CN101571389B - Method for precisely assembling space remote sensing camera body structure - Google Patents
Method for precisely assembling space remote sensing camera body structure Download PDFInfo
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- CN101571389B CN101571389B CN2009100670727A CN200910067072A CN101571389B CN 101571389 B CN101571389 B CN 101571389B CN 2009100670727 A CN2009100670727 A CN 2009100670727A CN 200910067072 A CN200910067072 A CN 200910067072A CN 101571389 B CN101571389 B CN 101571389B
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Abstract
The invention provides a method for precisely assembling a space remote sensing camera body structure, belonging to the technical field of assembly connection of body equipment. The method is to use aglue film as the close loop size of body assembly, lead assembly precision and assembly stress to depend on the deflection of the glue film, cancel the pad which may generate larger error, change the assembly mode of a transition component from glue connection first and screwed connection second of mechanical connection method into screwed connection first and glue connection second, use the meta l pad to be wound on the transition component to be closely matched with an inner hole of a strut, and better achieve the aims of small assembly stress, high assembly precision and steady and firm structure through a microstress glue connection method. The glue connection method reduces the stress of the body structure on sensitive orientation, namely on axial of the strut, and optimizes the stress status of the body. Meanwhile, the method has simple and convenient operation, short assembly period and low cost, and overcomes the defects of long period and high cost of the prior assembly methodby finishing the pad.
Description
Technical field
The invention belongs to the accurate mounting technology of space optics exact instrument airframe structure field, be specially a kind of method of space remote sensing camera airframe structure assembling.
Background technology
Airframe structure is the critical component of space remote sensing camera.Main effect is the relative position that accurately guarantees each optical element, forms optical imaging system, bears extraneous impact.So airframe structure needs the good rigidity of structure and structural stability, this needs that not only sufficient assurance is arranged in design, and also good implementation method will be arranged in the assembling link.
The assembling effect depends on the height of assembly precision and the size of erection stress.Owing to all have error when measuring, processing and assembling, so will inevitably produce erection stress.If erection stress is bigger, fuselage will produce the distortion of the trace that continues in considerable time after assembling, make the fuselage loses stability, causes precise decreasing.Though erection stress can't be eliminated fully, must adopt suitable assembly method to reduce as far as possible.
For satisfying the big lightweight requirement of the high volume of airframe structure rigidity.The large-sized space camera fuselage of many long-focus adopts the split-type structural design mostly, makes load-carrying construction with light-weight high-strength material and connects a plurality of metal frameworks compositions, to reach the effect that loss of weight does not subtract rigidity.
The mechanical connection assembling method partial sectional view that prior art adopts is as shown in Figure 1:
Part shown in the figure: framework 1, transition piece 2, pole 3, glue-line 4, touch-up pad 5.
Being connected between pole 3 and the metal framework 1 is the main task of assembling, now generally adopts bonding mode to carry out both connections.For improving assembly process process, between pole 3 and framework 1, use titanium alloy transition piece 2, one sides to glued joint opposite side and be threaded with framework 1 with pole 3.
It mainly is the relative position that guarantees between former and later two metal frameworks 1 that assembly precision requires.Main accurate assembling means is by the spacing between accurate gage frame 1 and transition piece 2 both ends of the surface now, and the thickness of touch-up pad 5 and face type are just in time to adapt to the method for this spacing, as shown in Figure 1 then.The characteristics of the method are that the closed loop size that will assemble is arranged on the link of repairing accent pad 5.
But there is certain defective in this method:
1. when measuring 5 types of pad, can only find and the true akin situation of face type, can't accurately record true face type by multimetering.
2. the repeatedly measurement resetting to single-point is relatively more difficult, and also there is identical problem in processing with detecting during touch-up pad 5, so produce bigger measurement and mismachining tolerance.
Pad 5 after the finishing when assembling can't be fully state when measuring be consistent, always have some rotation and skew existence.
