CN102902042A - Composite flexible support structure for large caliber reflector - Google Patents
Composite flexible support structure for large caliber reflector Download PDFInfo
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- CN102902042A CN102902042A CN2012104285523A CN201210428552A CN102902042A CN 102902042 A CN102902042 A CN 102902042A CN 2012104285523 A CN2012104285523 A CN 2012104285523A CN 201210428552 A CN201210428552 A CN 201210428552A CN 102902042 A CN102902042 A CN 102902042A
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Abstract
The invention discloses a composite flexible support structure for a large caliber reflector, relates to the technical field of space optical remote sensing, and solves the problem that the conventional single flexible support structure cannot ensure the surface shape accuracy of a reflector to influence the imaging quality of a space optical remote sensor. The composite flexible support structure comprises a small adhesive surface taper sleeve which is adhered with the reflector in a small area, and a composite flexible support rod connected with a back plate of the reflector, wherein the small adhesive surface taper sleeve is fixedly connected with the composite flexible support rod through screws; the composite flexible support rod is provided with two layers of flexible structures, namely L-shaped grooves and annular grooves; four L-shaped grooves are uniformly distributed along the axis of the composite flexible support rod, the front sections of the L-shaped grooves are parallel to the axis of the composite flexible support rod, and the back sections of the L-shaped grooves form an included angle of 60 degrees with the axis; and inner and outer annular grooves respectively consist of four sections of arc grooves which are uniformly distributed at the periphery and have the same width and radian. By two layers of flexible links, the surface shape accuracy of the reflector is improved and the imaging quality of the space optical remote sensor is ensured.
Description
Technical field
The present invention relates to the space optical remote technical field, be specifically related to a kind of composite and flexible supporting construction of large caliber reflecting mirror.
Background technology
Space optical remote sensor has important science and economic implications in the application in the fields such as observation, deep space probing over the ground.Large caliber reflecting mirror refers to clear aperature greater than the catoptron of 500mm, is most important optical element in the Optical Integrated Analysis of Space Remote Sensor system, and its surface figure accuracy is directly determining the image quality of space optical remote sensor.Because large caliber reflecting mirror minute surface size is large, Heavy Weight, the mirror physique heart relies on minute surface, and back-supported easily causes surface deformation, how to guarantee that therefore the surface figure accuracy of catoptron and the stability of raising face shape seem particularly important.
The supporting construction of large caliber reflecting mirror generally all adopts single flexible support structure, as shown in Figure 1, the single flexible support structure of large caliber reflecting mirror comprises with catoptron 1 and carries out the bonding tapered sleeve of gross area 3, tapered sleeve 3 outside surfaces mainly are comprised of bonding plane A, carry out gross area by bonding plane A and catoptron 1 bonding; The single flexible support bar 4 that is connected by screw with catoptron backboard 2; Have L shaped groove 5 on the single flexible support bar 4; Tapered sleeve 3 is connected by screw with single flexible support bar 4.Its shortcoming mainly contains three aspects: one, because the mirror body has sole mass, in the process that the conversion of gravity and microgravity state is arranged, single flexible support structure can not make the mirror body produce pure displacement, at the residual larger stress in the junction of minute surface and tapered sleeve 3, therefore the single flexible support structure distortion adaptive faculty that deadweight causes to the mirror body decreases; Two, can only guarantee that in ± 3 ℃ of temperature ranges the mirror shape precision does not change, when there is larger temperature variation in the residing space environment of space optical remote sensor (for example greater than ± 5 ℃), because the inconsistency of catoptron 1 and catoptron backboard 2 linear expansion coefficients, make catoptron 1 and the 2 flexible appearance of catoptron backboard inconsistent, and single flexible support structure is when offsetting thermal stress by distortion, can not discharge larger thermal stress fully and causes mirror shape to change; Three, the bonding way of tapered sleeve 3 is that gross area is bonding, and bonding plane A is extended near the minute surface always, because bonding agent exists remaining adhesive stress easily to cause surface deformation.The shortcoming of above-mentioned three aspects all can affect the surface figure accuracy of catoptron 1, thereby affects the image quality of space optical remote sensor, reduces the stability of mirror shape.
Summary of the invention
Can not guarantee that in order to solve existing single flexible support structure thereby the reflecting mirror surface shape precision affects the problem of space optical remote sensor image quality, the invention provides a kind of composite and flexible supporting construction of large caliber reflecting mirror.
