CN102109657B - Ball hinge support structure of large caliber reflector of space remote sensor - Google Patents
Ball hinge support structure of large caliber reflector of space remote sensor Download PDFInfo
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- CN102109657B CN102109657B CN2011100462666A CN201110046266A CN102109657B CN 102109657 B CN102109657 B CN 102109657B CN 2011100462666 A CN2011100462666 A CN 2011100462666A CN 201110046266 A CN201110046266 A CN 201110046266A CN 102109657 B CN102109657 B CN 102109657B
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Abstract
A ball hinge support structure of a large caliber reflector of a space remote sensor belongs to the technical field of space remote sensors, relates to a ball hinge support structure, and aims to provide the ball hinge support structure of the large caliber reflector of the space remote sensor. The invention adopts the technical scheme that the ball hinge support structure comprises a connecting flange, an upper bearing support, a lower bearing support, a ball rod, a ball rod grooves, cylindrical pins, a taper sleeve, a reflecting mirror, a back panel, and the like, wherein an end of the ball hinge adjacent to the flange is a cylinder-shaped structure; four grooves are formed on the ball rod at intervals; a ball head at the other end of the ball rod is a spherical cavity; the rod end of the ball rod is connected with the flange through a screw and the cylindrical pin; the flange is connected with the back panel through a screw; the upper bearing support, the ball head of the ball rod and the lower bearing support are assembled together through a screw and the cylindrical pin; the upper bearing support is connected with the taper sleeve through a screw; and glue is used for gluing the taper sleeve and the reflecting mirror. By the adoption of the ball hinge support structure, the temperature stress and the assembly stress caused by different linear expansion coefficients of materials are unloaded, the vibration is reduced, and the reflecting mirror shape accuracy and the imaging quality are ensured.
Description
Technical field:
The invention belongs to the space remote sensing technical field, the supporting construction of a kind of Space Remote Sensors large-aperture optical catoptron that relates to.
Background technology:
Space Remote Sensors is used for the earth and space resources is generally investigated and detailed survey, has important science and economic implications in the application in fields such as observation, deep space probing over the ground.Optical element in the Space Remote Sensors particularly large caliber reflecting mirror is most important parts in the whole optical system, and its surface figure accuracy just is directly connected to the quality of whole remote sensor image quality.At optics circle, usually the call heavy caliber of clear aperature, because the minute surface size is big, Heavy Weight usually causes that minute surface produces distortion greater than 600mm.The quality of surface figure accuracy and the supporting construction of catoptron have very big relation, and good supporting construction can make the surface figure accuracy of catoptron better, and stability is better.
The present invention in the past; Homogeneous structure generally all adopts or the gentle head more than 3 to carry out back support at 3; With the most approaching prior art of the present invention be the optical mirror supporting construction of the Space Remote Sensors developed of Changchun Institute of Optics, Fine Mechanics and Physics, CAS; As shown in Figure 1, comprise backboard 1, first screw 2, gentle 3, tapered sleeve 4, second screw 5, catoptron 6.Pass through first screw 2 for gentle 3 and be connected with backboard 1, gentle 3 the other end is connected with tapered sleeve 4 through second attachment screw 5, and tapered sleeve 4 sticks with glue with catoptron 6 and connects.This supporting way can guarantee that through the groove of processing some and form on gentle 3 gentle head has suitable flexibility.The relative merits of this structure are: when camera bears vibration; Gentle head can absorb the effect that energy plays vibration damping, but when there is temperature variation in the residing space environment of remote sensor, because the inconsistency of catoptron and propping material linear expansion coefficient; Even gentle head has certain flexibility; Catoptron still can receive very big stress, and the assembling of this structure is very difficult besides, has deviation will have very big erection stress slightly and produces; Can have a strong impact on the face shape of catoptron like this, influence image quality.
Summary of the invention:
In order to overcome the defective that prior art exists; The objective of the invention is to propose a kind of effective support mode, guarantee that the catoptron of remote sensor can bear the oscillating load of certain magnitude, during space temperature environmental change simultaneously; This kind supporting way can not cause mirror mirror face shape to change because of temperature variation; Because the existence of ball pivot can well be eliminated erection stress in this structure, assembling realizes easily, thus the image quality of assurance remote sensor.
