CN115016095B - 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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- CN115016095B CN115016095B CN202210744936.XA CN202210744936A CN115016095B CN 115016095 B CN115016095 B CN 115016095B CN 202210744936 A CN202210744936 A CN 202210744936A CN 115016095 B CN115016095 B CN 115016095B
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- 239000003292 glue Substances 0.000 claims description 27
- 238000002347 injection Methods 0.000 claims description 15
- 239000007924 injection Substances 0.000 claims description 15
- 239000000463 material Substances 0.000 claims description 9
- 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
- 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
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 2
- 229910052782 aluminium Inorganic materials 0.000 claims description 2
- 230000003014 reinforcing effect Effects 0.000 claims description 2
- 230000005855 radiation Effects 0.000 claims 1
- 238000002310 reflectometry Methods 0.000 abstract 1
- 230000005484 gravity Effects 0.000 description 6
- 230000003287 optical effect Effects 0.000 description 5
- 238000013461 design Methods 0.000 description 4
- 230000035882 stress Effects 0.000 description 4
- 238000001514 detection method Methods 0.000 description 3
- 238000012360 testing method Methods 0.000 description 3
- 230000015556 catabolic process Effects 0.000 description 2
- 238000006731 degradation reaction Methods 0.000 description 2
- 238000003384 imaging method Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- 238000007711 solidification Methods 0.000 description 2
- 230000008023 solidification Effects 0.000 description 2
- 230000008646 thermal stress Effects 0.000 description 2
- 238000003466 welding Methods 0.000 description 2
- 229910001069 Ti alloy Inorganic materials 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
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- 230000005489 elastic deformation Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
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- 238000012986 modification Methods 0.000 description 1
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- 238000005457 optimization Methods 0.000 description 1
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Classifications
-
- 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
-
- 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
-
- 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)
- General Physics & Mathematics (AREA)
- Optics & Photonics (AREA)
- Life Sciences & Earth Sciences (AREA)
- 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 of low rigidity, large structural size, poor designability and high position precision and surface type precision of the traditional Bipod supporting structure aiming at the large-caliber reflector, and comprises the following steps: the reflection mirror comprises a reflection mirror of a closed hexagonal light-weight structure, three rectangular tangent planes processed on the side wall of the large-caliber reflection mirror, a rectangular boss connected with the rectangular tangent planes, a Bipod flexible support assembly connected with the rectangular boss, and a reflection mirror support plate connected with the Bipod flexible support assembly; the novel Bipod flexible supporting component comprises a bottom plate, two axial parallel incision double-shaft flexible supporting legs fixedly connected to the bottom plate and a rectangular connecting frame connected with the tops of the flexible supporting legs. The space reflector has good designability, high rigidity and good stability, can resist larger mechanical interference, and can meet the technical requirements of high surface shape precision and position reflectivity of the large-caliber reflector.
Description
Technical Field
The invention belongs to the field of space reflector lightweight designs and flexible supporting structures thereof, and particularly relates to a large-caliber space reflector with a novel Bipod flexible supporting structure.
Background
With the rapid development of space technology, in order to meet high-resolution and long-distance space detection, a space optical system is required to meet large caliber, long focal length and high resolution. The large-caliber reflector is used as an important optical element of the optical-mechanical structure of the space telescope, and the surface shape precision and the position precision of the large-caliber reflector determine the imaging quality of the whole optical system. The space telescope needs to be subjected to adjustment detection, temperature test and vibration test on the ground before being transmitted so as to ensure the optical supporting performance and structural stability during on-orbit. During ground test, the main mirror assembly is affected by gravity, assembly errors and temperature, and during rail, the main mirror assembly is mainly affected by gravity release and temperature non-uniformity. 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, in the design of flexible support of the space reflector, the gravity, the temperature, the ground adjustment, the emission vibration, overload and other severe environmental conditions must be considered, so that the surface shape precision of the reflector and the imaging quality of the telescope can be ensured.