The present invention is that the technical scheme that adopts of technical solution problem is as follows:
A kind of composite and flexible supporting construction of large caliber reflecting mirror comprises:
Carry out the bonding little bonding plane tapered sleeve of small size with catoptron by bonding agent, outside surface mainly is comprised of bonding plane B and empty knife face C;
The composite and flexible support bar that links to each other by screw with the catoptron backboard;
Described little bonding plane tapered sleeve and described composite and flexible support bar are fixedly linked by screw;
Be provided with L shaped groove and ring-shaped groove two sheets of flexible structure on the described composite and flexible support bar, 4 L shaped grooves evenly distribute along composite and flexible support bar axis, the leading portion of described L shaped groove is parallel with composite and flexible support bar axis, and back segment becomes 60 degree angles with composite and flexible support bar axis;
Described ring-shaped groove is comprised of diameter different inner ring groove and outer annular groove, and inner ring groove and outer annular groove form by 4 sections deep-slotted chip breakers along circumference uniform distribution, and the width of every section deep-slotted chip breaker is all identical with radian.
Described L shaped groove is uniform 4 of 90 degree along composite and flexible support bar axis interval, and two relative L shaped groove cut direction are identical, and two adjacent L shaped groove cut direction are opposite, and the back segment of L shaped groove becomes 60 to spend angles with composite and flexible support bar axis.
Described inner ring groove diameter is less than the outer annular groove diameter, described inner ring groove and outer annular groove form by four sections deep-slotted chip breakers, the width of every section deep-slotted chip breaker is identical, radian is 60 degree, be spaced apart 30 degree between adjacent two sections deep-slotted chip breakers, overlap 15 between one section deep-slotted chip breaker of inner ring groove and the end deep-slotted chip breaker of outer annular groove and spend.
Described little bonding plane tapered sleeve adopts the 4J32 material to make.
Described composite and flexible support bar adopts the TC4 material to make.
The invention has the beneficial effects as follows: composite and flexible supporting construction of the present invention, utilized the two sheets of flexible link, namely by the cooperation between L shaped groove and the ring-shaped groove, make large caliber reflecting mirror when gravity and temperature variation, the mirror body only produces parallel displacement and non-residual stress, make the mirror shape precision in wider temperature range, (± 15 ℃) keep stable, effectively strengthened the adaptability of large caliber reflecting mirror to erection stress and external environment; Then adopt a kind of small size bonding way for mirror body and little bonding plane tapered sleeve bonding, avoided to greatest extent bonding agent and bonding unrelieved stress on the impact of mirror shape, guaranteed the image quality of space optical remote sensor.
Description of drawings
Fig. 1 is the schematic diagram of single flexible support structure among Fig. 1;
Fig. 2 is the schematic diagram that the single flexible support structure of existing large caliber reflecting mirror is connected with catoptron, catoptron backboard;
Fig. 3 is the schematic diagram of the composite and flexible supporting construction of a kind of large caliber reflecting mirror of the present invention;
Fig. 4 is the structural representation of ring-shaped groove among the present invention;
Fig. 5 is the principle of work schematic diagram of composite and flexible supporting construction among Fig. 3.
Among the figure: 1, catoptron, 2, the catoptron backboard, 3, tapered sleeve, 4, single flexible support bar, 5, L shaped groove, 6, little bonding plane tapered sleeve, 7, the composite and flexible support bar, 8, inner ring groove, 9, outer annular groove.
Embodiment
Below in conjunction with accompanying drawing the present invention is described in further detail.
As shown in Figure 2, catoptron 1 and catoptron backboard 2 are connected in one by supporting construction, and catoptron 1 adopts the SiC material to make, diameter Ф 676mm, the thick 70mm in center, catoptron backboard 2 adopts the 4J32 material to make, and length * wide * height is 460mm * 400mm * 38mm.
As shown in Figure 3, the composite and flexible supporting construction of a kind of large caliber reflecting mirror of the present invention, mainly comprise little bonding plane tapered sleeve 6 and composite and flexible support bar 7, little bonding plane tapered sleeve 6 adopts the 4J32 material to make, diameter Ф 74mm, high 58mm, the outside surface of little bonding plane tapered sleeve 6 mainly is comprised of bonding plane B and empty knife face C, bonding plane B is the face of cylinder, height is 31.5mm, empty knife face C is the face of cylinder, and height is 26.5mm, and bonding plane B is arranged on the rear end of little bonding plane tapered sleeve 6, empty knife face C is arranged on the front end of little bonding plane tapered sleeve 6, it is bonding that bonding plane B carries out small size by bonding agent and catoptron 1, and bonding plane B is far away apart from minute surface, has reduced the impact of bonding agent unrelieved stress on mirror shape.
