CN204086650U - Secondary mirror support structure of space camera - Google Patents
Secondary mirror support structure of space camera Download PDFInfo
- Publication number
- CN204086650U CN204086650U CN201420546984.9U CN201420546984U CN204086650U CN 204086650 U CN204086650 U CN 204086650U CN 201420546984 U CN201420546984 U CN 201420546984U CN 204086650 U CN204086650 U CN 204086650U
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- China
- Prior art keywords
- circle cylinder
- outer shroud
- secondary mirror
- metal insert
- inner ring
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- Expired - Lifetime
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- 239000002184 metal Substances 0.000 claims abstract description 51
- 210000003205 muscle Anatomy 0.000 claims abstract description 26
- 239000002131 composite material Substances 0.000 claims abstract description 13
- 239000000835 fiber Substances 0.000 claims abstract description 11
- 238000004804 winding Methods 0.000 claims abstract description 7
- 238000000034 method Methods 0.000 claims abstract description 6
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 8
- 229910052799 carbon Inorganic materials 0.000 claims description 8
- 230000013011 mating Effects 0.000 claims description 4
- 238000000465 moulding Methods 0.000 claims description 3
- 230000003014 reinforcing effect Effects 0.000 claims description 2
- 239000000463 material Substances 0.000 abstract description 6
- 230000003287 optical effect Effects 0.000 description 5
- 238000010586 diagram Methods 0.000 description 4
- 230000002787 reinforcement Effects 0.000 description 4
- 239000000126 substance Substances 0.000 description 4
- 229920000049 Carbon (fiber) Polymers 0.000 description 3
- 239000004917 carbon fiber Substances 0.000 description 3
- 150000001875 compounds Chemical class 0.000 description 3
- 238000010276 construction Methods 0.000 description 3
- 239000003292 glue Substances 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 239000004593 Epoxy Substances 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- -1 carbon fiber compound Chemical class 0.000 description 1
- 238000013016 damping Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000003822 epoxy resin Substances 0.000 description 1
- 239000002360 explosive Substances 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 229920000647 polyepoxide Polymers 0.000 description 1
- 229920013657 polymer matrix composite Polymers 0.000 description 1
- 239000011160 polymer matrix composite Substances 0.000 description 1
- 238000007363 ring formation reaction Methods 0.000 description 1
- 238000007711 solidification Methods 0.000 description 1
- 230000008023 solidification Effects 0.000 description 1
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- Telescopes (AREA)
Abstract
The utility model provides a space camera secondary mirror supporting structure, including secondary mirror support, metal insert and metal flange, secondary mirror support is including inner ring, the outer loop that sets up with one heart, connect through many tangential muscle of equipartition between inner ring and the outer loop, the outer loop is carbon-fibre composite laminated board structure, and the inner ring uses the metal insert to twine as the dabber by carbon-fibre composite preimpregnation material and forms, carries out the winding in-process of last round and splits the preimpregnation material in the thickness direction, and every divides a branch of preimpregnation material through the equant point of an inner ring, and the tip and the outer loop of the preimpregnation material of dividing are connected and are formed the tangential muscle. The utility model solves the contradiction between high rigidity and light weight; meanwhile, a method of winding and laying prepreg by taking the metal insert as a mandrel and curing the metal insert and the composite material together is adopted, so that the problem of firm assembly of the metal insert and the composite material secondary mirror support is solved.
Description
Technical field
The utility model relates to a kind of space camera secondary mirror supporting structure.
Background technology
Long-focus High Resolution Space Camera extensively adopts three-mirror reflection optical system, and the interval between primary and secondary mirror is very large, and the image quality impact of variation on camera of its relative position is very large.Added the type of attachment of time mirror support between usual primary mirror assembly and secondary mirror assembly by main support tube, existing time mirror support mostly is metal construction, there is the technical matterss such as weight is large, the ratio of obstruction is high, thermal adaptability is poor.
Utility model content
The utility model proposes a kind of secondary mirror supporting structure based on carbon fibre composite, high specific stiffness, little requirement of blocking when good thermal adaptability can be met.
Technical solution of the present utility model is:
A kind of space camera secondary mirror supporting structure, comprises time mirror support, metal insert and metal flange, and described time mirror support comprises the inner ring, the outer shroud that arrange with one heart, and connected by uniform many tangential muscle between described inner ring and outer shroud, its special character is:
Described outer shroud is carbon fibre laminate composites structure, described inner ring is that mandrel is wound by carbon fibre composite prepreg with metal insert, in the process of carrying out last lap winding, at thickness direction, beam splitting is carried out to prepreg, Along ent often through an inner ring separates a branch of prepreg, and the end of the prepreg separated and outer shroud are connected to form described tangential muscle.
