rectangular section (14) is slightly larger than the size of the mounting surface of each rectangular boss (2);
bipod flexible support subassembly includes bottom plate (33), links firmly two biax flexible support legs (32) on bottom plate (33), and with rectangular connection frame (31) that two biax flexible support leg tops are connected, biax flexible support leg (32) have the axial and juxtapose the incision, bottom plate (33) fix on reflector backup pad (4).
2. The large-aperture space reflector with the novel Bipod flexible supporting structure as claimed in claim 1, wherein:
the reflector body (1) is of a closed hexagonal lightweight structure; the reflector body (1) is circular, is made of fused quartz materials, and has a diameter larger than 600 mm.
3. The large-aperture space reflector with the novel Bipod flexible supporting structure as claimed in claim 2, wherein:
the reflector body (1) comprises a reflector front panel (11), a reflector honeycomb interlayer (12) and a reflector rear panel (13), and the reflector front panel (11), the reflector honeycomb interlayer (12) and the reflector rear panel (13) are connected in a welding mode.
4. The large-caliber space reflector with the novel Bipod flexible supporting structure as claimed in claim 1, wherein:
circular glue injection grooves (21) with the groove depth of 0.2mm are uniformly distributed on the rear end face of the rectangular boss (2), and glue injection holes (22) with the diameter of 2mm and glue overflow holes (23) with the diameter of 1.5mm are processed in the circular glue injection grooves (21); the rectangular boss (2) is bonded with the rectangular section (14) through epoxy resin, and bonding positions are uniformly distributed.
5. The large-aperture space reflector with the novel Bipod flexible supporting structure as claimed in claim 1, wherein:
the intersection point of the extension lines of the two biaxial flexible support legs (32) of each Bipod flexible support assembly is positioned on the neutral plane of the reflector body (1); the axial juxtaposition cuts are parabolic profile cuts which are arranged on the upper shaft part and the lower shaft part of the biaxial flexible supporting leg.
6. The large-aperture space reflector with the novel Bipod flexible supporting structure as claimed in claim 1, wherein:
the rectangular boss (2) comprises a thin-wall frame, and three threaded holes are formed in the upper side, the left side and the right side of the thin-wall frame respectively and are used for being fixedly connected with the rectangular connecting frame (31); the bottom plate (33) is fixedly connected with the reflector support plate (4) through screws.
7. The large-aperture space reflector with the novel Bipod flexible supporting structure as claimed in claim 5, wherein: and a mounting boss (41) with the thickness of 0.5mm is processed on the mounting surface of the reflector support plate (4).
8. The large-aperture space reflector with the novel Bipod flexible supporting structure as claimed in claim 1, wherein: the material of the rectangular boss (2) is matched with the linear expansion coefficient of the material of the reflector body (1).
9. The large-aperture space reflector with the novel Bipod flexible supporting structure as claimed in claim 1, wherein: the Bipod flexible supporting component (3) is made of TC 4; the reflector supporting plate is prepared by processing an aluminum-based silicon carbide material.
10. The large-aperture space reflector with the novel Bipod flexible supporting structure as claimed in claim 4, wherein: the epoxy resin is DP 460.
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| CN202210744936.XA CN115016095B (en) | 2022-06-28 | 2022-06-28 | Large-caliber space reflector with novel Bipod flexible supporting structure |
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