Composite and flexible support bar 7 is positioned at the inside of little bonding plane tapered sleeve 6, composite and flexible support bar 7 front ends are connected by screw and little bonding plane tapered sleeve 6 front ends are inner, composite and flexible support bar 7 rear ends are connected with catoptron backboard 2 by screw, composite and flexible support bar 7 adopts the TC4 material to make, with the joint face of catoptron backboard 2 be E face among Fig. 3, external diameter Ф 67mm, internal diameter Ф 43mm, screw hole distribution circle Ф 53mm, the joint face external diameter Ф 59mm of composite and flexible support bar 7 and little bonding plane tapered sleeve 6, internal diameter Ф 43mm, screw hole distribution circle Ф 28mm.
Have four L shaped grooves 5 that 1mm is wide on the composite and flexible support bar 7, four L shaped grooves 5 at interval, composite and flexible support bar 7 inner space 90 degree uniform, two relative L shaped groove 5 cut direction are identical, two adjacent L shaped groove 5 cut direction are opposite, the leading portion of four L shaped grooves 5 is all parallel with composite and flexible support bar 7 axis, parallel distance is 16mm, and the back segment of four L shaped grooves 5 all becomes 60 degree angles with composite and flexible support bar 7 axis, and rear segment length is greater than front segment length.
As shown in Figure 4, the front end of composite and flexible support bar 7 has by the inner ring groove 8 of staggered layout and the ring-shaped groove that outer annular groove 9 forms, inner ring groove 8 is different with the diameter of outer annular groove 9, inner ring groove 8 centerline diameter are Ф 37.5mm, outer annular groove 9 centerline diameter are Ф 41.5mm, inner ring groove 8 is comprised of four sections deep-slotted chip breakers, the width of every section deep-slotted chip breaker is 0.5mm, radian is 60 degree, be spaced apart 30 degree between adjacent two sections deep-slotted chip breakers, outer annular groove 9 also is comprised of four sections deep-slotted chip breakers, the width of every section deep-slotted chip breaker is 0.5mm, radian is 60 degree, is spaced apart 30 degree between adjacent two sections deep-slotted chip breakers, overlaps 15 between one section deep-slotted chip breaker of inner ring groove 8 and the end deep-slotted chip breaker of outer annular groove 9 and spends.
Above-mentioned all screws of using all adopt the TB3 material to make.
Above-mentioned 4J32 material and SiC material have close linear expansion coefficient.
As shown in Figure 5, when the gravity environment at space optical remote sensor place and temperature environment change, because the variation of gravity condition and the linear expansion coefficient of each component materials are inconsistent, mirror body and the mutual alignment between the catoptron backboard 2 that catoptron 1 can occur change, if catoptron backboard 2 is rigidity, then catoptron 1 relative catoptron backboard 2 will produce the trend that leans forward and move down, and single flexible support structure can not discharge the energy that its change in location causes, most of merit will be transformed into mirror body deformability energy, thereby cause the local gross distortion of minute surface, cause image quality to worsen, by composite and flexible supporting construction of the present invention, under the impact of gravity and temperature variation, catoptron 1 is subjected to displacement along parallel direction, discharge the deformation energy that change in location causes fully, residual stress not, in ± 15 ℃ of temperature ranges, make catoptron 1 mirror shape precision keep stable, then adopted a kind of small size bonding way to overcome adhesive stress that bonding location excessively closely causes apart from minute surface to the impact of mirror shape for mirror body and little bonding plane tapered sleeve 6 bonding.
Thoroughly clean all parts before the assembling, guarantee the free from dust foreign matter, assembly environment guarantees clean, at first, carry out the bonding of catoptron 1 and little bonding plane tapered sleeve 6: little bonding plane tapered sleeve 6 is repaiied with the supported hole of corresponding catoptron 1 ground and mark, epoxide-resin glue is evenly spread upon on the bonding plane B of little bonding plane tapered sleeve 6, and little bonding plane tapered sleeve 6 is bonded in the corresponding catoptron 1 respective support hole, the weight that loads 5kg weight at the D of little bonding plane tapered sleeve 6 face makes little bonding plane tapered sleeve 6 reliably contact with catoptron 1, and the operation instruction of pressing epoxide-resin glue keeps cure cycle naturally; Secondly, composite and flexible support bar 7 is assembled: three composite and flexible support bars 7 are installed in separately the little bonding plane tapered sleeve 6 according to 120 ° of normal distribution modes, and the screw gluing fixed, catoptron 1 is buckled on the platform, integral body is repaiied the E face that grinds three composite and flexible support bars 7, makes the E face of three composite and flexible support bars 7 coplanar, franchise 0.003mm, and parallel with the front end face of catoptron 1, franchise 0.005mm; At last, catoptron backboard 2 is assembled: catoptron backboard 2 is connected by screw on the E face of repairing three ground composite and flexible support bars 7, and screw is carried out gluing fix, whole assembling process is finished.Because catoptron 1 belongs to hard brittle material, when assembling and transportation, must handle with care.