The technical matters that the present invention will solve is: a kind of Space Remote Sensors large-aperture optical reflecting mirror support structure is provided.The technical scheme of technical solution problem is as shown in Figure 2, comprising: catoptron 7, backboard 8, catoptron supporting component 9, mirror assembly reconditioning pad 10, supporting component over cap 11, first screw 12, second screw 13, the 3rd screw 14, tapered sleeve 15; Wherein, the structure of mirror assembly 9 such as Fig. 3, Fig. 4, shown in Figure 5 comprise: groove 16, joint flange 17, the 4th screw 18, top chock 19, club 20, step 21, the 5th screw 22, first straight pin 23, second straight pin 24; Club 20 is columnar structured near an end of joint flange 17; Around the club wall, have the 90o distribution at interval on club of 16, four grooves of four grooves, relative groove cut direction is identical; The adjacent grooves cut direction is opposite; Groove can increase flexibility, plays damping effect, and the other end bulb of club 20 is spherical hollow spaces; Joint flange 17 is connected with backboard 8 through first screw 12 in catoptron supporting component 9; Joint flange 17 is connected with tapered sleeve 15 through second screw 13 simultaneously; Top chock 19 is a clearance fit with the surface of contact C of tapered sleeve 15; Tapered sleeve 15 is gluing with catoptron 7; The bulb of top chock 19, club 20 and step 21 are assembled together by shown in Figure 3 through the 5th screw 22 and second straight pin 24, and the rod end of club 20 links together with joint flange 17 through the 4th screw 18, first straight pin 23; Supporting component over cap 11 is fixed on the backboard 8 through the 3rd screw 14, prevents that dust from falling in the cavity of club 20.Mirror assembly reconditioning pad 10 has 3; Become 120o to distribute; When being fitted on the mirror assembly integral installation in the remote sensing camera framework; Can guarantee the Design for optical system index request through its thickness of reconditioning and angle, catoptron reconditioning pad 10 is pressed between remote sensing camera framework and the backboard 8 through the attachment screw between remote sensor phase machine frame and the backboard 8.
Principle of work explanation: when the space environment temperature variation, because the inconsistency of the linear expansion coefficient of material can produce the relative motion of supporting with catoptron; If be supported for rigid support, then the major part of this part merit will be transformed into mirror body deformability ability, thereby cause the severe local distortion of minute surface; Cause image quality to worsen, in this supporting construction, adopted ball pivot, allowing has micro-relative motion between support and the mirror body; Can be with this part deformation energy unloading, with the minute surface face shape that guarantees; Have four grooves 16 that 1mm is wide on the club 20; Four grooves interval 90 degree on club are uniformly distributed with, and relative groove cut direction is identical, and the adjacent trenches cut direction is opposite; They can play the excellent vibration damping effect; Simultaneously can eliminate the part erection stress, during temperature variation, because the inconsistent stress that causes of line of material expansion coefficient also can be eliminated a part.
Good effect of the present invention: the existence of ball pivot, can avoid the generation of erection stress, the assembling of mirror assembly is realized more easily; On club 20, have four grooves 16; Energy in the time of can absorbed oscillation plays the excellent vibration damping effect, makes catoptron can bear more high-magnitude, worse vibration; In the time of simultaneously can eliminating part erection stress and temperature variation, because the inconsistent stress that causes of line of material expansion coefficient.The existence of two characteristics can make mirror assembly stand worse environment and better meet mission requirements.
Description of drawings:
Fig. 1 is the synoptic diagram of prior art large caliber reflecting mirror supporting construction;
Fig. 2 is the general illustration of large caliber reflecting mirror ball pivot supporting construction among the present invention;
Fig. 3 is the structural front view of large caliber reflecting mirror supporting component among the present invention;
Fig. 4 is the left view of Fig. 3;
Fig. 5 is the right view of Fig. 3;
Fig. 6 is the combiner front view of upper and lower bearing seat in the embodiment;
Fig. 7 is the combiner right view of upper and lower bearing seat in the embodiment.
Embodiment:
The present invention implements by structure shown in Figure 2.Wherein, catoptron supporting component 9 is pressed Fig. 3, Fig. 4 and structure enforcement shown in Figure 5.
