CN103795907A - Main frame assembling device and assembling method for space optical camera - Google Patents
Main frame assembling device and assembling method for space optical camera Download PDFInfo
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- CN103795907A CN103795907A CN201410032091.7A CN201410032091A CN103795907A CN 103795907 A CN103795907 A CN 103795907A CN 201410032091 A CN201410032091 A CN 201410032091A CN 103795907 A CN103795907 A CN 103795907A
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Abstract
The invention discloses a main frame assembling device and assembling method for a space optical camera, and belongs to the field of aerospace. The problems that an existing main frame assembling method of the space optical camera is low in assembling precision, the structural stability of a main frame of the camera is poor, and then the imaging quality of the space optical camera is reduced are solved. The device comprises a fixed frame formed by welding a square structure and a U-shaped structure through a hollow square steel tube, a spiral fine adjusting mechanism, a spiral leveling mechanism, a pressing mechanism and a connecting seat, the spiral fine adjusting mechanism, the spiral leveling mechanism and the pressing mechanism are arranged on the square structure, the spiral fine adjusting mechanism and the spiral leveling mechanism are used for carrying out six-freedom-degree adjustment on a front frame, the pressing mechanism is used for fixing the front frame to the square structure, the connecting seat is arranged on the U-shaped structure, and the connecting seat is used for fixing a rear frame to the U-shaped structure. The position precision of the front frame and the rear frame can meet requirements, the assembling precision is high, assembling and adjusting difficulty is low, residual stress cannot be generated in the assembling process, and the structural stability is high.
Description
Technical field
The present invention relates to field of aerospace technology, be specifically related to a kind of main frame assembling device and assembly method of space optical camera.
Background technology
Space optical camera main frame is the vitals of space optical camera.In space optical camera, each mirror assembly and imaging sensor all need be arranged on camera main frame according to optical position.As shown in Figure 1, camera main frame is by front baffle 11, afterframe 12, the fine pole 13 of multiple carbon and multiple strut connector 14 form, in the time of assembling camera main frame, first afterframe 12 is placed on platform, after again epoxide-resin glue being coated in the fine pole of all carbon 13 two ends, glued joint with strut connector 14, as shown in Figure 2, all glued joint at the two ends of the fine pole 13 of carbon strut connector 14, the feature of utilizing epoxide-resin glue to grow curing time, adjust respectively the position relationship of strut connector 14 and front baffle 11 and afterframe 12, then adopt screw to be fixedly connected with front baffle 11 with afterframe 12 strut connector 14, leave standstill and treat epoxy resin adhesive curing.
At present, all to adopt above-mentioned assembly method for the assembling of space optical camera main frame, but, in above-mentioned assembling process, there is certain alignment error: as shown in Figure 2, during screw connects, the unthreaded hole of strut connector 14 and screw have the gap of monolateral 0.5mm, between the fine pole 13 of carbon and strut connector 14, have the gap of monolateral 0.2mm to carry out the filling of epoxide-resin glue.These two kinds of bad meetings of alignment error control cause the positional precision of camera main frame to decline, and reduce the installation accuracy of each mirror assembly, can cause the location conflicts of mirror assembly and camera main frame when serious; The gravity of front baffle 11 makes the glue-line between the fine pole 13 of carbon and strut connector 14 press to a side, cause glue-line inhomogeneous, can make camera main frame occur residual stress, in the vibration of space optical camera experience transmitter section and after entering the orbit after weightless and vacuum environment, camera main frame has certain residual stress and discharges, this can make the optical position between each mirror assembly change, and reduces the stability of camera main frame structure, and then reduces the image quality of space optical camera.
Summary of the invention
Low in order to solve the assembly precision that existing space optical camera main frame assembly method exists, the structural stability of camera main frame is poor, and then reduce the problem of space optical camera image quality, the invention provides a kind of simple in structure, main frame assembling device of the space optical camera that can effectively improve camera main frame installation accuracy and structural stability and the high accuracy space optical camera main frame assembly method that adopts this device to realize.
The present invention for the technical scheme that technical solution problem adopts as follows:
The main frame assembling device of space optical camera, comprising:
The fixed frame being welded by hollow square steel pipe by square shape structure and U character form structure;
Be arranged on the structural screw micro-adjustment mechanism of square shape, spiral levelling gear and hold-down mechanism, described screw micro-adjustment mechanism and spiral levelling gear are for front baffle is carried out to six degree of freedom adjustment, and described hold-down mechanism is for being fixed on square shape structure by front baffle;
Be arranged on the Connection Block on U character form structure, described Connection Block is for being fixed on U character form structure by afterframe.
Described square shape structure adopts four hollow square steel pipes to be welded in turn.
Described U character form structure adopts three hollow square steel pipes to be welded.
Described Connection Block is four, on the U-shaped two ends that two are symmetricly set on U character form structure, on the top that all the other two are symmetricly set on U character form structure.
Described screw micro-adjustment mechanism is six, on two opposite side that four are symmetricly set on square shape structure, on two other opposite side that all the other two are symmetricly set on square shape structure.
Described spiral levelling gear is three, and three spiral levelling gears are separately positioned on three limits of square shape structure.
The main frame assembly method of space optical camera, comprises the following steps:
Step 1, afterframe is placed on platform, the U character form structure of fixed frame is enclosed within on afterframe, by Connection Block, the U character form structure of afterframe and 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 levelling gear, front baffle is carried out to six degree of freedom adjustment, by hold-down mechanism, the square shape structure of front baffle and fixed frame is fixed;
Step 3, fine carbon pole and strut connector are set in together, then carry out trial assembly with front baffle and afterframe, the link position between fine setting strut connector and front baffle and afterframe can rotate carbon fibre pole in strut connector;
Step 4, respectively organize the fine pole of carbon and complete with strut connector trial assembly after, carbon fibre pole and strut connector are unloaded one by one, smear epoxide-resin glue, and be again mounted with front baffle and afterframe;
Step 5, after camera main frame has assembled, adopt laser range finder to recheck the position relationship between front baffle and afterframe, if have overproof, finely tune by screw micro-adjustment mechanism and spiral levelling gear, until the designing requirement of the positional precision meeting spatial optical camera main frame of front baffle and afterframe leaves standstill and treats epoxy resin adhesive curing.
In described step 2, the concrete steps of front baffle being carried out to six degree of freedom adjustment by screw micro-adjustment mechanism and spiral levelling gear are: adopt laser range finder to measure respectively the actual positional relationship of front baffle and three high accuracy quadrature detection datum levels of afterframe, by calculating theoretical position and physical location deviation, by screw micro-adjustment mechanism, the front baffle of camera main frame is carried out the fine setting of azimuth and two horizontal direction translation three degree of freedoms, by spiral levelling gear, the front baffle of camera main frame is carried out to the angle of pitch, rock the fine setting of angle and short transverse translation three degree of freedom, through repeatedly iteration measurement and adjustment, the positional precision of front baffle and afterframe is adjusted in the designing requirement of space optical camera main frame.
The invention has the beneficial effects as follows:
The assembling that adopts device of the present invention to carry out camera main frame can guarantee that the positional precision between front baffle and afterframe meets design requirement, improve the assembly precision of camera main frame, the positional precision of camera main frame meets design requirement, and reduces the difficulty that mirror optics is debug; The fine pole of each carbon and strut connector all can be assembled alone, reduce execute-in-place difficulty; Between the fine pole of carbon and strut connector, glue-line is evenly distributed, and camera main frame can not produce residual stress in assembling process, has improved 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.
Accompanying drawing explanation
Fig. 1 is the structural representation of camera main frame;
Fig. 2 is the cutaway view that the fine pole of carbon and strut connector are gluedd joint by epoxide-resin glue;
Fig. 3 is the structural representation of the main frame assembling device of space optical camera of the present invention;
Fig. 4 is the perspective view adopting after device of the present invention assembles space optical camera main frame;
Fig. 5 is and the rightabout view of the perspective view shown in Fig. 4;
Fig. 6 is the right view of the perspective view shown in Fig. 5;
Fig. 7 is the front view of the perspective view shown in Fig. 5.
In figure: 11, front baffle, 12, afterframe, 13, the fine pole of carbon, 14, strut connector, 21, fixed frame, 22, Connection Block, 23, screw micro-adjustment mechanism, 24, spiral levelling gear, 25, hold-down mechanism.
Embodiment
Below in conjunction with accompanying drawing, the present invention is described in further detail.
As shown in Figure 3, the main frame assembling device of space optical camera of the present invention, comprises fixed frame 21, Connection Block 22, screw micro-adjustment mechanism 23, spiral levelling gear 24 and hold-down mechanism 25.
According to the feature of the different structure form of camera main frame and each governor motion and fixed structure, fixed frame 21 is designed to upper and lower double-layer structure, superstructure is to adopt four square shape structures that hollow square steel pipe is welded in turn, understructure is to adopt three U character form structures that hollow square steel pipe is welded, and between square shape structure and U character form structure, welds together by four hollow square steel pipes.
Four Connection Blocks 22 are arranged on the U character form structure of fixed frame 21, wherein two Connection Blocks 22 are symmetricly set on the U-shaped two ends hollow square steel pipe of U character form structure, all the other two Connection Blocks 22 are symmetricly set on the top hollow square steel pipe of U character form structure, and Connection Block 22 is for linking together the afterframe of camera main frame 12 and the U character form structure of 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 are symmetricly set on two opposite side hollow square steel pipes of square shape structure, all the other two screw micro-adjustment mechanisms 23 are symmetricly set on two other opposite side hollow square steel pipe of square shape structure, and six screw micro-adjustment mechanisms 23 can carry out to the front baffle of camera main frame 11 fine setting of 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, three spiral levelling gears 24 are separately positioned on three hollow square steel pipes of square shape structure, three fine settings that spiral levelling gear 24 can carry out the angle of pitch to the front baffle of camera main frame 11, rock angle and short transverse translation three degree of freedom.By screw micro-adjustment mechanism 23 and spiral levelling gear 24, front baffle 11 is finely tuned, then by four hold-down mechanisms 25, front baffle 11 and the square shape structure of fixed frame 21 are fixed together.
As shown in Figure 4, Figure 5, Figure 6 and Figure 7, the method that adopts device of the present invention to assemble space optical camera main frame, is realized by following steps:
(1) afterframe of camera main frame 12 is placed on platform, the U character form structure of fixed frame 21 is enclosed within on afterframe 12 simultaneously, by Connection Block 22, afterframe 12 and the U character form structure of fixed frame 21 are fixed together;
(2) front baffle of camera main frame 11 is placed in the square shape structure of fixed frame 21, by screw micro-adjustment mechanism 23 and spiral levelling gear 24, front baffle 11 is carried out to six degree of freedom adjustment:
Adopt laser range finder to measure respectively the actual positional relationship of front baffle 11 and 12 3 high accuracy quadrature detection datum levels of afterframe, by calculating theoretical position and physical location deviation, by screw micro-adjustment mechanism 23, the front baffle 11 of camera main frame is carried out the fine setting of azimuth and two horizontal direction translation three degree of freedoms, by spiral levelling gear 24, the front baffle 11 of camera main frame is carried out to the angle of pitch, rock the fine setting of angle and short transverse translation three degree of freedom, through repeatedly iteration measurement and adjustment, front baffle 11 and the positional precision of afterframe 12 are adjusted in the designing requirement of space optical camera main frame, do like this and can guarantee that the position relationship between front baffle 11 and afterframe 12 can not change in whole assembling process, guarantee installation accuracy,
(3) after front baffle 11 and the position of afterframe 12 are adjusted, by hold-down mechanism 25, front baffle 11 and the square shape structure of fixed frame 21 are fixed;
(4) fine the carbon of camera main frame pole 13 and strut connector 14 are set in together, carry out trial assembly with front baffle 11 and afterframe 12 again, link position between fine setting strut connector 14 and front baffle 11 and afterframe 12, guarantee that the fine pole 13 of carbon can be in the interior light rotation of strut connector 14, without phenomenons such as clamping stagnation, other strength;
(5) after respectively organizing the fine pole 13 of carbon and completing with strut connector 14 trial assemblies, fine carbon pole 13 is unloaded one by one with strut connector 14, smeared epoxide-resin glue, and be again mounted with front baffle 11 and afterframe 12;
(6) after camera main frame has assembled, adopt laser range finder to recheck the position relationship between front baffle 11 and afterframe 12, if have overproof, finely tune by screw micro-adjustment mechanism 23 and spiral levelling gear 24, until the designing requirement of the positional precision meeting spatial optical camera main frame of front baffle 11 and afterframe 12;
(7) leave standstill and treat epoxy resin adhesive curing.
Claims (8)
1. the main frame assembling device of space optical camera, is characterized in that, comprising:
The fixed frame (21) being welded by hollow square steel pipe by square shape structure and U character form structure;
Be arranged on the structural screw micro-adjustment mechanism of square shape (23), spiral levelling gear (24) and hold-down mechanism (25), described screw micro-adjustment mechanism (23) and spiral levelling gear (24) are for front baffle (11) is carried out to six degree of freedom adjustment, and described hold-down mechanism (25) is for being fixed on square shape structure by front baffle (11);
Be arranged on the Connection Block (22) on U character form structure, described Connection Block (22) is for being fixed on U character form structure by afterframe (12).
2. the main frame assembling device of space optical camera according to claim 1, is characterized in that, described square shape structure adopts four hollow square steel pipes to be welded in turn.
3. the main frame assembling device of space optical camera according to claim 1, is characterized in that, described U character form structure adopts three hollow square steel pipes to be welded.
4. the main frame assembling device of space optical camera according to claim 1, is characterized in that, described Connection Block (22) is four, on the U-shaped two ends that two are symmetricly set on U character form structure, on the top that all the other two are symmetricly set on U character form structure.
5. the main frame assembling device of space optical camera according to claim 1, it is characterized in that, described screw micro-adjustment mechanism (23) is six, on two opposite side that four are symmetricly set on square shape structure, on two other opposite side that all the other two are symmetricly set on square shape structure.
6. the main frame assembling device of space optical camera according to claim 1, is characterized in that, described spiral levelling gear (24) is three, and three spiral levelling gears (24) are separately positioned on three limits of square shape structure.
7. the main frame assembly method of space optical camera as claimed in claim 1, is characterized in that, comprises the following steps:
Step 1, afterframe (12) is placed on platform, the U character form structure of fixed frame (21) is enclosed within to afterframe (12) upper, by Connection Block (22), afterframe (12) and the U character form structure of fixed frame (21) are 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), front baffle (11) is carried out to six degree of freedom adjustment, by hold-down mechanism (25), front baffle (11) and the square shape structure of fixed frame (21) are fixed;
Step 3, fine carbon pole (13) and strut connector (14) are set in together, carry out trial assembly with front baffle (11) and afterframe (12) again, link position between fine setting strut connector (14) and front baffle (11) and afterframe (12) can rotate the fine pole of carbon (13) in strut connector (14);
Step 4, respectively organize the fine pole of carbon (13) and complete with strut connector (14) trial assembly after, the fine pole of carbon (13) and strut connector (14) are unloaded one by one, smear epoxide-resin glue, and be again mounted with front baffle (11) and afterframe (12);
Step 5, after camera main frame has assembled, adopt laser range finder to recheck the position relationship between front baffle (11) and afterframe (12), if have overproof, finely tune by screw micro-adjustment mechanism (23) and spiral levelling gear (24), until the designing requirement of the positional precision meeting spatial optical camera main frame of front baffle (11) and afterframe (12) leaves standstill and treats epoxy resin adhesive curing.
8. the main frame assembly method of space optical camera according to claim 7, it is characterized in that, in described step 2, the concrete steps of front baffle (11) being carried out to six degree of freedom adjustment by screw micro-adjustment mechanism (23) and spiral levelling gear (24) are: adopt laser range finder to measure respectively the actual positional relationship of front baffle (11) and (12) three high accuracy quadrature detection datum levels of afterframe, by calculating theoretical position and physical location deviation, front baffle (11) by screw micro-adjustment mechanism (23) to camera main frame carries out the fine setting of azimuth and two horizontal direction translation three degree of freedoms, front baffle (11) by spiral levelling gear (24) to camera main frame carries out the angle of pitch, rock the fine setting of angle and short transverse translation three degree of freedom, through repeatedly iteration measurement and adjustment, front baffle (11) and the positional precision of afterframe (12) are adjusted in the designing requirement of space optical camera main frame.
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| 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 |
| CN104777581A (en) * | 2015-04-21 | 2015-07-15 | 中国科学院长春光学精密机械与物理研究所 | Three-dimensional adjusting device with compact structure for mounting and adjusting space camera |
| CN105607216A (en) * | 2015-12-30 | 2016-05-25 | 中国科学院长春光学精密机械与物理研究所 | Large-size and high specific stiffness truss off-axis three-reflection optical system main support structure |
| 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 |
| CN110333186A (en) * | 2019-07-05 | 2019-10-15 | 广州市锐博生物科技有限公司 | Regulating device, regulating system, adjusting method and control set for adjusting |
| CN112461259A (en) * | 2020-10-22 | 2021-03-09 | 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 |
| 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 |
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