4. when screw was fastening, friction force can make and produce relative displacement between the connected piece, directly causes frame deflection.Because the assembling link is numerous, cumulative errors is bigger, produces bigger stress and distortion when causing assembling, and grows up to this height assembly period.This influences for requiring high-precision space camera is bigger, will directly cause camera properties to descend, even can't finish preplanned mission.
Summary of the invention
The present invention has changed traditional mechanical assembly method, has overcome the big shortcoming of its assembly precision low stress.A kind of assembly method of simple and fast is provided, has guaranteed higher assembly precision and lower erection stress simultaneously, and significantly reduced the cost and the cycle of assembling.
For further improving assembly precision, use bonded process at work instead and carry out the fuselage assembling, promptly before adhesive solidification, finish the location between each parts of fuselage, rely on adhesive solidification to finish last connection task.
The feature of microstress bonded process is that assembly precision and erection stress depend on the size of glue-line deflection with the closed loop size of glue-line as the fuselage assembling, as shown in Figure 2, comprising framework, transition piece, pole, glue-line, metallic gasket.Bonded process has been cancelled the pad that can produce than mistake, the transition piece fit is gluedd joint by the elder generation of mechanical connection method be threaded again, and changing into is threaded earlier glueds joint the distortion that has produced when having avoided trip bolt again.
Tackifier was a fluid before solidifying, when the Stress Transfer that produces during assembling arrives the glue-line link, tackifier can produce self-adaptation by flowing and absorb stress and distortion, being released camera body in erection stress reaches stable back glue-line and can be cured under this steady state (SS), solidify the back camera body and still can be among this steady state (SS), thereby meet the requirements of high assembly precision and low assembly stress.
Tackifier because of factors such as volatilization, cooling, crosslinked and crystallizations, cause volumetric contraction to produce bond stress, and the differential contraction stress size is relevant with the tackifier volume when solidifying.Because glue-line is unfettered along the pole axial shrinkage time, so axial shrinkage stress is less.Glue-line is subjected to by the constraint of bond along the pole radial shrinkage time, so the bond stress action direction is mainly along pole radially i.e. bondline thickness direction.The best bondline thickness of the tackifier that uses between 0.1mm～0.2mm, the tackifier shrinkage factor is less than 1%, so amount of contraction is about 0.002mm, is far smaller than the error of touch-up pad, so the bonded process erection stress obviously reduces.
The action direction of mechanical connection method erection stress is the fastening direction of screw, promptly along pole axially.The action direction of bonded process erection stress is the glue-line shrinkage direction, is mainly along pole radially.Bonded process has reduced the stress of airframe structure on sensitive direction (being that pole is axial), has optimized the stress of fuselage.
But still there is a shortcoming in this bonded process, be exactly when transition piece 2 glueds joint with carbon fiber pole 3, the hole of pole 3 cooperates with the axle of transition piece 2 and glueds joint, because existing, gravity factor make the glue-line attenuation below glue-line 4 that is stressed in top be subjected to the pulling force thickening, because bondline thickness can produce stress and produce difference on mechanical property after there are differences curing in the abutting edge, make glue-line easily in the weakness fracture, thereby do not reach designing requirement.Think the homogeneity that guarantees glue-line 4, bonded process is improved.Be wrapped on the transition piece 2 with thin metallic gasket 6 and closely cooperate with pole 3 endoporus, replace the position of original a part of tackifier 4, all the other places are still filled up with tackifier 4.Gravity finally is delivered on the metal framework 1 by metallic gasket 6, and tackifier 4 solidifies under situation about not stressing, thereby has guaranteed the homogeneity of bondline thickness, as shown in Figure 3.
Advantage of the present invention: this microstress bonded process is with the closed loop size of glue-line as the fuselage assembling, assembly precision and erection stress depend on the size of glue-line deflection, cancelled the pad that can produce than mistake, the elder generation splicing of transition piece fit by the mechanical connection method is threaded again, and changing into is threaded earlier glueds joint again.Reached better that erection stress is little, assembly precision is high and the firm firm purpose of structure by bonded process.Bonded process has reduced airframe structure at sensitive direction, i.e. the stress of pole on has axially been optimized the stress of fuselage.This method is simple to operation simultaneously, and assembly period, short cost was low, has overcome and has leaned on the shortcoming that the touch-up pad assembly method cycle is long, cost is high in the past.