Claims (5)
1. the composite and flexible supporting construction of a large caliber reflecting mirror is characterized in that, comprising:
Carry out the bonding little bonding plane tapered sleeve (6) of small size with catoptron (1) by bonding agent, outside surface mainly is comprised of bonding plane B and empty knife face C;
The composite and flexible support bar (7) that links to each other by screw with catoptron backboard (2);
Described little bonding plane tapered sleeve (6) is fixedly linked by screw with described composite and flexible support bar (7);
Be provided with L shaped groove (5) and ring-shaped groove two sheets of flexible structure on the described composite and flexible support bar (7), 4 L shaped grooves (5) evenly distribute along composite and flexible support bar (7) axis, the leading portion of described L shaped groove (5) is parallel with composite and flexible support bar (7) axis, and back segment becomes 60 degree angles with composite and flexible support bar (7) axis;
Described ring-shaped groove is comprised of the different inner ring groove of diameter (8) and outer annular groove (9), and inner ring groove (8) and outer annular groove (9) form by 4 sections deep-slotted chip breakers along circumference uniform distribution, and the width of every section deep-slotted chip breaker is all identical with radian.
2. the composite and flexible supporting construction of a kind of large caliber reflecting mirror according to claim 1, it is characterized in that, described L shaped groove (5) along composite and flexible support bar (7) axis interval 90 the degree uniform 4, relative two L shaped grooves (5) cut direction is identical, adjacent two L shaped grooves (5) cut direction is opposite, and the back segment of L shaped groove (5) becomes 60 degree angles with composite and flexible support bar (7) axis.
3. the composite and flexible supporting construction of a kind of large caliber reflecting mirror according to claim 1, it is characterized in that, described inner ring groove (8) diameter is less than outer annular groove (9) diameter, described inner ring groove (8) and outer annular groove (9) form by four sections deep-slotted chip breakers, the width of every section deep-slotted chip breaker is identical, radian is 60 degree, be spaced apart 30 degree between adjacent two sections deep-slotted chip breakers, overlap 15 between one section deep-slotted chip breaker of inner ring groove (8) and the end deep-slotted chip breaker of outer annular groove (9) and spend.
4. the composite and flexible supporting construction of a kind of large caliber reflecting mirror according to claim 1 is characterized in that, described little bonding plane tapered sleeve (6) adopts the 4J32 material to make.
5. the composite and flexible supporting construction of a kind of large caliber reflecting mirror according to claim 1 is characterized in that, described composite and flexible support bar (7) adopts the TC4 material to make.
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| CN2012104285523A CN102902042A (en) | 2012-10-31 | 2012-10-31 | Composite flexible support structure for large caliber reflector |
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| CN2012104285523A CN102902042A (en) | 2012-10-31 | 2012-10-31 | Composite flexible support structure for large caliber reflector |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104267481A (en) * | 2014-10-23 | 2015-01-07 | 中国工程物理研究院总体工程研究所 | Back supporting device for large-caliber reflector |
| CN104280858A (en) * | 2014-10-23 | 2015-01-14 | 中国工程物理研究院总体工程研究所 | Flexible back supporting device for large-caliber reflector |
| CN104570318A (en) * | 2014-11-24 | 2015-04-29 | 中国科学院国家天文台南京天文光学技术研究所 | Ball-type ultralow-temperature mirror surface side supporting mechanism for astronomical telescope |
| CN106443959A (en) * | 2016-12-07 | 2017-02-22 | 中国科学院长春光学精密机械与物理研究所 | Split type bi-material flexible mechanism of space-based large-calibre high-facial-contour-precision reflector assembly |