Above-mentioned mirror support also comprises and thickeies circle, and the described circle that thickeies to be laid along the opposite sides of two adjacent tangential muscle and the outer shroud inwall pitch of the laps be clipped between two tangential muscle by carbon fibre composite prepreg and formed.
Above-mentioned outer shroud also comprises the outside flange arranged along outer shroud both sides radial direction, and the flange of both sides and the outer circumference surface of outer shroud form ring groove;
Described outer shroud also comprises annularly trench bottom circumference and end to end multiple box-like structures, described box-like structure comprises bottom surface, is arranged on the left surface of the left and right sides, bottom surface and right flank, the leading flank being arranged on both sides before and after bottom surface and trailing flank, described bottom surface and annular groove bottom suitable, described left surface and right flank and outer shroud flange suitable, described leading flank and trailing flank are arranged along the radial direction of outer shroud, and the flange of multiple box-like structure and both sides forms reinforcing rib structure jointly.
The external cylindrical surface of above-mentioned metal insert comprises two terminal circle cylinder and is clipped in the middle circle cylinder between two terminal circle cylinder, and the external diameter of two terminal circle cylinder is identical and be greater than the external diameter of middle circle cylinder, and described middle circle cylinder is the winding face of inner ring when being formed.
What above-mentioned middle circle cylinder was arranged has the uniform multiple circumferential groove in densely covered interval.
The inner cylinder face of above-mentioned metal insert also comprises two terminal circle cylinder and is clipped in the middle circle cylinder between two terminal circle cylinder, the internal diameter of two terminal circle cylinder is identical and be less than the internal diameter of middle circle cylinder, this two terminal circle cylinder is the mating surface with secondary microscope base, and this two terminal circle cylinder is provided with vertically symmetrical groove.
Above-mentioned mirror support 1 and metal insert 2 integral heat pressure curing molding.
The xsect l-shaped of above-mentioned metal flange, the end face of L shape structure and external cylindrical surface coordinate with the end face of main support tube and inner cylinder face respectively.
Carry out fastening with screw again after cementing between above-mentioned metal flange and outer shroud.
Compared with prior art, advantage is the utility model:
1, the utility model adopts high modulus carbon fiber compound substance, solves the contradiction between high rigidity and lightweight; Adopt with metal insert is that mandrel is wound around and lays prepreg the method that metal insert is solidified together with compound substance simultaneously, solves the problem that metal insert firmly assembles with the secondary mirror support of compound substance; In addition, tangential muscle structure and carbon fibre material improve the thermal adaptability of time mirror element.
2, be connected by cementing and the two kinds of modes that are spirally connected between the utility model metal flange with compound substance time mirror support, connect assured uniform.
3, the utility model adopts and closes the problem that box-like structure structure reinforcement solves traditional reinforcement strength of joint and insufficient rigidity; Specific direction rigidity and strengthened problem is solved by composite plys design optimization;
4, optics blocks little: optimize four tangential muscle along the height of optical axis direction with the thickness of four muscle achieves high rigidity and little optics blocks.
Accompanying drawing explanation
Fig. 1 is one-piece construction schematic diagram of the present utility model;
Fig. 2 is the explosive view of Fig. 1;
Fig. 3 the utility model time mirror support schematic diagram;
Fig. 4 is the utility model metal insert structural representation;
Fig. 5 is the front view of the utility model metal flange;
Fig. 6 is the cut-open view of the utility model metal flange;
Fig. 7 is the connection diagram of the utility model time mirror support and main support tube;
Fig. 8 is the partial sectional view of Fig. 7;
Fig. 9 is the utility model time mirror support and time mirror assembly connection diagram;
Figure 10 is the partial sectional view of Fig. 9;
Wherein Reference numeral is: 1-mirror support, 11-inner ring, 12-outer shroud, the tangential muscle of 13-, 15-flange, 16-box-like structure, 2-metal insert, 21-circumferential groove, 22-groove, 3-metal flange, 4-mirror assembly, 41-microscope base, 42-secondary mirror, 43-secondary mirror light shield.