Description of drawings
Fig. 1 prior art mechanical connection assembling method partial sectional view:
Part shown in the figure is: framework 1, transition piece 2, carbon fiber pole 3, glue-line 4, touch-up pad 5.
Fig. 2 the present invention glueds joint the assembling method partial sectional view, also is Figure of abstract:
Part shown in the figure is: framework 1, transition piece 2, carbon fiber pole 3, glue-line 4, metallic gasket 6.
Fig. 3 glue-line homogeneity control method cut-open view:
Part shown in the figure is: transition piece 2, carbon fiber pole 3, glue-line 4, metallic gasket 6.
Fig. 4 fuselage assembly relation front elevation:
Part shown in the figure is: transition piece 2, carbon fiber pole 3, glue-line 4, metallic gasket 6.
Embodiment
In conjunction with the accompanying drawings 2,3,4, be that example further specifies concrete grammar of the present invention with the space remote sensing camera:
At first, that the surface planarity grinding that cooperatively interacts of framework 1 and transition piece 2 is smooth with the relative position centering between the metal framework 1; The circularity of the axle of the hole of carbon fiber pole 3 and transition piece 2 is ground, and tolerance clearance will be determined according to the use adhesive performance between the axle of hole.Then thin-wall metal pad 6 width are trimmed to about 4mm～5mm, narrow meeting influence bearing accuracy, and wide can the minimizing gluedd joint area.Metallic gasket 6 is wrapped in transition piece 3 thes tip of the axis, and twining the thickness optimum value is that metallic gasket 6 external diameters are less than hole internal diameter 0.02mm～0.04mm, so that assembling and glue-line absorb erection stress.After working good, pole 3 and transition piece 2 take trial assembly between the framework 1, transition piece (2) one sides are threaded with framework (1), opposite side cooperates with pole (3) hole axle, length by finishing pole 3, the transition piece 2 that reaches pole 3 two ends all can be good fit with framework 1, do not make framework 1 produce distortion and be as the criterion.At last transition piece 2 is taken off, between the axle mating surface of hole, reinstall in the hole of pole behind the gluing, transition piece 2 is connected to framework 1, just finish assembling after waiting bonding agent 4 full solidification, shown in Fig. 4 fuselage assembly relation synoptic diagram.If it is longer to glued joint the face length degree, can be according to actual conditions at the end of transition piece 2 according to above method, twine one section metallic gasket 6 again, so that position better.
With respect to the mechanical connection method, the microstress bonded process can be improved the stress distribution situation of bond, has cancelled the pad that has than mistake, has eliminated the distortion when screw is fastening, thereby has reduced erection stress, has improved the assembly precision and the structural stability of fuselage.With the airframe structure of the space remote sensing camera of the method assembling, maximum deformation quantity can be controlled in the 0.01mm, and adopts traditional mechanical assembly method, and maximum deformation quantity is at 0.03mm～0.05mm even bigger; The method can be controlled in about 10 days assembly period, and traditional assembly method then needs about one month.
Claims (1)
1. the Precise Assembling Method of a space remote sensing camera airframe structure, it is characterized in that this Precise Assembling Method relates to framework (1), transition piece (2), pole (3), glue-line (4) and metallic gasket (6), this microstress bonded process is with the closed loop size of glue-line (4) as the fuselage assembling, and concrete assembly method is as follows:
1), that the surface planarity grinding that cooperatively interacts of framework (1) and transition piece (2) is smooth at first with the relative position centering between the metal framework (1);
2) with pole (3) endoporus and transition piece (2) the axle the circularity cutting down;
3) metallic gasket (6) is wrapped in transition piece (2) the tip of the axis, transition piece (2) and pole (3) endoporus are closely cooperated;
4) after working good, pole (3) and transition piece (2) take trial assembly between the framework (1), between pole (3) and framework (1), use transition piece (2), transition piece (2) one sides are threaded with framework (1), opposite side and pole (3) are gluedd joint, length by finishing pole (3) makes the transition piece (2) at pole (3) two ends all can be good fit with framework (1);
5) at last transition piece (2) is taken off, between the axle mating surface of hole, reinstall in the hole of pole (3) behind the gluing, transition piece (2) is connected to framework (1), just finish assembling after waiting glue-line (4) full solidification.
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| Application Number | Priority Date | Filing Date | Title |
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| CN2009100670727A CN101571389B (en) | 2009-06-05 | 2009-06-05 | Method for precisely assembling space remote sensing camera body structure |
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| CN2009100670727A CN101571389B (en) | 2009-06-05 | 2009-06-05 | Method for precisely assembling space remote sensing camera body structure |
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| CN101571389B true CN101571389B (en) | 2011-08-17 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109752903A (en) * | 2018-12-29 | 2019-05-14 | 中国科学院长春光学精密机械与物理研究所 | Truss structure and its assemble method for remote sensing camera |
Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102284859A (en) * | 2011-05-06 | 2011-12-21 | 中国科学院上海技术物理研究所 | Digital assembly method of space remote sensing instrument |
| CN102426615B (en) * | 2011-09-01 | 2013-04-10 | 北京理工大学 | Matching error calculation method for error transfer modeling of precision mechanical system |
| CN102338919B (en) * | 2011-10-18 | 2013-07-24 | 北京空间机电研究所 | Method for assembling and adjusting all-microcrystalline lens |
| CN103795907B (en) * | 2014-01-23 | 2017-04-05 | 中国科学院长春光学精密机械与物理研究所 | The main frame assembling device of space optical camera and assembly method |
| CN104034315B (en) * | 2014-06-30 | 2016-01-13 | 中国科学院长春光学精密机械与物理研究所 | The assembly method of overlength focal length remote sensing camera truss-frame structure |
| CN104832511B (en) * | 2015-04-21 | 2017-07-25 | 中国科学院长春光学精密机械与物理研究所 | A kind of method for controlling optical sensor space truss bar to be bonded bondline thickness |
| CN114935817A (en) * | 2022-05-16 | 2022-08-23 | 长光卫星技术股份有限公司 | Telescope truss structure and precision assembly method thereof |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2536446Y (en) * | 2002-02-22 | 2003-02-19 | 常州理研精工机械有限公司 | Luggage racks on vehicle top |
| CN2743875Y (en) * | 2004-10-28 | 2005-11-30 | 中国科学院长春光学精密机械与物理研究所 | Strucure of optical remote sensing camera frame |
| CN201042797Y (en) * | 2007-05-25 | 2008-04-02 | 山东硅苑新材料科技股份有限公司 | Alumina ceramic handle kitchen tool |
-
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Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2536446Y (en) * | 2002-02-22 | 2003-02-19 | 常州理研精工机械有限公司 | Luggage racks on vehicle top |
| CN2743875Y (en) * | 2004-10-28 | 2005-11-30 | 中国科学院长春光学精密机械与物理研究所 | Strucure of optical remote sensing camera frame |
| CN201042797Y (en) * | 2007-05-25 | 2008-04-02 | 山东硅苑新材料科技股份有限公司 | Alumina ceramic handle kitchen tool |
Non-Patent Citations (1)
| Title |
|---|
| 丁亚林.一种提高碳纤维符合材料框架结构应用性能的结构技术.《光学紧密工程》.2003,第11卷(第3期),287-290. * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109752903A (en) * | 2018-12-29 | 2019-05-14 | 中国科学院长春光学精密机械与物理研究所 | Truss structure and its assemble method for remote sensing camera |
| CN109752903B (en) * | 2018-12-29 | 2020-10-27 | 中国科学院长春光学精密机械与物理研究所 | Truss structure for remote sensing camera and assembling method thereof |
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