| CN106772884A (en) * | 2016-12-21 | 2017-05-31 | 北京空间机电研究所 | A kind of low-temperature lens compress release type and disappear thermal stress supporting construction |
| CN107656367A (en) * | 2017-10-13 | 2018-02-02 | 中国科学院上海技术物理研究所 | A kind of scanning mirror assembly for spaceborne sweep mechanism |
| CN109799594A (en) * | 2019-03-21 | 2019-05-24 | 长光卫星技术有限公司 | A kind of flexible mandrel for eliminating large caliber reflecting mirror adhesive stress |
| CN110716279A (en) * | 2019-11-09 | 2020-01-21 | 季华实验室 | Flexible aluminum reflector |
| CN111258025A (en) * | 2020-02-28 | 2020-06-09 | 中国科学院西安光学精密机械研究所 | Large-diameter reflector supporting device |
| CN111522122A (en) * | 2020-05-27 | 2020-08-11 | 长光卫星技术有限公司 | Rigid heat dissipation device for medium and small-caliber space reflector |
| CN109932805B (en) * | 2019-03-04 | 2021-06-01 | 杭州电子科技大学 | Adaptive supporting method for large-aperture reflector |
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| CN102096172A (en) * | 2011-01-18 | 2011-06-15 | 中国科学院长春光学精密机械与物理研究所 | Back flexible supporting structure for reflecting mirror of space remote sensor |
| CN102109657A (en) * | 2011-02-25 | 2011-06-29 | 中国科学院长春光学精密机械与物理研究所 | Ball hinge support structure of large caliber reflector of space remote sensor |
| CN102508348A (en) * | 2011-11-09 | 2012-06-20 | 中国科学院长春光学精密机械与物理研究所 | Spatial flexible filter supporting mechanism and method for mounting filter |
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Patent Citations (3)
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| CN102096172A (en) * | 2011-01-18 | 2011-06-15 | 中国科学院长春光学精密机械与物理研究所 | Back flexible supporting structure for reflecting mirror of space remote sensor |
| CN102109657A (en) * | 2011-02-25 | 2011-06-29 | 中国科学院长春光学精密机械与物理研究所 | Ball hinge support structure of large caliber reflector of space remote sensor |
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Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104267481A (en) * | 2014-10-23 | 2015-01-07 | 中国工程物理研究院总体工程研究所 | Back supporting device for large-caliber reflector |
| CN104280858A (en) * | 2014-10-23 | 2015-01-14 | 中国工程物理研究院总体工程研究所 | Flexible back supporting device for large-caliber reflector |
| CN104267481B (en) * | 2014-10-23 | 2016-08-24 | 中国工程物理研究院总体工程研究所 | A kind of large caliber reflecting mirror back support device |
| CN104570318A (en) * | 2014-11-24 | 2015-04-29 | 中国科学院国家天文台南京天文光学技术研究所 | Ball-type ultralow-temperature mirror surface side supporting mechanism for astronomical telescope |
| CN104570318B (en) * | 2014-11-24 | 2016-11-09 | 中国科学院国家天文台南京天文光学技术研究所 | The ball-type ultralow temperature mirrored sides supporting device of astronomical telescope |
| CN106443959A (en) * | 2016-12-07 | 2017-02-22 | 中国科学院长春光学精密机械与物理研究所 | Split type bi-material flexible mechanism of space-based large-calibre high-facial-contour-precision reflector assembly |
| CN106772884A (en) * | 2016-12-21 | 2017-05-31 | 北京空间机电研究所 | A kind of low-temperature lens compress release type and disappear thermal stress supporting construction |
| CN106772884B (en) * | 2016-12-21 | 2019-01-25 | 北京空间机电研究所 | A kind of low-temperature lens compress release type and disappear thermal stress support construction |
| CN107656367A (en) * | 2017-10-13 | 2018-02-02 | 中国科学院上海技术物理研究所 | A kind of scanning mirror assembly for spaceborne sweep mechanism |
| CN107656367B (en) * | 2017-10-13 | 2022-12-30 | 中国科学院上海技术物理研究所 | Scanning mirror assembly for satellite-borne scanning mechanism |
| CN109932805B (en) * | 2019-03-04 | 2021-06-01 | 杭州电子科技大学 | Adaptive supporting method for large-aperture reflector |
| CN109799594A (en) * | 2019-03-21 | 2019-05-24 | 长光卫星技术有限公司 | A kind of flexible mandrel for eliminating large caliber reflecting mirror adhesive stress |
| CN110716279A (en) * | 2019-11-09 | 2020-01-21 | 季华实验室 | Flexible aluminum reflector |
| CN111258025A (en) * | 2020-02-28 | 2020-06-09 | 中国科学院西安光学精密机械研究所 | Large-diameter reflector supporting device |
| CN111522122A (en) * | 2020-05-27 | 2020-08-11 | 长光卫星技术有限公司 | Rigid heat dissipation device for medium and small-caliber space reflector |
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Application publication date: 20130130 |