Embodiment
The utility model comprises time mirror support 1, metal insert 2 and metal flange 3, secondary mirror support 1 is laid by high modulus carbon fiber reinforced epoxy based composites laminate and is formed, in laying process, utilize different moulds to form different structures, finally fit together, inhale glue, enter solidification of hot-press tank.The material selection high modulus carbon fiber of secondary mirror support 1 strengthens polymer matrix composites and makes, solve the contradiction between high rigidity and lightweight, meanwhile, there is high damping, the programmable feature of thermal expansivity, there is good vibration suppressioning effect and temperature stability in space environment.
Secondary mirror support in the utility model comprises inner ring 11, outer shroud 12 and the tangential muscle 13 between inner ring and outer shroud, inner ring is for mandrel is wound with metal insert 2, the prepreg of drawing from inner ring forms the tangential muscle of four wings, when variation of ambient temperature causes the length variations of four muscle, inner ring can be rotated around secondary mirror optical axis, little on image quality impact; In order to meet the thickness requirement of the tangential muscle of four wings and the design size requirement of inner ring and outer shroud, stiffening ring can be laid along the opposite sides of two adjacent tangential muscle and the outer shroud inwall pitch of the laps be clipped between two tangential muscle; Meanwhile, multilayer prepreg and the outer shroud of four muscle can overlap different length, and the seam that forming position is different, reduces the risk that seam crossing destroys.In addition, the utility model is optimized along the height of optical axis direction and the thickness of muscle the tangential muscle of four wings, realizes high rigidity and little optics blocks; The fiber lay down number of plies amount along the length direction of muscle in the tangential muscle of four wings can be increased, to increase the strength and stiffness of the length direction along muscle when Lay up design.
Further, the outer shroud of the utility model time mirror support 1 is flange 15 structure, and there are 12 box-like structures 16 inside; The flange of 12 box-like structures and outer shroud forms multiple reinforcement jointly, solves a difficult problem for traditional reinforcement strength of joint and insufficient rigidity.
Further, the outside surface of metal insert 2 of the present utility model comprises two terminal circle cylinder and is clipped in the middle circle cylinder between two terminal circle cylinder, the external diameter of two terminal circle cylinder is identical and be greater than the external diameter of middle circle cylinder, winding face when middle circle cylinder is inner ring formation, and middle circle cylinder is provided with the uniform multiple circumferential groove 21 in densely covered interval, the design of this structure on the one hand can by means of the face of cylinder at two ends as positioning datum when inner ring is formed, and the circumferential groove of gathering on the other hand increases the adhesion of prepreg and metal insert.
In addition, the inner cylinder face of the utility model metal insert also comprises two terminal circle cylinder and is clipped in the middle circle cylinder between two terminal circle cylinder, the internal diameter of two terminal circle cylinder is identical and be less than the internal diameter of middle circle cylinder, this two terminal circle cylinder is the mating surface with secondary microscope base, and this two terminal circle cylinder is provided with vertically symmetrical groove 22.Metal insert 2 only coordinates at two terminal circle cylinder with time microscope base 41, this construction reduces the length coordinating the face of cylinder, improves quality of fit, the axial groove that two terminal circle cylinder is processed, and kills when preventing from assembling between metal insert 2 and secondary mirror assembly.
Further, the utility model is processed with multiple circumferential groove at metal insert 2 and the mating surface of inner ring, enhances secondary connection reliability between mirror support 1 and metal insert 2.
Carrying out a step, of the present utility model mirror support 1 together with metal insert 2 in autoclave integral heat pressure curing molding, add the consistance of structure.
Finally, metal flange 3 of the present utility model is connected with time mirror support 1 by epoxide-resin glue and 12 attachment screws, ensure that strength of joint and connects homogeneity; Metal flange 3 section is L shape, and the end face of L shape structure and external cylindrical surface coordinate with the end face of main support tube and inner cylinder face respectively.After metal insert 2, metal flange 3 have all been connected with time mirror support 1, finishing is carried out to the two terminal circle cylinder that metal insert 2 coordinates with time mirror assembly, obtained the high quality of fit with time microscope base; Semi-finishing is carried out with the end face metal insert 2 after finishing coordinating the face of cylinder coordinate with main support tube metal flange 3 for benchmark with secondary mirror assembly and the face of cylinder when being unkitted time microscope base; After secondary mirror assembly 4 and time mirror support 1 have assembled, metal flange 3 when secondary mirror support and main support tube assemble with secondary mirror 42 optical axis for benchmark carries out high-precision aligning processing to counterface and the face of cylinder, thus the high precision realizing time mirror support and main support tube is assembled.
