CN112965324B - Carbon fiber truss body assembling and adjusting device and process based on gluing error compensation - Google Patents
Carbon fiber truss body assembling and adjusting device and process based on gluing error compensation Download PDFInfo
- Publication number
- CN112965324B CN112965324B CN202110312689.1A CN202110312689A CN112965324B CN 112965324 B CN112965324 B CN 112965324B CN 202110312689 A CN202110312689 A CN 202110312689A CN 112965324 B CN112965324 B CN 112965324B
- Authority
- CN
- China
- Prior art keywords
- frame
- reticle
- upper frame
- lower frame
- assembly
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- G—PHYSICS
- G03—PHOTOGRAPHY; CINEMATOGRAPHY; ANALOGOUS TECHNIQUES USING WAVES OTHER THAN OPTICAL WAVES; ELECTROGRAPHY; HOLOGRAPHY
- G03B—APPARATUS OR ARRANGEMENTS FOR TAKING PHOTOGRAPHS OR FOR PROJECTING OR VIEWING THEM; APPARATUS OR ARRANGEMENTS EMPLOYING ANALOGOUS TECHNIQUES USING WAVES OTHER THAN OPTICAL WAVES; ACCESSORIES THEREFOR
- G03B17/00—Details of cameras or camera bodies; Accessories therefor
- G03B17/02—Bodies
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Telescopes (AREA)
Abstract
The invention relates to a carbon fiber truss body assembling and adjusting device and a carbon fiber truss body assembling and adjusting process based on gluing error compensation, and aims to solve the problems that an existing conventional assembling and adjusting process of a carbon fiber truss body is easy to generate assembling errors, and trimming links are more in the assembling process, so that the working efficiency is low. The device comprises an optical platform, an assembling and adjusting platform, an optical alignment assembly, an upper frame reference partition plate assembly and a lower frame reference partition plate assembly. The adjusting platform comprises a reflector chamber arranged on the optical platform, an objective table arranged at the upper end of the reflector chamber, three or four bearing columns arranged on the objective table, a pitching fine adjustment mechanism and a translation fine adjustment mechanism arranged on the bearing columns, wherein a first window is arranged on the side wall of the reflector chamber, and a second window is arranged in the middle of the objective table. The optical alignment assembly comprises a four-dimensional adjusting table arranged in the reflector chamber, a 45-degree reflector set arranged on the four-dimensional adjusting table, a lifting table arranged outside the reflector chamber, and a micrometering collimating telescope arranged on the lifting table.
Description
Technical Field
The invention relates to the technical field of optics, in particular to a carbon fiber truss body assembling and adjusting device and process based on gluing error compensation.
Background
The camera body structure is an important component of a remote sensing camera, is the key of high-quality imaging of an optical system, can bear the impact on the camera in the test and emission stages, and also can meet the use requirement under the space environment, so that the camera body structure needs to have enough dynamic and static rigidity and structural stability.
At present, with the requirement of space camera for light weight and the development of new material technology, a design scheme of a carbon fiber truss structure is gradually adopted in the structural design of large and medium-sized space cameras. The carbon fiber truss structure is typically constructed by connecting a front group to a rear group by a number of rods to form a stable system. The structure of the carbon fiber truss fuselage is shown in fig. 1 and 2, and includes an upper frame 01, a lower frame 02, and a plurality of connecting rod assemblies 03 composed of carbon fiber rods 031 and metal joints 032. The truss body mainly depends on the connecting rod assembly 03 as a bearing structure, so the assembly of the connecting rod assembly 03 is an important link for ensuring the structural performance of the truss body. For spatial optical systems, the performance of the fuselage structure depends to a large extent on the assembly of the fuselage.
The conventional assembly and adjustment process of the carbon fiber truss body comprises the following steps:
the first step is as follows: the single carbon fiber rod 031 is assembled and bonded with the metal joint 032. The relative position of the metal joint 032 and the carbon fiber rod 031 needs to be controlled during assembly, so that the parallelism of the upper and lower surfaces of the metal joint 032 and the position accuracy of the connecting hole are guaranteed. In addition, the consistency of the lengths and the form and position errors of the plurality of connecting rod assemblies 03 formed by bonding the carbon fiber rods 031 with the metal joints 032 at the two ends is controlled.
The second step is that: and assembling the truss body. A plurality of connecting rod assemblies 03 are connected with the upper frame 01 and the lower frame 02 in a screw connection mode, and assembling errors between the metal connector 032 and the carbon fiber rod 031 are compensated through trimming pads in the assembling process, so that the truss body is assembled.
The third step: the truss fuselage is stress relieved. And eliminating the internal assembly stress of the truss body through temperature circulation and vibration.
The assembly and adjustment process has the following problems:
firstly, after the truss bodies are rigidly connected together through screws due to assembly errors and trimming pad processing errors of the connecting rod assemblies 03, the interior of the truss bodies is deformed and generates large internal stress, so that the optical performance of an optical-mechanical system is reduced and unstable, and the realization of the optical technical indexes of the system can be influenced finally;
secondly, the assembly reference surface of the upper frame 01 and the lower frame 02 is used as an interface for connecting the optical assembly, and has higher requirements on the parallelism, so that the trimming cushion is designed as an adjusting link, so that the number of trimming links in the assembly process of the truss body is large, the precision control is very difficult, and the working efficiency is greatly reduced.
Disclosure of Invention
The invention aims to solve the problems that the conventional assembly and adjustment process of the carbon fiber truss body is easy to generate assembly errors, so that the optical performance of an optical-mechanical system is reduced and unstable, more trimming links are needed in the assembly process, the precision control is very difficult, and the working efficiency is reduced, and provides the carbon fiber truss body assembly and adjustment device and process based on adhesion error compensation.
In order to achieve the purpose, the technical scheme adopted by the invention is as follows:
the utility model provides a carbon fiber truss fuselage assembly and adjustment device based on sticky error compensation which characterized in that:
the device comprises an optical platform, an assembling and adjusting platform, an optical alignment assembly, an upper frame reference partition plate assembly and a lower frame reference partition plate assembly;
the adjusting platform comprises a reflector chamber arranged on the optical platform, an objective table arranged at the upper end of the reflector chamber, three or four bearing columns arranged on the objective table, a pitching fine adjustment mechanism and a translation fine adjustment mechanism arranged on the bearing columns; a first window is arranged on the side wall of the reflector chamber; the object stage is used for placing the lower frame, and a second window is arranged in the middle of the object stage; the bearing column is used for installing the upper frame; the pitching fine adjustment mechanism and the translation fine adjustment mechanism are used for adjusting the position and the posture of the upper frame;
the optical alignment assembly comprises a four-dimensional adjusting table, a 45-degree reflector group, a lifting table and a micrometering collimating telescope; the four-dimensional adjusting table is arranged on the optical platform and is positioned in the reflector chamber; the 45-degree reflector group is arranged on the four-dimensional adjusting table; the lifting platform is arranged on the optical platform and is positioned outside the reflector chamber; the micro-alignment telescope is arranged on the lifting platform;
the upper frame reference reticle assembly comprises an upper frame reticle frame and an upper frame reticle arranged on the upper frame reticle frame; the upper frame reticle has a frame matched and connected with the upper frame, so that the optical axis of the upper frame reticle is superposed with the axis of the upper frame;
the lower frame reference reticle assembly comprises a lower frame reticle frame and a lower frame reticle arranged on the lower frame reticle frame; the lower frame reticle frame is in matched connection with the lower frame, so that an optical axis of the lower frame reticle coincides with an axis of the lower frame;
the upper frame reticle and the lower frame reticle can be observed through the micrometric collimating telescope through the first window, the 45-degree reflector group and the second window.
Furthermore, the upper frame reticle frame is of a cylindrical structure, the outer diameter of the upper frame reticle frame is matched with the inner diameter of a central hole of the upper frame, and the outer side of the lower end of the upper frame reticle frame is provided with an annular boss which is fixedly connected with the lower end face of the upper frame; the upper frame reticle is arranged in the middle of the lower end face of the upper frame reticle mirror frame, and the optical axis of the upper frame reticle mirror frame is superposed with the axis of the upper frame reticle mirror frame;
the lower frame reticle frame is of a cylindrical structure, the outer diameter of the lower frame reticle frame is matched with the inner diameter of a central hole of the lower frame, an annular boss is arranged on the outer side of the upper end of the lower frame reticle frame, and the annular boss is fixedly connected with the upper end face of the lower frame; the lower frame reticle is arranged in the middle of the upper end face of the lower frame reticle mirror frame, and the optical axis of the lower frame reticle is superposed with the axis of the lower frame reticle mirror frame.
Furthermore, the pitching fine adjustment mechanism comprises an adjusting bolt which is arranged on each bearing column and the axis of the adjusting bolt is vertical to the table top of the optical platform;
the translation fine adjustment mechanism comprises adjusting bolts which are arranged on each bearing column and the axes of which are parallel to the table top of the optical platform.
The carbon fiber truss body assembling and adjusting process based on gluing error compensation is characterized by comprising the following steps of:
1) building the carbon fiber truss body assembling and adjusting device based on gluing error compensation;
2) pre-assembling the truss fuselage;
3) respectively installing the upper frame reference partition board assembly and the lower frame reference partition board assembly on an upper frame and a lower frame to finish the structure assembly reference calibration;
4) the truss body is pre-installed on the installing and adjusting platform, all connecting screws for connecting the upper frame, the lower frame and the connecting rod assembly are required to be in a loose connection state, the upper frame is positioned above the bearing column, and the whole weight of the upper frame is borne by the bearing column;
5) taking out the carbon fiber rod and the metal joint, uniformly coating the metal joint with glue, and then sleeving the carbon fiber rod and the metal joint together;
6) installing the connecting rod assembly and the trimming pad between the upper frame and the lower frame, and installing connecting screws between the metal joint and the upper frame and between the metal joint and the lower frame to reach moment;
7) the visual axis of the micro-alignment telescope is coincided with the optical axis of the lower frame reticle on the lower frame by adjusting the postures of the micro-alignment telescope and the 45-degree reflector group;
8) the position and the posture of the upper frame are adjusted through the pitching fine adjustment mechanism and the translation fine adjustment mechanism, so that the optical axis of the upper frame reticle on the upper frame coincides with the visual axis of the micrometric collimation telescope;
9) monitoring the contact ratio of the optical axis of the upper frame reticle and the optical axis of the lower frame reticle in the glue curing process, and returning to the step 8) to perform adjustment again if the contact ratio is changed;
10) unloading the supporting force on the pitching fine adjustment mechanism after the glue is cured, rechecking the contact ratio of the optical axis of the upper frame reticle and the optical axis of the lower frame reticle, and repairing if the contact ratio is changed; and if the contact ratio is not changed, the truss body is assembled.
Further, the step 5) is specifically carried out according to the following steps:
5.1) taking out the carbon fiber rod and the metal joint, and finely wiping the assembly surfaces of the carbon fiber rod and the metal joint by using a special solution;
5.2) uniformly coating the metal joint with glue, embedding steel wires in the glue or mixing micro glass beads in the glue, and then sleeving the carbon fiber rod and the metal joint together.
Compared with the prior art, the invention has the beneficial effects that:
by the carbon fiber truss body assembling and adjusting device and the process based on gluing error compensation, the space pose adjustment of the truss body and the bonding of the carbon fiber rods and the metal connectors can be completed at one time, the assembly difficulty is reduced, and the assembly efficiency is improved; the processing error of the structural member is compensated through the gluing process, so that the assembly precision of the truss body can be effectively improved, and the assembly error is reduced; the glue layer is used for absorbing part of assembly stress, so that the stability and reliability of the truss body can be improved.
Drawings
FIG. 1 is a schematic structural view of a prior art carbon fiber truss fuselage;
FIG. 2 is a schematic structural diagram of a connecting rod assembly in a conventional carbon fiber truss fuselage;
fig. 3 is a schematic structural diagram of one embodiment of the carbon fiber truss fuselage assembly adjustment device based on gluing error compensation of the present invention (the upper frame reference partition plate assembly and the lower frame reference partition plate assembly are not shown);
FIG. 4 is a schematic perspective view of an alignment platform, a four-dimensional alignment stage, and a 45 ° reflector assembly according to an embodiment of the present invention;
FIG. 5 is a schematic view of an assembly structure of an embodiment of the present invention with a truss fuselage;
FIG. 6 is a schematic diagram of an upper frame datum reticle assembly in an embodiment of the present invention;
fig. 7 is a schematic structural diagram of a lower frame reference partition plate assembly in an embodiment of the invention.
In the figure, 01-upper frame, 02-lower frame, 03-connecting rod assembly, 031-carbon fiber rod, 032-metal joint;
1-an optical bench;
2-adjusting platform, 21-reflector chamber, 211-first window, 22-objective table, 221-second window, 23-bearing column, 24-pitching fine adjustment mechanism and 25-translation fine adjustment mechanism;
3-optical alignment assembly, 31-four-dimensional adjusting table, 32-45 degree reflector group, 33-lifting table and 34-micrometric collimation telescope;
4-upper frame reference reticle assembly, 41-upper frame reticle mirror frame, 42-upper frame reticle; 5-lower frame reference reticle assembly, 51-lower frame reticle frame, 52-lower frame reticle.
Detailed Description
To make the objects, advantages and features of the present invention more apparent, a carbon fiber truss fuselage assembly and adjustment device and process based on gluing error compensation according to the present invention will be described in detail with reference to the accompanying drawings and specific embodiments.
The carbon fiber truss body assembly device based on gluing error compensation provided by the embodiment is shown in fig. 3 to 6 and comprises an optical platform 1, an assembly platform 2, an optical alignment assembly 3, an upper frame reference reticle assembly 4 and a lower frame reference reticle assembly 5. The assembling and adjusting platform 2 and the optical alignment assembly 3 are both arranged on the optical platform 1 and are used for assembling and adjusting the truss body; the upper frame reference reticle assembly 4 and the lower frame reference reticle assembly 5 are respectively mounted on the upper frame 01 and the lower frame 02 and used for calibrating the structural assembly reference of the upper frame 01 and the lower frame 02.
As shown in fig. 3, 4, and 5, the adjustment platform 2 includes a mirror chamber 21 provided on the optical platform 1, an object stage 22 provided at an upper end of the mirror chamber 21, three or four force bearing columns 23 provided on the object stage 22, a pitch fine adjustment mechanism 24 provided on the force bearing columns 23, and a translation fine adjustment mechanism 25. A first window 211 is arranged on the side wall of the reflector chamber 21; the object stage 22 is used for placing the lower frame 02, and a second window 221 is arranged in the middle of the object stage; the bearing column 23 is used for installing the upper frame 01; the pitch fine adjustment mechanism 24 and the pan fine adjustment mechanism 25 are used to adjust the position and posture of the upper frame 01. In this embodiment, the object stage 22 has a circular structure, the top surface of the object stage 22 is parallel to the top surface of the optical platform 1, and a circular second window 221 is disposed in the middle of the object stage 22; four bearing columns 23 are arranged, the four bearing columns 23 are uniformly distributed along the circumferential direction of the table top of the objective table 22, the pitching fine adjustment mechanism 24 comprises four adjusting bolts which are respectively arranged on the four bearing columns 23 and the axes of the four adjusting bolts are perpendicular to the table top of the optical platform 1, and the translation fine adjustment mechanism 25 comprises four adjusting bolts which are respectively arranged on the four bearing columns 23 and the axes of the four adjusting bolts are parallel to the table top of the optical platform 1. When the device is used, the end surfaces of the four adjusting bolts of the pitching fine adjustment mechanism 24 respectively prop against the lower bottom surface of the upper frame 01, and the end surfaces of the four adjusting bolts of the translation fine adjustment mechanism 25 respectively prop against the outer circular surface of the upper frame 01.
The optical alignment assembly 3 comprises a four-dimensional adjusting table 31, a 45-degree reflecting mirror group 32, a lifting table 33 and a micro-collimation telescope 34. The four-dimensional adjusting table 31 is arranged on the optical platform 1 and is positioned in the reflector room 21; the 45-degree reflector group 32 is arranged on the four-dimensional adjusting table 31, and the posture of the reflector group can be adjusted through the four-dimensional adjusting table 31; the lifting platform 33 is arranged on the optical platform 1 and is positioned outside the reflector room 21; the microcollimator 34 is arranged on a lifting table 33, the height of which can be adjusted by means of the lifting table 33.
As shown in fig. 6, the upper frame reference reticle assembly 4 includes an upper frame reticle frame 41 and an upper frame reticle 42 provided on the upper frame reticle frame 41, and the upper frame reticle frame 41 is fittingly connected to the upper frame 01 such that an optical axis of the upper frame reticle 42 coincides with an axis of the upper frame 01. Specifically, the upper frame reticle frame 41 has a cylindrical structure, an outer diameter of the upper frame reticle frame is matched with an inner diameter of a center hole of the upper frame 01, and an annular boss is arranged on an outer side of a lower end of the upper frame reticle frame and abuts against a lower end face of the upper frame 01 and is fixedly connected with the lower end face through a bolt. The upper frame reticle 42 is disposed in the middle of the lower end surface of the upper frame reticle mirror 41, and the optical axis thereof coincides with the axis of the upper frame reticle mirror 41.
As shown in fig. 7, the lower frame reference reticle assembly 5 includes a lower frame reticle frame 51 and a lower frame reticle 52 disposed on the lower frame reticle frame 51, and the lower frame reticle frame 51 is cooperatively connected with the lower frame 02 such that an optical axis of the lower frame reticle 52 coincides with an axis of the lower frame 02. Specifically, the lower frame reticle frame 51 has a cylindrical structure, an outer diameter of which is matched with an inner diameter of a central hole of the lower frame 02, and an annular boss is arranged on an outer side of an upper end of the lower frame reticle frame, and the annular boss abuts against an upper end surface of the lower frame 02 and is fixedly connected with the upper end surface of the lower frame 02 through a bolt. The lower frame reticle 52 is disposed in the middle of the upper end surface of the lower frame reticle mirror frame 51, and the optical axis thereof coincides with the axis of the lower frame reticle mirror frame 51.
Above-mentioned reticle and reticle picture frame can be fixed as the reticle subassembly through gluing or gluing + mode equipment of clamping ring, then through optics centering processing (with the reticle optical axis as the benchmark, carry out the finish machining to reticle picture frame connection terminal surface and outer face of cylinder) to guarantee that the connection terminal surface and the reticle optical axis of reticle picture frame are strict perpendicular, the excircle axis and the reticle optical axis of reticle picture frame are strict coaxial.
Wherein, the outer cylindrical surface of the reticle mirror frame is configured according to the size of the central hole of the upper frame 01/lower frame 02, so that when the reticle assembly is mounted to the upper frame 01/lower frame 02, the assembly reference of the upper frame 01/lower frame 02 is converted to the reticle optical axis.
The upper frame reticle 42 and the lower frame reticle 52 are viewable through the microcollimator 34 via the first window 211, the 45 ° mirror array 32, and the second window 221.
The embodiment also provides a carbon fiber truss fuselage assembly and adjustment process based on gluing error compensation, which comprises the following steps:
1) building the carbon fiber truss body assembling and adjusting device based on gluing error compensation;
2) the truss body is preassembled to eliminate interference, so that the truss body can be quickly assembled and glued in the subsequent assembling and adjusting process;
3) respectively installing an upper frame reference reticle assembly 4 and a lower frame reference reticle assembly 5 on an upper frame 01 and a lower frame 02 to finish the structural assembly reference calibration, and then, assembling the truss body by taking the upper frame reference reticle assembly 4 and the lower frame reference reticle assembly 5 as references;
4) the truss body is pre-installed on the installing and adjusting platform 2, all connecting screws for connecting the upper frame, the lower frame and the connecting rod assembly are required to be in a loose connection state, the upper frame 01 is positioned above the bearing column 23, all the weight of the upper frame is borne by the bearing column 23, and at the moment, the carbon fiber rod 031 is not stressed;
5) taking out the carbon fiber rod 031 and the metal joint 032, uniformly coating the metal joint 032 with glue, and then sleeving the carbon fiber rod 031 and the metal joint 032 together;
the method specifically comprises the following steps:
5.1) taking out the carbon fiber rod 031 and the metal joint 032, and finely wiping the assembly surfaces of the carbon fiber rod 031 and the metal joint 032 by using special solution;
5.2) uniformly coating the metal joint 032 with glue, embedding steel wires in the glue or mixing micro glass beads in the glue to ensure reasonable gaps of glued parts, and then sleeving the carbon fiber rod 031 and the metal joint 032 together; in addition, a shaft section can be designed at the root of the metal joint 032 to be matched with an inner hole of the carbon fiber rod 031, so that a reasonable gap of a gluing part can be ensured;
6) the connecting rod assembly 03 and the trimming pad are arranged between the upper frame 01 and the lower frame 02, connecting screws between the metal joint 032 and the upper frame 01 and the lower frame 02 are screwed up to a moment, and the metal joint 032, the upper frame and the lower frame and the carbon fiber rod 031 in a matched state are sensed in the tightening process, so that no interference and poor strength exist;
7) the postures of the micro-alignment telescope 34 and the 45-degree reflector group 32 are adjusted, so that the visual axis of the micro-alignment telescope 34 is coincided with the optical axis of the lower frame reticle 52 on the lower frame 02 (namely, the visual axis is self-aligned with the lower frame reticle 52 and coincided with the center of the lower frame reticle 52);
8) the position and the posture of the upper frame 01 are adjusted through the pitching fine adjustment mechanism 24 and the translation fine adjustment mechanism 25, so that the optical axis of the upper frame reticle 42 on the upper frame 01 is superposed with the visual axis of the micrometric collimation telescope 34, and the unification of the assembly reference of the upper frame 01 and the lower frame 02 is completed;
9) monitoring the coincidence degree of the optical axis of the upper frame reticle 42 and the optical axis of the lower frame reticle 52 in the glue curing process, and returning to the step 8) for readjustment if the coincidence degree changes;
10) after the glue is cured, unloading the supporting force on the pitching fine adjustment mechanism 24, rechecking the coincidence degree of the optical axis of the upper frame reticle 42 and the optical axis of the lower frame reticle 52, and repairing if the coincidence degree is changed; and if the contact ratio is not changed, the truss body is assembled.
Claims (4)
1. The utility model provides a carbon fiber truss fuselage assembly and adjustment device based on sticky error compensation which characterized in that:
the device comprises an optical platform (1), an assembling and adjusting platform (2), an optical alignment assembly (3), an upper frame reference partition plate assembly (4) and a lower frame reference partition plate assembly (5);
the adjusting platform (2) comprises a reflector chamber (21) arranged on the optical platform (1), an object stage (22) arranged at the upper end of the reflector chamber (21), three or four bearing columns (23) arranged on the object stage (22), a pitching fine adjustment mechanism (24) and a translation fine adjustment mechanism (25) arranged on the bearing columns (23); a first window (211) is arranged on the side wall of the reflector chamber (21); the object stage (22) is used for placing the lower frame (02), and a second window (221) is arranged in the middle of the object stage; the bearing column (23) is used for mounting an upper frame (01); the pitching fine adjustment mechanism (24) and the translation fine adjustment mechanism (25) are used for adjusting the position and the posture of the upper frame (01);
the optical alignment assembly (3) comprises a four-dimensional adjusting table (31), a 45-degree reflecting mirror group (32), a lifting table (33) and a micro-alignment telescope (34); the four-dimensional adjusting table (31) is arranged on the optical platform (1) and is positioned in the reflector chamber (21); the 45-degree reflecting mirror group (32) is arranged on the four-dimensional adjusting table (31); the lifting table (33) is arranged on the optical platform (1) and is positioned outside the reflector chamber (21); the micro-alignment telescope (34) is arranged on the lifting platform (33);
