CN103795907B - The main frame assembling device of space optical camera and assembly method - Google Patents
The main frame assembling device of space optical camera and assembly method Download PDFInfo
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- CN103795907B CN103795907B CN201410032091.7A CN201410032091A CN103795907B CN 103795907 B CN103795907 B CN 103795907B CN 201410032091 A CN201410032091 A CN 201410032091A CN 103795907 B CN103795907 B CN 103795907B
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- front baffle
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Abstract
The main frame assembling device of space optical camera and assembly method, aerospace field, the assembly precision for solving the presence of existing space optical camera main frame assembly method is low, and the structural stability of camera main frame is poor, and then reduces the problem of space optical camera image quality.The device includes：By the fixed frame of square shape structure and U-shaped structure by hollow square steel sealing of tube；, for carrying out six degree of freedom adjustment to front baffle, hold-down mechanism is for being fixed on square shape structure by front baffle for screw micro-adjustment mechanism, spiral levelling gear and hold-down mechanism in square shape structure, screw micro-adjustment mechanism and spiral levelling gear；Connecting seat in U-shaped structure, connecting seat is for being fixed on U-shaped structure by afterframe.This invention ensures that the positional precision of forward and backward framework meets to require, assembly precision is high, and resetting difficulty is low, and residual stress will not be produced in assembling process, and structural stability is high.
Description
Technical field
The present invention relates to field of aerospace technology, and in particular to a kind of main frame of space optical camera assembling device and
Assembly method.
Background technology
Space optical camera main frame is the vitals of space optical camera.Each mirror assembly in space optical camera
It is both needed to be arranged on camera main frame according to optical position with imaging sensor.As shown in figure 1, camera main frame is by front baffle
11st, afterframe 12, multiple carbon fibre pole 13 and multiple strut connectors 14 are constituted, when camera main frame is assembled, first by afterframe
12 are placed on platform, then all carbon fibre pole 13 two ends are coated be glued with strut connector 14 after epoxide-resin glue, such as Fig. 2 institutes
Show, the two ends of carbon fibre pole 13 are glued and have strut connector 14, using epoxide-resin glue hardening time it is longer the characteristics of, adjust respectively
Whole strut connector 14 and front baffle 11 and the position relationship of afterframe 12, then by strut connector 14 and front baffle 11 and afterframe
12 are fixedly connected using screw, and standing treats epoxy resin adhesive curing.
At present, for the assembling of space optical camera main frame is all using above-mentioned assembly method, however, above-mentioned dress
There is certain alignment error during matching somebody with somebody：As shown in Fig. 2 in mode connects for screw, unthreaded hole and the screw of strut connector 14 have monolateral
The gap of 0.5mm, the gap for having monolateral 0.2mm between carbon fibre pole 13 and strut connector 14 carry out the filling of epoxide-resin glue.This
Two kinds of alignment errors control the bad positional precision that can cause camera main frame and decline, and reduce the installation essence of each mirror assembly
Degree, can cause the location conflicts of mirror assembly and camera main frame when serious；The gravity of front baffle 11 make carbon fibre pole 13 with
Glue-line between strut connector 14 presses to side, causes glue-line uneven, camera main frame can be made residual stress occur, in spatial light
After learning camera experience transmitter section vibration and entering the orbit after weightless and vacuum environment, camera main frame has certain residual stress and releases
Put, this can make the optical position between each mirror assembly change, reduce the stability of camera main frame structure, and then reduce
The image quality of space optical camera.
The content of the invention
It is low in order to solve the assembly precision that existing space optical camera main frame assembly method is present, camera main frame
Structural stability is poor, and then reduces the problem of space optical camera image quality, the present invention provide a kind of simple structure, can be effective
Improve the main frame assembling device of the space optical camera of camera main frame installation accuracy and structural stability and adopt the device
The high-precision spatial optical camera main frame assembly method of realization.
The present invention is as follows by solving the technical scheme that technical problem is adopted：
The main frame assembling device of space optical camera, including：
By the fixed frame of square shape structure and U-shaped structure by hollow square steel sealing of tube；
Screw micro-adjustment mechanism, spiral levelling gear and hold-down mechanism in square shape structure, the spiral fine setting
, for carrying out six degree of freedom adjustment to front baffle, the hold-down mechanism is for front baffle is fixed on for mechanism and spiral levelling gear
In square shape structure；
Connecting seat in U-shaped structure, the connecting seat is for being fixed on U-shaped structure by afterframe.
The square shape structure is sequentially welded using four hollow square steel pipes.
The U-shaped structure is formed using three hollow square steel sealing of tube.
The connecting seat is four, and two are symmetricly set on the U-shaped two ends of U-shaped structure, and other two is symmetrical arranged
On the top of U-shaped structure.
The screw micro-adjustment mechanism is six, and four are symmetricly set on two opposite side of square shape structure, other two
It is symmetricly set on two other opposite side of square shape structure.
The spiral levelling gear is three, and three spiral levelling gears are separately positioned on three sides of square shape structure
On.
The main frame assembly method of space optical camera, comprises the following steps：
Step one, afterframe is placed on platform, the U-shaped structure of fixed frame is enclosed within afterframe, by connection
U-shaped structure of the seat by afterframe with fixed frame is fixed together；
Step 2, front baffle is placed in the square shape structure of fixed frame, by screw micro-adjustment mechanism and spiral leveling
Mechanism carries out six degree of freedom adjustment to front baffle, compresses front baffle and the square shape structure of fixed frame by hold-down mechanism solid
It is fixed；
Step 3, carbon fibre pole and strut connector are set in together, then trial assembly is carried out with front baffle and afterframe, finely tuned
Link position between strut connector and front baffle and afterframe, makes carbon fibre pole rotate in strut connector；
After the completion of step 4, each group carbon fibre pole and strut connector trial assembly, carbon fibre pole is unloaded one by one with strut connector,
Epoxide-resin glue is smeared, and assembling fixation is carried out with front baffle and afterframe again；
Step 5, camera main frame assembling after the completion of, using laser range finder to the position between front baffle and afterframe
The relation of putting is rechecked, if having overproof, is finely adjusted by screw micro-adjustment mechanism and spiral levelling gear, until front baffle with
The positional precision of afterframe meets the design requirement of space optical camera main frame, and standing treats epoxy resin adhesive curing.
In the step 2, six degree of freedom adjustment is carried out to front baffle by screw micro-adjustment mechanism and spiral levelling gear
Concretely comprise the following steps：The reality of front baffle and three high accuracy quadrature detection datum levels of afterframe is measured respectively using laser range finder
Position relationship, by being calculated theoretical position and physical location deviation, by screw micro-adjustment mechanism to camera main frame before
Framework carries out the fine setting of azimuth and two horizontal direction translation three degree of freedoms, by spiral levelling gear to camera main frame
Front baffle carry out the angle of pitch, rock angle and the fine setting of short transverse translation three degree of freedom, through successive ignition measure and adjust
It is whole, positional precision of the front baffle with afterframe is adjusted in the design requirement of space optical camera main frame.
The invention has the beneficial effects as follows：
The assembling that camera main frame is carried out using the device of the present invention can ensure the positional precision between front baffle and afterframe
Meet design requirement, improve the assembly precision of camera main frame, the positional precision of camera main frame meets design requirement, reduce
The difficulty that mirror opticss are debug；Each carbon fibre pole can be assembled alone with strut connector, reduce execute-in-place difficulty；Carbon
Between fine pole and strut connector, glue-line is evenly distributed, and camera main frame will not produce residual stress in assembling process, improve
The structural stability of camera main frame.The present invention can be used for the fields such as the frame structure assembling of space flight and fine structure.
Description of the drawings
Structural representations of the Fig. 1 for camera main frame；
Fig. 2 is the sectional view that carbon fibre pole is glued by epoxide-resin glue with strut connector；
Fig. 3 is the structural representation that the main frame of the space optical camera of the present invention assembles device；
Fig. 4 is the dimensional structure diagram after being assembled to space optical camera main frame using the device of the present invention；
Fig. 5 is and the rightabout view of dimensional structure diagram shown in Fig. 4；
Fig. 6 is the right view of the dimensional structure diagram shown in Fig. 5；
Fig. 7 is the front view of the dimensional structure diagram shown in Fig. 5.
In figure：11st, front baffle, 12, afterframe, 13, carbon fibre pole, 14, strut connector, 21, fixed frame, 22, connecting seat,
23rd, screw micro-adjustment mechanism, 24, spiral levelling gear, 25, hold-down mechanism.
Specific embodiment
The present invention is described in further detail below in conjunction with accompanying drawing.
As shown in figure 3, the space optical camera of the present invention main frame assembling device, including fixed frame 21, connecting seat 22,
Screw micro-adjustment mechanism 23, spiral levelling gear 24 and hold-down mechanism 25.
According to the characteristics of the different structure form and each governor motion and fixed structure of camera main frame, fixed frame 21 sets
Upper and lower double-layer structure is calculated as, superstructure is the square shape structure being sequentially welded using four hollow square steel pipes, and lower floor ties
Structure is the U-shaped structure using three hollow square steel sealing of tube, empty by four between square shape structure and U-shaped structure
Heart square steel tube welds together.
Four connecting seats 22 are arranged in the U-shaped structure of fixed frame 21, and two of which connecting seat 22 is symmetricly set on U-shaped
On the U-shaped two ends hollow square steel pipe of shape structure, other two connecting seat 22 is symmetricly set on the top hollow square steel of U-shaped structure
Guan Shang, connecting seat 22 link together for the U-shaped structure by the afterframe 12 of camera main frame with fixed frame 21.
Six screw micro-adjustment mechanisms 23 are arranged in the square shape structure of fixed frame 21, wherein four screw micro-adjustment mechanisms 23
It is symmetricly set on two opposite side hollow square steel pipes of square shape structure, other two screw micro-adjustment mechanism 23 is symmetricly set on mouth
On two other opposite side hollow square steel pipe of character form structure, six screw micro-adjustment mechanisms 23 can be to the front baffle of camera main frame
11 fine settings for carrying out azimuth and two horizontal direction translation three degree of freedoms.
Three spiral levelling gears 24 are arranged in the square shape structure of fixed frame 21, and three spiral levelling gears 24 are distinguished
It is arranged on three hollow square steel pipes of square shape structure, three spiral levelling gears 24 can be to the front baffle of camera main frame
11 carry out the angle of pitch, rock angle and the fine setting of short transverse translation three degree of freedom.Adjusted by screw micro-adjustment mechanism 23 and spiral
Flattening mechanism 24 is finely adjusted to front baffle 11, then the square shape by four hold-down mechanisms 25 by front baffle 11 with fixed frame 21 is tied
Structure is fixed together.
As shown in Figure 4, Figure 5, Figure 6 and Figure 7, space optical camera main frame is assembled using the device of the present invention
Method, is realized by following steps：
（1）The afterframe 12 of camera main frame is placed on platform, while after the U-shaped structure of fixed frame 21 is enclosed within
On framework 12, the U-shaped structure by connecting seat 22 by afterframe 12 with fixed frame 21 is fixed together；
（2）The front baffle 11 of camera main frame is placed in the square shape structure of fixed frame 21, by spiral freqency fine adjustment machine
Structure 23 and spiral levelling gear 24 carry out six degree of freedom adjustment to front baffle 11：
The reality of front baffle 11 and 12 3 high accuracy quadrature detection datum levels of afterframe is measured respectively using laser range finder
Border position relationship, by being calculated theoretical position and physical location deviation, by screw micro-adjustment mechanism 23 to camera main frame
Front baffle 11 carry out the fine setting of azimuth and two horizontal direction translation three degree of freedoms, by 24 pairs of phases of spiral levelling gear
The front baffle 11 of owner's framework carries out the angle of pitch, rocks angle and the fine setting of short transverse translation three degree of freedom, through repeatedly repeatedly
The positional precision of front baffle 11 and afterframe 12 is adjusted to the design requirement of space optical camera main frame by generation measurement and adjustment
Interior, do so can ensure that the position relationship in whole assembling process between front baffle 11 and afterframe 12 will not occur to become
Change, it is ensured that installation accuracy；
（3）After front baffle 11 good with the position adjustment of afterframe 12, by hold-down mechanism 25 is by front baffle 11 and fixes
The square shape structure of frame 21 is fixed；
（4）The carbon of camera main frame fibre pole 13 and strut connector 14 are set in together, then with front baffle 11 and after-frame
Frame 12 carries out trial assembly, fine setting strut connector 14 and the link position between front baffle 11 and afterframe 12, it is ensured that carbon fibre pole 13
Can easily rotate in strut connector 14, without phenomenons such as clamping stagnation, other strength；
（5）After the completion of each group carbon fibre pole 13 and 14 trial assembly of strut connector, by carbon fibre pole 13 with strut connector 14 one by one
Unload, smear epoxide-resin glue, and assembling fixation is carried out with front baffle 11 and afterframe 12 again；
（6）After the completion of the assembling of camera main frame, using laser range finder to the position between front baffle 11 and afterframe 12
The relation of putting is rechecked, if having overproof, is finely adjusted by screw micro-adjustment mechanism 23 and spiral levelling gear 24, until front frame
The positional precision of frame 11 and afterframe 12 meets the design requirement of space optical camera main frame；
（7）Standing treats epoxy resin adhesive curing.
Claims (7)
1. the main frame assembly method of space optical camera, it is characterised in that the main frame dress of the space optical camera for being adopted
Include with device：
By the fixed frame (21) of square shape structure and U-shaped structure by hollow square steel sealing of tube；
Screw micro-adjustment mechanism (23), spiral levelling gear (24) and hold-down mechanism (25) in square shape structure, it is described
Screw micro-adjustment mechanism (23) and spiral levelling gear (24) are for carrying out six degree of freedom adjustment, the compacting machine to front baffle (11)
Structure (25) is for being fixed on square shape structure by front baffle (11)；
Connecting seat (22) in U-shaped structure, the connecting seat (22) are tied for afterframe (12) is fixed on U-shaped
On structure；
The main frame assembly method of space optical camera, comprises the following steps：
Step one, afterframe (12) is placed on platform, the U-shaped structure of fixed frame (21) is enclosed within afterframe (12),
U-shaped structure by connecting seat (22) by afterframe (12) with fixed frame (21) is fixed together；
Step 2, front baffle (11) is placed in the square shape structure of fixed frame (21), by screw micro-adjustment mechanism (23) and
Spiral levelling gear (24) carries out six degree of freedom adjustment to front baffle (11), by hold-down mechanism (25) by front baffle (11) with it is solid
The square shape structure for determining frame (21) is fixed；
Step 3, by carbon fibre pole (13) and strut connector (14) be set in together, then with front baffle (11) and afterframe (12)
Trial assembly, fine setting strut connector (14) and the link position between front baffle (11) and afterframe (12) are carried out, carbon fibre pole is made
(13) can be in rotation in strut connector (14)；
After the completion of step 4, each group carbon fibre pole (13) and strut connector (14) trial assembly, by carbon fibre pole (13) and strut connector
(14) unload one by one, smear epoxide-resin glue, and assembling fixation is carried out with front baffle (11) and afterframe (12) again；
Step 5, camera main frame assembling after the completion of, using laser range finder between front baffle (11) and afterframe (12)
Position relationship rechecked, if having overproof, be finely adjusted by screw micro-adjustment mechanism (23) and spiral levelling gear (24),
Until the positional precision of front baffle (11) and afterframe (12) meets the design requirement of space optical camera main frame, standing treats ring
Oxygen tree fat adhesive curing.
2. the main frame assembly method of space optical camera according to claim 1, it is characterised in that the square shape knot
Structure is sequentially welded using four hollow square steel pipes.
3. the main frame assembly method of space optical camera according to claim 1, it is characterised in that the U-shaped knot
Structure is formed using three hollow square steel sealing of tube.
4. the main frame assembly method of space optical camera according to claim 1, it is characterised in that the connecting seat
(22) it is four, two are symmetricly set on the U-shaped two ends of U-shaped structure, and other two is symmetricly set on the top of U-shaped structure
On end.
5. the main frame assembly method of space optical camera according to claim 1, it is characterised in that the spiral fine setting
Mechanism (23) is six, and four are symmetricly set on two opposite side of square shape structure, and other two is symmetricly set on square shape
On two other opposite side of structure.
6. the main frame assembly method of space optical camera according to claim 1, it is characterised in that the spiral leveling
Mechanism (24) is three, and three spiral levelling gears (24) are separately positioned on three sides of square shape structure.
7. the main frame assembly method of space optical camera according to claim 1, it is characterised in that the step 2
In, the concrete step of six degree of freedom adjustment is carried out by screw micro-adjustment mechanism (23) and spiral levelling gear (24) to front baffle (11)
Suddenly it is：The reality of front baffle (11) and (12) three high accuracy quadrature detection datum levels of afterframe is measured respectively using laser range finder
Border position relationship, by being calculated theoretical position and physical location deviation, by screw micro-adjustment mechanism (23) to phase owner's frame
The front baffle (11) of frame carries out the fine setting of azimuth and two horizontal direction translation three degree of freedoms, by spiral levelling gear
(24) front baffle (11) to camera main frame carries out the angle of pitch, rocks angle and the fine setting of short transverse translation three degree of freedom,
Measure and adjust through successive ignition, positional precision of the front baffle (11) with afterframe (12) is adjusted to into space optical camera master
In the design requirement of framework.
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN104076523B (en) * | 2014-06-30 | 2016-07-06 | 中国科学院长春光学精密机械与物理研究所 | The optical system alignment method of Low rigidity frame structure |
| CN104777581B (en) * | 2015-04-21 | 2017-03-01 | 中国科学院长春光学精密机械与物理研究所 | A kind of space camera of compact conformation is debug and is used three-dimensional adjusting device |
| CN105607216B (en) * | 2015-12-30 | 2018-09-14 | 中国科学院长春光学精密机械与物理研究所 | The off-axis three reflecting optical systems main supporting structure of large scale high specific stiffness truss-like |
| CN110333186B (en) * | 2019-07-05 | 2023-04-07 | 广州市锐博生物科技有限公司 | Adjusting device, adjusting system, adjusting method and adjusting control device |
| CN112461259B (en) * | 2020-10-22 | 2022-09-20 | 中国科学院长春光学精密机械与物理研究所 | Gravity balancing device for large-caliber space camera |
| CN112666675A (en) * | 2021-01-15 | 2021-04-16 | 长光卫星技术有限公司 | High-stability light and small off-axis three-mirror main support structure |
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| 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 |
| CN101571389A (en) * | 2009-06-05 | 2009-11-04 | 中国科学院长春光学精密机械与物理研究所 | Method for precisely assembling space remote sensing camera body structure |
| CN103406696A (en) * | 2013-07-31 | 2013-11-27 | 广西玉柴专用汽车有限公司 | Compressor welding tool |
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| 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 |
| CN101571389A (en) * | 2009-06-05 | 2009-11-04 | 中国科学院长春光学精密机械与物理研究所 | Method for precisely assembling space remote sensing camera body structure |
| CN103406696A (en) * | 2013-07-31 | 2013-11-27 | 广西玉柴专用汽车有限公司 | Compressor welding tool |
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