Claims (9)
1. a space camera secondary mirror supporting structure, comprises time mirror support, metal insert and metal flange, and described time mirror support comprises the inner ring, the outer shroud that arrange with one heart, is connected, it is characterized in that between described inner ring and outer shroud by uniform many tangential muscle:
Described outer shroud is carbon fibre laminate composites structure, described inner ring is that mandrel is wound by carbon fibre composite prepreg with metal insert, in the process of carrying out last lap winding, at thickness direction, beam splitting is carried out to prepreg, Along ent often through an inner ring separates a branch of prepreg, and the end of the prepreg separated and outer shroud are connected to form described tangential muscle.
2. space camera secondary mirror supporting structure according to claim 1, it is characterized in that: described mirror support also comprises and thicken circle, the described circle that thickeies to be laid along the opposite sides of two adjacent tangential muscle and the outer shroud inwall pitch of the laps be clipped between two tangential muscle by carbon fibre composite prepreg and is formed.
3. space camera secondary mirror supporting structure according to claim 1 and 2, is characterized in that: described outer shroud also comprises the outside flange arranged along outer shroud both sides radial direction, and the flange of both sides and the outer circumference surface of outer shroud form ring groove;
Described outer shroud also comprises annularly trench bottom circumference and end to end multiple box-like structures, described box-like structure comprises bottom surface, is arranged on the left surface of the left and right sides, bottom surface and right flank, the leading flank being arranged on both sides before and after bottom surface and trailing flank, described bottom surface and annular groove bottom suitable, described left surface and right flank and outer shroud flange suitable, described leading flank and trailing flank are arranged along the radial direction of outer shroud, and the flange of multiple box-like structure and both sides forms reinforcing rib structure jointly.
4. space camera secondary mirror supporting structure according to claim 3, it is characterized in that: the external cylindrical surface of described metal insert comprises two terminal circle cylinder and is clipped in the middle circle cylinder between two terminal circle cylinder, the external diameter of two terminal circle cylinder is identical and be greater than the external diameter of middle circle cylinder, and described middle circle cylinder is the winding face of inner ring when being formed.
5. space camera secondary mirror supporting structure according to claim 4, is characterized in that: what described middle circle cylinder was arranged has the uniform multiple circumferential groove in densely covered interval.
6. space camera secondary mirror supporting structure according to claim 5, it is characterized in that: the inner cylinder face of described metal insert also comprises two terminal circle cylinder and is clipped in the middle circle cylinder between two terminal circle cylinder, the internal diameter of two terminal circle cylinder is identical and be less than the internal diameter of middle circle cylinder, this two terminal circle cylinder is the mating surface with secondary microscope base, and this two terminal circle cylinder is provided with vertically symmetrical groove.
7. space camera secondary mirror supporting structure according to claim 6, is characterized in that:
Described mirror support and metal insert integral heat pressure curing molding.
8. space camera secondary mirror supporting structure according to claim 7, is characterized in that: the xsect l-shaped of described metal flange, and the end face of L shape structure and external cylindrical surface coordinate with the end face of main support tube and inner cylinder face respectively.
9. space camera secondary mirror supporting structure according to claim 8, is characterized in that: carry out fastening with screw again after cementing between described metal flange and outer shroud.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420546984.9U CN204086650U (en) | 2014-09-22 | 2014-09-22 | Secondary mirror support structure of space camera |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420546984.9U CN204086650U (en) | 2014-09-22 | 2014-09-22 | Secondary mirror support structure of space camera |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204086650U true CN204086650U (en) | 2015-01-07 |
Family
ID=52179350
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420546984.9U Expired - Lifetime CN204086650U (en) | 2014-09-22 | 2014-09-22 | Secondary mirror support structure of space camera |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204086650U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104267479A (en) * | 2014-09-22 | 2015-01-07 | 中国科学院西安光学精密机械研究所 | Secondary mirror support structure of space camera |
-
2014
- 2014-09-22 CN CN201420546984.9U patent/CN204086650U/en not_active Expired - Lifetime
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104267479A (en) * | 2014-09-22 | 2015-01-07 | 中国科学院西安光学精密机械研究所 | Secondary mirror support structure of space camera |
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| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |