CN107144935B - Primary and secondary mirror support of high resonant frequency of micro-deformation - Google Patents
Primary and secondary mirror support of high resonant frequency of micro-deformation Download PDFInfo
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- CN107144935B CN107144935B CN201710458209.6A CN201710458209A CN107144935B CN 107144935 B CN107144935 B CN 107144935B CN 201710458209 A CN201710458209 A CN 201710458209A CN 107144935 B CN107144935 B CN 107144935B
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- secondary mirror
- supporting seat
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- support
- wings
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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
- G02B7/008—Mountings, adjusting means, or light-tight connections, for optical elements with means for compensating for changes in temperature or for controlling the temperature; thermal stabilisation
-
- 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
Abstract
The invention particularly relates to a micro-deformation primary and secondary mirror support with high resonant frequency, which solves the problems of complex structure, higher cost and lower resonant frequency of the conventional primary and secondary mirror support device. The mirror support comprises a primary mirror support seat, a secondary mirror support seat, three support wings and three reinforcing ribs; the primary mirror supporting seat is of a circular ring structure, and the secondary mirror supporting seat is of a hollow truncated cone structure; one ends of the three supporting wings are fixedly arranged on the primary mirror supporting seat at equal intervals; the other ends of the three supporting wings are fixedly arranged on the secondary mirror supporting seat at equal intervals and are tangent to the conical surface of the secondary mirror supporting seat, and when the secondary mirror supporting seat is seen in the axial direction, a small triangle is formed by the tangent parts of the three supporting wings and the conical surface of the secondary mirror supporting seat, and the small triangle is also the edge of the secondary mirror supporting seat; the three reinforcing ribs are respectively arranged in the middle of the adjacent supporting wings. The invention has better structural stability and can effectively improve the resonant frequency of the large-span primary mirror bracket and the large-span secondary mirror bracket.
Description
Technical Field
The invention belongs to the field of aerospace optical lens supporting devices, and particularly relates to a large-span micro-deformation primary and secondary lens support with high resonant frequency.
Background
At present, in the field of aerospace optical engineering, particularly in a large-caliber coaxial optical system, the requirement on the optical interval of a primary mirror and a secondary mirror is high, the requirement on the accuracy of the optical interval is high, and the requirement on the coaxiality of the primary mirror and the secondary mirror is high and the requirement on the blocking ratio is low. In order to ensure that the system has a smaller blocking ratio, the supporting structure generally supports and fixes the secondary mirror by a plurality of supporting ribs, the resonant frequency of the bracket of the primary mirror and the secondary mirror is lower due to insufficient rigidity of the supporting ribs, and the optical axis of the secondary mirror and the optical axis of the primary mirror deviate due to external vibration or thermal strain to form aberration so as to influence the observation index of the whole system. If the design allowance of the primary mirror support and the secondary mirror support is insufficient, optical load failure and rejection are even caused in the vibration examination test process of the mechanical environment.
In a conventional supporting structure, a secondary mirror assembly is connected with a primary mirror through a lens barrel, the lens barrel expands with heat and contracts with cold, the change of the optical interval of the primary mirror and the secondary mirror and the deviation of a system optical axis are caused, the position of an optical load optimal image surface changes along with the temperature, the problem is solved by adding a dynamic focusing mechanism at the rear end of the load in the conventional device, the dynamic focusing mechanism adjusts the optimal imaging focal plane according to the change of temperature parameters, so as to ensure the optimal optical index, but due to the complexity of an in-orbit space environment, the risk of failure of the dynamic focusing mechanism is higher, and the focusing mechanism also increases the quality of the load, so that the supporting device for the primary mirror and the secondary mirror has a complex structure and increased cost, and does not accord with the design requirement of light weight in spaceflight. Meanwhile, all the supporting structural members of the optical system are made of micro-thermal strain materials with high density, so that the optical load is too large.
Disclosure of Invention
In order to solve the problems of complex structure, higher cost and lower resonant frequency of the conventional primary and secondary mirror supporting device, the invention provides a large-span micro-strain high-resonant-frequency primary and secondary mirror support, which has higher resonant frequency and smaller weight on the premise of ensuring smaller thermal strain and ensures the stability of indexes of an optical system.
The technical scheme of the invention is as follows:
a primary mirror support and a secondary mirror support with micro-deformation and high resonant frequency comprise a primary mirror support seat and a secondary mirror support seat which are coaxially arranged, and further comprise three support wings and three reinforcing ribs; the primary mirror supporting seat is of a circular ring structure, the secondary mirror supporting seat is of a hollow truncated cone structure, and a through hole for mounting the secondary mirror is formed in the end face of the secondary mirror supporting seat; one ends of the three supporting wings are fixedly arranged on the primary mirror supporting seat at equal intervals; the other ends of the three supporting wings are fixedly arranged on the secondary mirror supporting seat at equal intervals, and combined with structural mechanics analysis, when the three supporting wings are tangent to the conical surface of the secondary mirror supporting seat to form offset type support, the secondary mirror support has higher resonant frequency, and when viewed from the axial direction of the secondary mirror supporting seat, the tangent parts of the three supporting wings and the conical surface of the secondary mirror supporting seat form a small triangle which is also the edge of the secondary mirror supporting seat; the three reinforcing ribs are respectively arranged in the middle of the adjacent supporting wings.
Furthermore, a lightening hole is also formed in the secondary mirror supporting seat. The lightening holes can lighten the whole weight of the bracket, increase the effective light-passing area of the system and reduce the obscuration ratio of the optical system.
Furthermore, the main mirror supporting seat, the secondary mirror supporting seat, the supporting wings and the reinforcing ribs are all made of metal materials or carbon fiber composite materials with low thermal expansion coefficients, so that the drift displacement of the optimal focal plane of the system is reduced within an acceptable range, and the metal materials with the low thermal expansion coefficients have relatively low manufacturing cost, short processing period and relatively light weight.
Furthermore, the primary mirror support seat, the secondary mirror support seat, the support wings and the reinforcing ribs are integrally formed by casting when made of metal materials with low thermal expansion coefficients, so that the overall structural stability of the support is ensured.
Furthermore, the primary mirror supporting seat, the secondary mirror supporting seat, the supporting wings and the reinforcing ribs are all made of iron-nickel alloy, so that the support has low cost.
Furthermore, in order to ensure the overall structural stability of the support, the three reinforcing ribs are arranged on the same plane, so that the structural stability of the support is better.
The invention has the advantages that:
1. the bracket has better structural stability through the 2 large triangles and the 2 small triangles, and the resonant frequency of the large-span primary mirror bracket and the large-span secondary mirror bracket can be effectively improved.
2. The invention has no moving parts and has the advantages of low cost, high safety factor of on-orbit operation and smaller weight.
3. The drift displacement of the optimal focal plane of the system is reduced within an acceptable range by the metal material with the low thermal expansion coefficient, and the metal material with the low thermal expansion coefficient has relatively low manufacturing cost, short processing period and relatively light weight.
4. The lightening holes in the invention can not only lighten the whole weight of the bracket, but also increase the effective light-passing area of the system and reduce the blocking ratio of the optical system.
5. The primary mirror bracket and the secondary mirror bracket are integrally formed by casting, so that the structural stability of the whole bracket is ensured.
Drawings
FIG. 1 is a schematic diagram of a first embodiment of the present invention;
FIG. 2 is an axial view of FIG. 1;
FIG. 3 is a schematic diagram of the second embodiment of the present invention;
FIG. 4 is a simplified schematic diagram of an embodiment of the present invention.
Reference numerals: 1-supporting wings, 2-reinforcing ribs, 3-large triangles, 4-small triangles, 5-primary mirror supporting seats, 6-secondary mirror supporting seats and 7-lightening holes.
Detailed Description
The invention is described in further detail below with reference to the following figures and specific examples:
as shown in fig. 1, the micro-deformation high-resonant-frequency primary and secondary mirror support comprises a primary mirror support seat 5 and a secondary mirror support seat 6 which are coaxially arranged, wherein the primary mirror support seat 5 is of a circular ring structure, the secondary mirror support seat 6 is of a hollow truncated cone structure, the two support seats are connected together through three support wings 1, reinforcing ribs 2 are arranged between the adjacent support wings, and the three support wings 1 are uniformly distributed between the primary mirror support seat and the secondary mirror support seat along the circumference. One end of each supporting wing is fixedly connected with the primary mirror supporting seat, the other end of each supporting wing is tangent to the conical surface of the secondary mirror supporting seat, namely, when the secondary mirror supporting seat is seen from the axial direction, the tangent part of the conical surface of each supporting wing and the conical surface of each secondary mirror supporting seat forms a small triangle 4, the small triangle 4 is also the edge of one end of each secondary mirror supporting seat, and the other end of each secondary mirror supporting seat is a round hole and is used for mounting a secondary mirror. The three reinforcing ribs 2 are arranged on the same plane, namely, the reinforcing ribs are connected end to form a large triangle 3.
The secondary mirror supporting seat 6 is provided with a lightening hole 7. The lightening holes 7 can lighten the whole weight of the bracket, increase the effective light-passing area of the system and reduce the obscuration ratio of the optical system. The three reinforcing ribs 2 are respectively and fixedly arranged in the middle of the adjacent supporting wings, finite element analysis software is applied to set the positions of the reinforcing ribs 2 as variable parameters, the optimized resonance frequency is solved, and the arrangement positions of the reinforcing ribs 2 are finally determined according to the higher resonance frequency.
The primary mirror supporting seat 5, the secondary mirror supporting seat 6, the supporting wings 1 and the reinforcing ribs 2 are all made of metal materials or carbon fiber composite materials with low thermal expansion coefficients, and micro thermal strain design is achieved. In order to ensure the stability of the bracket structure, the primary and secondary mirror brackets are cast and integrally formed when the metal material with low thermal expansion coefficient is adopted.
As shown in figure 2, the invention provides a large-span microstrain high-resonance-frequency primary and secondary mirror support, the whole support is formed by processing iron-nickel alloy, a support structure adopts three support wings 1, and the support wings 1 are tangent to the conical surface of a secondary mirror support seat
The offset type supporting form of the support structure comprises three supporting wings 1, a small triangle 4 is formed at the tangent part of the conical surface of a secondary mirror supporting seat 6, the resonant frequency of the supporting structure is improved, the middle parts of the three supporting wings 1 are connected through three reinforcing ribs 2, a large triangle 3 is formed at the middle part of the supporting wing 1, the structural stability of the front triangle and the rear triangle is utilized, the resonant frequency of a large-span primary mirror support and the secondary mirror support can be effectively improved, the drifting displacement of the optimal focal plane of the system is reduced within an acceptable range through a metal material with a low thermal expansion coefficient, the metal material with the low thermal expansion coefficient is low in price, and the heating is performed on the metal material with the low thermal expansion coefficientThe invention has the advantages of low cost, high safety factor of on-orbit operation and smaller weight.
As shown in fig. 3 and 4, the support wing 1 is in the shape of a lath, and has the structural parameters: width b1, thickness h1; the reinforcing ribs 2 are in the shape of laths, and the structural parameters are as follows: width b2, thickness h2; on the premise of ensuring the blocking ratio index requirement of the optical system, a certain temperature change condition is set through finite element analysis software, four parameters of the support wing 1 and the reinforcing rib 2 are optimized and analyzed by taking the sum of the relative offset displacement D of the resonant frequency F and the secondary mirror as an optimization objective function, and a higher resonant frequency F is obtained by comprehensively analyzing the result max And a smaller D min . Through the design and optimization analysis measures and other measures, the large-span primary mirror and secondary mirror bracket has the characteristics of higher resonant frequency, micro thermal strain, low development cost, short development period, light product weight and high safety factor.
The protection scope of the present invention is not limited to the specific embodiments of the present invention, and it should be understood that the technical features of the present invention can be easily changed by those skilled in the art from the present disclosure, which is directly derived from the basic modifications of the present invention, which are related to the same principle and structure, or the substitution of the prior art with the commonly known techniques, and the mutual different combinations with the same features, the same or similar technical effects, all of which belong to the protection scope of the present invention.
Claims (6)
1. The utility model provides a primary and secondary mirror support of high resonant frequency warp a little, includes primary mirror supporting seat and secondary mirror supporting seat of coaxial setting, its characterized in that: the device also comprises three support wings and three reinforcing ribs; the primary mirror supporting seat is of a circular ring structure, the secondary mirror supporting seat is of a hollow truncated cone structure, and a through hole for mounting the secondary mirror is formed in the end face of the secondary mirror supporting seat;
one ends of the three supporting wings are fixedly arranged on the primary mirror supporting seat at equal intervals; the other ends of the three support wings are fixedly arranged on the secondary mirror support seat at equal intervals and are tangent to the conical surface of the secondary mirror support seat, and when viewed from the axial direction of the secondary mirror support seat, the tangent parts of the three support wings and the conical surface of the secondary mirror support seat form a small triangle which is also the edge of the secondary mirror support seat; the three reinforcing ribs are respectively arranged in the middle of the adjacent supporting wings.
2. The micro-deformed high-resonant-frequency primary and secondary mirror support of claim 1, wherein: the secondary mirror supporting seat is also provided with a lightening hole.
3. A micro-deformed high resonant frequency primary and secondary mirror mount as claimed in claim 1, further comprising: the primary mirror supporting seat, the secondary mirror supporting seat, the supporting wings and the reinforcing ribs are all made of metal materials or carbon fiber composite materials with low thermal expansion coefficients.
4. The micro-deformed high-resonant-frequency primary and secondary mirror support of claim 3, wherein: the primary mirror supporting seat, the secondary mirror supporting seat, the supporting wings and the reinforcing ribs are integrally formed by casting when made of metal materials with low thermal expansion coefficients.
5. The micro-deformed high-resonant-frequency primary and secondary mirror support according to any one of claims 1 to 4, wherein: the primary mirror supporting seat, the secondary mirror supporting seat, the supporting wings and the reinforcing ribs are all made of iron-nickel alloy.
6. The micro-deformed high-resonant-frequency primary and secondary mirror support of claim 5, wherein: the three reinforcing ribs are arranged on the same plane.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201710458209.6A CN107144935B (en) | 2017-06-16 | 2017-06-16 | Primary and secondary mirror support of high resonant frequency of micro-deformation |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201710458209.6A CN107144935B (en) | 2017-06-16 | 2017-06-16 | Primary and secondary mirror support of high resonant frequency of micro-deformation |
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| CN107144935A CN107144935A (en) | 2017-09-08 |
| CN107144935B true CN107144935B (en) | 2022-12-23 |
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