At present, a three-point supporting structure is often adopted for the space large-caliber reflecting mirror, and the ground installation and adjustment detection reliability is highest due to the fact that the supporting structure is simple, the processing is easy, the quality is small. 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 detecting the reflector support with the optical axis horizontal. Through reasonable flexible link design, the side three-point support can effectively eliminate the thermal stress generated by assembly stress and temperature change. Bipod flexible supports are a common way of side support, having two flexible rods distributed symmetrically at an angle, as shown in figure 1. However, when the orthogonal blade type structure is applied to the support of a large-caliber reflector, the following problems are faced:
1) When three-point side support is adopted, in order to maintain the position accuracy and the surface type accuracy of the reflector under the working condition that the space reflector is subjected to radial gravity and temperature change, deformation of the flexible links of the orthogonal blades is needed to reduce surface type degradation and thermal stress, but when parameters of the orthogonal blades Bipod are 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 adoption of the orthogonal blade type Bipod supports, the stress concentration is reduced by chamfering the intersecting root, and the radial and axial rotation is realized, at least two pairs of orthogonal blades are required to be combined, and when the caliber of the reflector is increased, the size and the weight of the flexible support are also increased.
3) The orthogonal blade Bipod support has simple structure, but the structural parameters are not changed greatly, the designability is poor, and the structural form also determines the upper limit of the support rigidity and the support flexibility.
Disclosure of Invention
The invention provides a space reflector with a novel Bipod flexible supporting structure, which aims to solve 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, and the flexible link of the novel Bipod flexible supporting structure adopts a double-shaft flexible unit with an axial parallel incision, so that the structural designability of a supporting component is good, the rigidity is high, the stability is good, larger mechanical interference can be resisted, and the technical requirements of high surface shape precision and position mirror degree of a large-caliber reflector can be met.
In order to achieve the above purpose, the present invention adopts the following technical scheme:
A large-caliber space reflector with a novel Bipod flexible supporting structure, the space reflector comprises a reflector body (1), three rectangular tangential planes (14) are arranged on the side wall of the reflector body (1), rectangular bosses (2) are arranged on the rectangular tangential planes (14), the space reflector further comprises Bipod flexible supporting components (3) connected with the rectangular bosses (2), and reflector supporting plates (4) connected with the Bipod flexible supporting components (3);
The three rectangular tangential planes (14) are uniformly distributed along the circumferential direction of the reflector body (1), and the cross section size of the rectangular tangential planes (14) is slightly larger than the mounting surface size of the rectangular boss (2);
the Bipod flexible support assembly comprises a bottom plate (33), two double-shaft flexible support legs (32) fixedly connected to the bottom plate (33), and a rectangular connecting frame (31) connected to the tops of the two double-shaft flexible support legs, wherein the double-shaft flexible support legs (32) are provided with axial juxtaposition cuts, and the bottom plate (33) is fixed to the reflector support plate (4).
Further, the reflector body (1) is of a closed hexagonal lightweight structure; the reflector body (1) is circular and made of fused quartz material, and the diameter of the reflector body is larger than 600mm.
Further, 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 through welding.
Furthermore, round 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 tangential plane (14) through epoxy resin, and bonding positions are uniformly distributed.
Further, 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 apposition cuts are parabolic profile cuts apposed to the upper and lower shaft portions of the dual-shaft flexible support leg.
Further, 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 used for being fixedly connected with the rectangular connecting frame (31); the bottom plate (33) is fixedly connected with the reflector supporting plate (4) through screws.
Further, a mounting boss (41) with the thickness of 0.5mm is processed on the mounting surface of the reflector supporting plate (4).
Further, the rectangular boss (2) is made of Yan Gang materials, and the linear expansion coefficient of the rectangular boss is matched with that of the reflector body (1).
Further, the Bipod flexible support component (3) is made of TC 4; the reflector supporting plate is manufactured by processing an aluminum-based silicon carbide material (SiC/Al).
Further, the epoxy resin is DP460.
The beneficial effects of the invention are as follows:
1. the invention discloses a large-caliber space reflector with a novel Bipod flexible supporting structure, which adopts three Bipod flexible supports uniformly distributed on the side edges, and flexible supporting legs supported by each Bipod adopt two biaxial flexible units which are connected in series and are axially juxtaposed and notched.
2. According to the invention, through the reasonable design of the shape and thickness of the glue injection groove, the glue joint area and the glue joint thickness are strictly controlled, so that the tensile strength and the shearing strength of a glue joint mode can be effectively ensured, and the local stress generated during solidification shrinkage of the glue joint can be reduced.
Drawings
FIG. 1 is a schematic view of a three-point support knot hook on a side of a spatial mirror in the background art;
FIG. 2 is a top view of the large caliber spatial mirror of the present invention;
FIG. 3 is a front view of a large caliber spatial mirror of the present invention;
FIG. 4 is a 3/4 three-dimensional solid view of the lightweight structure of the large caliber space reflector of the present invention;
FIG. 5 is an enlarged view of a portion of the obscuration mirror of FIG. 3;
FIG. 6 is a partial schematic view of FIG. 3;
Wherein reference numerals include:
The reflector body 1, the rectangular boss 2, bipod flexible supporting components 3, the reflector supporting plate 4, the front panel 11, the honeycomb interlayer 12, the rear panel 13, the rectangular tangential plane 14, the circular glue injection groove 21, the glue injection hole 22, the glue overflow hole 23, the rectangular connecting frame 31, the flexible supporting legs 32, the bottom plate 33 and the mounting boss 41.
Detailed Description
For the purpose of more clearly describing the present invention, technical solutions and structural advantages, the present invention will be described in detail with reference to the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not to be construed as limiting the invention.
The following describes the embodiments of the present invention further with reference to the accompanying drawings by providing a large caliber space reflector with a novel Bipod flexible support structure.
As shown in fig. 2 and 3, the large-caliber space reflector with the novel Bipod flexible support structure comprises a reflector body 1, wherein the side wall of the reflector body 1 is provided with three rectangular tangent planes 14, the rectangular tangent planes 14 are connected with rectangular bosses 2, the space reflector further comprises a Bipod flexible support assembly 3 connected with the rectangular bosses 2, and a reflector support plate 4 connected with the Bipod flexible support assembly 3. The reflector body 1 realizes statically indeterminate support through a rectangular tangent plane 14 processed on the side wall of the reflector 1. In the embodiment of the invention, three rectangular tangential planes are uniformly distributed on the side wall of the large reflector body 1, specifically, the three rectangular tangential planes are uniformly distributed along the circumferential direction of the side wall of the reflector body 1 at 120 degrees, and each rectangular tangential plane corresponds to one rectangular boss and one novel Bipod flexible supporting component. The rectangular lug bosses are fixed at the rectangular tangential plane through cementing, and the installation axial positions of the three rectangular lug bosses are the same. Bipod the 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 kinematic supporting of the reflector is realized. The three side walls of the reflector support plate are provided with round lightening holes, the back of the reflector support plate adopts an open structure, and the reflector support plate is arranged by using radial reinforcing ribs, so that the weight is reduced and the rigidity of the components is enough.
In the embodiment of the present invention, as shown in fig. 4, the reflector body 1 is made of fused quartz material, and its diameter is generally greater than 600mm. As shown in fig. 4, the mirror front panel 11, the mirror honeycomb sandwich 12, and the mirror rear panel 13 are formed by welding; the hexagonal honeycomb lightweight structure is processed by the reflector honeycomb interlayer 12 in a cutting mode, so that the weight of the reflector body 1 is reduced.
In the embodiment of the invention, in order to facilitate 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 by 120 degrees, and the sizes of the three rectangular tangential surfaces 11 are slightly larger than those of the rectangular boss 3.
In the embodiment of the present invention, as shown in fig. 5, the rectangular boss 2 is made of Yan Gang material having a coefficient of expansion close to that of the reflector body 1. The rear end face of the rectangular boss 2 is provided with a circular glue injection groove 21, and the groove depth is 0.2mm. 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 the glue injection operation of the glue injector is convenient, and whether the glue injection groove is full or not is observed; the area and the thickness of the glue spots can be effectively controlled through the circular glue injection groove, so that the stress generated during the solidification and shrinkage of the glue layer is reduced as much as possible on the basis of guaranteeing the glue joint strength, and the surface shape precision of the reflector 1 is reduced. The rear end face of the rectangular boss 2 is bonded with a rectangular section of the side wall of the reflector through epoxy resin, and bonding positions are uniformly distributed; the epoxy resin is DP460. The front end of the rectangular boss 2 is 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 used for being fixedly connected 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 support assemblies 3 are fabricated from titanium alloy (TC 4), and each Bipod flexible support assembly 3 includes a base plate 33, two axially juxtaposed cut-outs, namely parabolic profile cut-outs juxtaposed to upper and lower shaft portions of the two axially juxtaposed cut-outs of the base plate, of the two axially juxtaposed flexible support legs 32, and a rectangular connecting frame 31 connected to the tops of the flexible support legs, thereby forming a flexible joint structure. In order to reduce degradation of mirror surface shape accuracy under radial gravity, the intersection point of the extension lines of the two flexible support legs of each Bipod coincides with the neutral plane of the mirror. The bottom plate 33 is fixed on the reflector supporting plate 4; the mounting surface of the reflector support 4 is provided with a mounting boss 41 with the thickness of 0.5mm, and the purpose of reducing the grinding area of a plane is mainly achieved, so that the coplanarity accuracy of the mounting boss 41 is ensured to be smaller than 1 mu with higher accuracy. Each double-shaft flexible supporting leg 32 supported by the novel Bipod disclosed by the invention adopts a two-shaft flexible link, the flexible link can realize two-direction rotation, the occupied space is greatly reduced, and the structural rigidity is sufficiently high through reasonable integration optimization, so that the surface shape precision of the reflecting mirror in the temperature, gravity, impact and vibration environments can be met. In order to realize precise assembly and adjustment of the rectangular boss and the novel Bipod flexible support assembly, threaded holes are formed in the top and two side edges of the rectangular boss for installing and fixing the Bipod flexible support assembly, and four sharp corners of a rectangular connecting frame of the Bipod flexible support assembly are convenient to assemble and adjust by adopting back chipping treatment; and the bottom plate of the Bipod flexible supporting component is fixedly connected with the reflector supporting plate by adopting a screw.
Although the foregoing has been described in some detail by way of illustration of one embodiment of the invention, it is to be understood that such embodiment is illustrative and not restrictive of the invention, and that structural changes, combinations, substitutions and alterations may be made herein by those skilled in the art without departing from the scope of the invention.
The above embodiments of the present invention do not fully define the scope of the invention. Any other modifications and variations made in accordance with the technical idea of the present invention should be included in the scope of the claims of the present invention.
Claims (9)
1. The large-caliber space reflector with the novel Bipod flexible supporting structure is characterized by comprising a reflector body (1), wherein three rectangular tangential planes (14) are arranged on the side wall of the reflector body (1), rectangular bosses (2) are arranged on the rectangular tangential planes (14), the space reflector further comprises Bipod flexible supporting components (3) connected with the rectangular bosses (2), and reflector supporting plates (4) connected with the Bipod flexible supporting components (3);
The three rectangular tangential planes (14) are uniformly distributed along the circumferential direction of the reflector body (1), and the cross section size of the rectangular tangential planes (14) is slightly larger than the mounting surface size of the rectangular boss (2);
The Bipod flexible support assembly comprises a bottom plate (33), two double-shaft flexible support legs (32) fixedly connected to the bottom plate (33), and a rectangular connecting frame (31) connected with the tops of the two double-shaft flexible support legs, wherein the two double-shaft flexible support legs (32) are respectively provided with an upper shaft part and a lower shaft part which are connected in series, the double-shaft flexible support legs (32) are provided with axial juxtaposition cuts, and the bottom plate (33) is fixed on the reflector support plate (4);
The back of the reflector supporting plate adopts an open structure and is arranged by using radiation type reinforcing ribs;
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 apposition cuts are parabolic profile cuts apposed to the upper and lower shaft portions of the dual-shaft flexible support leg.
2. The large caliber space mirror with novel Bipod flexible support structure as set forth in claim 1, wherein:
the reflector body (1) is of a closed hexagonal light-weight structure; the reflector body (1) is circular and made of fused quartz material, and the diameter of the reflector body is larger than 600mm.
3. A large caliber space reflector with a novel Bipod flexible support structure as set forth 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 welded mode.
4. The large caliber space mirror with novel Bipod flexible support structure as set forth 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 on the circular glue injection grooves (21); the rectangular boss (2) is bonded with the rectangular tangential plane (14) through epoxy resin, and bonding positions are uniformly distributed.
5. The large caliber space mirror with novel Bipod flexible support structure as set forth in claim 1, wherein:
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 used for being fixedly connected with the rectangular connecting frame (31); the bottom plate (33) is fixedly connected with the reflector supporting plate (4) through screws.
6. The large caliber space mirror with novel Bipod flexible support structure as set forth in claim 1, wherein: a mounting boss (41) with the thickness of 0.5mm is processed on the mounting surface of the reflector supporting plate (4).
7. The large caliber space mirror with novel Bipod flexible support structure as set forth 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).
8. The large caliber space mirror with novel Bipod flexible support structure as set forth in claim 1, wherein: the Bipod flexible supporting component (3) is made of TC 4; the reflector supporting plate is processed and prepared by adopting an aluminum-based silicon carbide material.
9. The large caliber space mirror with novel Bipod flexible support structure according to claim 4, wherein: the epoxy resin is DP460.
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| Application Number | Priority Date | Filing Date | Title |
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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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| CN202210744936.XA CN115016095B (en) | 2022-06-28 | 2022-06-28 | Large-caliber space reflector with novel Bipod flexible supporting structure |
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