Wherein, primary mirror 7 adopts the SiC material to process, and is of a size of diameter of phi 676mm, thick 99.7mm.Backboard 8 adopts the 4J32 material to process, and is of a size of 402x461x38mm.Mirror assembly is repaiied and is ground pad 10 and adopt the 4J32 materials to process, and is of a size of 151x90x2mm.Over cap 11 adopts the 2A12 material to process, and is of a size of diameter of phi 72mm, thick 1mm.The 3rd screw 14 adopts 30CrMnsi to process.First screw 12, second screw 13 adopt the TB3 materials to process.Tapered sleeve 15 adopts the 4J32 material to process, and is of a size of diameter of phi 79mm, high 58mm.Joint flange 17 adopts the 4J32 material to process, and is of a size of diameter of phi 82mm, high 18mm.First straight pin 23 and second straight pin 24 adopt the TC4 material to process.Top chock 19 adopts the 4J32 material to process, and outer profile size is largest diameter 78mm, maximum height 41.5mm.Club 20 adopts the 4J32 material to process, and outer profile size is largest diameter 39mm, maximum height 54.5mm.Step 21 adopts the 4J32 material to process, and outer profile size is largest diameter 60mm, maximum height 14mm.The 4th screw 18 and the 5th screw 22 adopt the TB3 material to process, and 4J32 material and catoptron SIC material have close linear expansion coefficient.
Thoroughly clean all parts before the assembling; Guarantee inclusion-free; It is clean that assembly environment is wanted, the assembling of catoptron supporting component 9: corresponding tapered sleeve, bearing seat and club will be beaten with mark before the facing-up, allow to use a small amount of MoS2 railway grease during assembling; Part 19,21 is installed the back facing-up with part 20, guarantee that the D face has the 0.001-0.003mm gap.Catoptron supporting component 9 is after mirror mirror roughing, to assemble with catoptron, confirms at first that before assembling the catoptron taper hole machines, and has passed through facing-up with tapered sleeve in the catoptron supporting component; Tapered sleeve 15 is sticked in catoptron 7 taper holes with the appointment bonding agent by mark; Guarantee solid and reliablely, the mating surface C of attention reflex mirror supporting component 9 and tapered sleeve 15 wants facing-up, guarantees the 0.001-0.003mm gap; After the installation of catoptron supporting component; Backboard 8 is installed, can be made three catoptron supporting components satisfy equation of equal altitude 0.003mm requirement, thereby guarantee the coplanarity (franchise 0.005mm) of backboard B face through the A end face of repairing the catoptron supporting component; After the assembled; Detection faces shape is broken pin in the relevant position after satisfying the optics requirement, because catoptron belongs to hard brittle material, in assembling and transportation, must handle with care.
Fig. 6 and Fig. 7 are combiner figure, comprising: step 21, top chock 19, the 5th screw 22, second straight pin 24.Directly influence the support effect of supporting component owing to the club and the quality that cooperates of metal (upper seat; So the Internal Spherical Surface that adopts combination to process the metal (upper seat guarantees that two hemispherical centre ofs sphere are concentric, two end face E of metal (upper seat guarantee flatness 0.003mm before the combination; The verticality 0.005mm of relative two part axis of symmetry; Then facing-up is carried out in the club combination, this mode can guarantee quality of fit, guarantees that surface of contact has the gap value of 0.001-0.003mm.
Claims (1)
1. a Space Remote Sensors large caliber reflecting mirror ball pivot supporting construction comprises catoptron (7), backboard (8), first screw (12), second screw (13), tapered sleeve (15); It is characterized in that also comprising: catoptron supporting component (9), mirror assembly reconditioning pad (10), supporting component over cap (11), the 3rd screw (14); Wherein, catoptron supporting component (9) comprising: groove (16), joint flange (17), the 4th screw (18), top chock (19), club (20), step (21), the 5th screw (22), first straight pin (23), second straight pin (24); Club (20) is columnar structured near an end of joint flange (17); Around the club wall, have four grooves (16); Four groove 90 ° of distributions at interval on club; Relative groove cut direction is identical, and the adjacent grooves cut direction is opposite, and the other end bulb of club (20) is a spherical hollow space; Joint flange (17) is connected with backboard (8) through first screw (12) in catoptron supporting component (9); Joint flange (17) is connected with tapered sleeve (15) through second screw (13) simultaneously, and top chock (19) is a clearance fit with the surface of contact C of tapered sleeve (15), and tapered sleeve (15) is gluing with catoptron (7); The bulb of top chock (19), club (20) and step (21) are assembled together through the 5th screw (22) and second straight pin (24), and the rod end of club (20) links together with joint flange (17) through the 4th screw (18), first straight pin (23); Supporting component over cap (11) is fixed on the backboard (8) through the 3rd screw (14); Mirror assembly reconditioning pad (10) has 3, becomes 120 ° of distributions, and mirror assembly reconditioning pad (10) is pressed between remote sensing camera framework and the backboard (8) through the attachment screw between remote sensor phase machine frame and the backboard (8).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN2011100462666A CN102109657B (en) | 2011-02-25 | 2011-02-25 | Ball hinge support structure of large caliber reflector of space remote sensor |
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| Application Number | Priority Date | Filing Date | Title |
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| CN2011100462666A CN102109657B (en) | 2011-02-25 | 2011-02-25 | Ball hinge support structure of large caliber reflector of space remote sensor |
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| CN102109657A CN102109657A (en) | 2011-06-29 |
| CN102109657B true CN102109657B (en) | 2012-06-13 |
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Families Citing this family (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102902042A (en) * | 2012-10-31 | 2013-01-30 | 中国科学院长春光学精密机械与物理研究所 | Composite flexible support structure for large caliber reflector |
| CN103018878A (en) * | 2012-12-21 | 2013-04-03 | 中国科学院长春光学精密机械与物理研究所 | Reflector supporting structure with temperature compensation function |
| 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 |
| CN104632974B (en) * | 2014-12-25 | 2016-08-24 | 中国科学院长春光学精密机械与物理研究所 | A kind of vibration-proof structure for aviation optical remote sensor |
| CN104678533A (en) * | 2015-02-13 | 2015-06-03 | 中国科学院长春光学精密机械与物理研究所 | Ground gravity unloading support method for large spatial reflector |
| CN104914550B (en) * | 2015-05-28 | 2017-11-07 | 北京空间机电研究所 | A kind of reflecting mirror support structure acted on thermal stress unloading |
| CN106443956B (en) * | 2016-09-23 | 2018-11-02 | 中国科学院西安光学精密机械研究所 | Large-diameter camera reflector mounting structure |
| CN107037567B (en) * | 2017-05-19 | 2020-09-18 | 北京空间机电研究所 | Reflector supporting structure with three-point ball head combined with radial cementation |
| CN110824661A (en) * | 2019-12-13 | 2020-02-21 | 中国科学院长春光学精密机械与物理研究所 | Secondary mirror supporting structure |
| CN111288916A (en) * | 2020-02-28 | 2020-06-16 | 中国科学院上海技术物理研究所 | Precise installation and adjustment device for optical reflector surface shape test |
| CN111999847B (en) * | 2020-08-04 | 2022-07-29 | 北京空间机电研究所 | High-stability supporting structure applied to strip-shaped space reflector |
| CN113703127B (en) * | 2021-09-07 | 2022-07-15 | 中国科学院长春光学精密机械与物理研究所 | Square heavy-calibre speculum bearing structure based on back three point supports |
| CN115268011B (en) * | 2022-09-29 | 2022-12-09 | 中国科学院长春光学精密机械与物理研究所 | Gravity unloading device for reflector |
| CN116533736A (en) * | 2022-12-30 | 2023-08-04 | 奥动新能源汽车科技有限公司 | Quick change device and contain its trading vehicle |
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| SU1697038A1 (en) * | 1989-04-14 | 1991-12-07 | Предприятие П/Я Г-4149 | Mount for optic component with central opening |
| US7405834B1 (en) * | 2006-02-15 | 2008-07-29 | Lockheed Martin Corporation | Compensated coherent imaging for improved imaging and directed energy weapons applications |
| CN201348670Y (en) * | 2009-01-22 | 2009-11-18 | 中国科学院西安光学精密机械研究所 | Three-point supporting device of large-diameter reflector |
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Granted publication date: 20120613 Termination date: 20140225 |