the upper frame reference reticle assembly (4) comprises an upper frame reticle frame (41) and an upper frame reticle (42) arranged on the upper frame reticle frame (41); the upper frame reticle frame (41) is in fit connection with the upper frame (01), so that the optical axis of the upper frame reticle (42) coincides with the axis of the upper frame (01);
the lower frame reference reticle assembly (5) comprises a lower frame reticle frame (51) and a lower frame reticle (52) arranged on the lower frame reticle frame (51); the lower frame reticle mirror frame (51) is matched and connected with the lower frame (02) so that the optical axis of the lower frame reticle (52) coincides with the axis of the lower frame (02);
the upper frame reticle (42) and the lower frame reticle (52) can be observed through a micrometric collimating telescope (34) through a first window (211), a 45-degree reflecting mirror group (32) and a second window (221);
the upper frame reticle frame (41) is of a cylindrical structure, the outer diameter of the upper frame reticle frame is matched with the inner diameter of a central hole of the upper frame (01), an annular boss is arranged on the outer side of the lower end of the upper frame reticle frame, and the annular boss is fixedly connected with the lower end face of the upper frame (01); the upper frame reticle (42) is arranged in the middle of the lower end face of the upper frame reticle mirror frame (41), and the optical axis of the upper frame reticle (42) is superposed with the axis of the upper frame reticle mirror frame (41);
the lower frame reticle frame (51) is of a cylindrical structure, the outer diameter of the lower frame reticle frame is matched with the inner diameter of a central hole of the lower frame (02), an annular boss is arranged on the outer side of the upper end of the lower frame reticle frame, and the annular boss is fixedly connected with the upper end face of the lower frame (02); the lower frame reticle (52) is arranged in the middle of the upper end face of the lower frame reticle mirror frame (51), and the optical axis of the lower frame reticle mirror frame coincides with the axis of the lower frame reticle mirror frame (51).
2. The carbon fiber truss fuselage assembly and adjustment device based on gluing error compensation of claim 1, wherein:
the pitching fine adjustment mechanism (24) comprises adjusting bolts which are arranged on each bearing column (23) and the axes of which are vertical to the table top of the optical platform (1);
the translation fine adjustment mechanism (25) comprises adjusting bolts which are arranged on each bearing column (23) and the axes of which are parallel to the table top of the optical platform (1).
3. The carbon fiber truss body assembling and adjusting process based on gluing error compensation is characterized by comprising the following steps of:
1) building the carbon fiber truss fuselage assembly and adjustment device based on gluing error compensation, according to claim 1;
2) pre-assembling the truss fuselage;
3) respectively installing an upper frame reference division plate assembly (4) and a lower frame reference division plate assembly (5) on an upper frame (01) and a lower frame (02) to finish the structure assembly reference calibration;
4) a truss body is pre-installed on the installing and adjusting platform (2), all connecting screws for connecting the upper frame (01), the lower frame (02) and the connecting rod assembly (03) are required to be in a loose connection state, the upper frame (01) is positioned above the bearing column (23), and the whole weight of the upper frame is borne by the bearing column (23);
5) taking out the carbon fiber rod (031) and the metal joint (032), uniformly coating the metal joint (032) with glue, and then sleeving the carbon fiber rod (031) and the metal joint (032) together;
6) installing the connecting rod assembly (03) and the trimming pad between the upper frame (01) and the lower frame (02), and installing connecting screws between the metal joint (032) and the upper frame (01) and the lower frame (02) to a moment;
7) the visual axis of the micro-alignment telescope (34) is coincided with the optical axis of a lower frame reticle (52) on a lower frame (02) by adjusting the postures of the micro-alignment telescope (34) and the 45-degree reflecting mirror group (32);
8) the position and the posture of the upper frame (01) are adjusted through the pitching fine adjustment mechanism (24) and the translation fine adjustment mechanism (25), so that the optical axis of an upper frame reticle (42) on the upper frame (01) is superposed with the visual axis of the micrometric collimation telescope (34);
9) monitoring the coincidence degree of the optical axis of the upper frame reticle (42) and the optical axis of the lower frame reticle (52) in the glue curing process, and returning to the step 8) for readjustment if the coincidence degree changes;
10) unloading the supporting force on the pitching fine adjustment mechanism (24) after the glue is cured, rechecking the coincidence degree of the optical axis of the upper frame reticle (42) and the optical axis of the lower frame reticle (52), and repairing if the coincidence degree changes; and if the contact ratio is not changed, the truss body is assembled.
4. The carbon fiber truss fuselage assembly and adjustment process based on gluing error compensation of claim 3, wherein:
the step 5) is specifically carried out according to the following steps:
5.1) taking out the carbon fiber rod (031) and the metal joint (032), and finely wiping the assembly surface of the carbon fiber rod (031) and the metal joint (032) by using a special solution;
and 5.2) uniformly coating the metal joint (032) with glue, embedding steel wires in the glue or mixing micro glass beads in the glue, and then sleeving the carbon fiber rod (031) and the metal joint (032) together.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110312689.1A CN112965324B (en) | 2021-03-24 | 2021-03-24 | Carbon fiber truss body assembling and adjusting device and process based on gluing error compensation |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110312689.1A CN112965324B (en) | 2021-03-24 | 2021-03-24 | Carbon fiber truss body assembling and adjusting device and process based on gluing error compensation |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112965324A CN112965324A (en) | 2021-06-15 |
| CN112965324B true CN112965324B (en) | 2022-02-18 |
Family
ID=76278902
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110312689.1A Active CN112965324B (en) | 2021-03-24 | 2021-03-24 | Carbon fiber truss body assembling and adjusting device and process based on gluing error compensation |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112965324B (en) |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104034315A (en) * | 2014-06-30 | 2014-09-10 | 中国科学院长春光学精密机械与物理研究所 | Assembling method of truss structure of ultra-long focal length remote sensing camera |
| CN104536113A (en) * | 2014-12-30 | 2015-04-22 | 中国科学院长春光学精密机械与物理研究所 | High-specific stiffness supporting structure of space optical remote sensor |
| CN104832511A (en) * | 2015-04-21 | 2015-08-12 | 中国科学院长春光学精密机械与物理研究所 | Method for controlling thickness of optical remote sensor space truss rod adhesive glue layer |
| 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 |
| CN206177256U (en) * | 2016-11-02 | 2017-05-17 | 中北大学 | Deep hole straightness accuracy detection device |
| CN110231689A (en) * | 2019-06-11 | 2019-09-13 | 中国科学院长春光学精密机械与物理研究所 | Push away the ultralight carbon fiber lattice supporting framework of solidifying integrated high-resolution space optics load |
| CN110764338A (en) * | 2019-10-30 | 2020-02-07 | 长光卫星技术有限公司 | Light-duty space camera owner load device that possesses focusing function |
| CN112032521A (en) * | 2020-08-26 | 2020-12-04 | 中国科学院西安光学精密机械研究所 | Truss supporting structure |
| CN112433338A (en) * | 2020-11-27 | 2021-03-02 | 中国科学院西安光学精密机械研究所 | Swing mirror assembly, swing mirror assembly assembling and adjusting system and assembling and adjusting method |
-
2021
- 2021-03-24 CN CN202110312689.1A patent/CN112965324B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104034315A (en) * | 2014-06-30 | 2014-09-10 | 中国科学院长春光学精密机械与物理研究所 | Assembling method of truss structure of ultra-long focal length remote sensing camera |
| CN104536113A (en) * | 2014-12-30 | 2015-04-22 | 中国科学院长春光学精密机械与物理研究所 | High-specific stiffness supporting structure of space optical remote sensor |
| CN104832511A (en) * | 2015-04-21 | 2015-08-12 | 中国科学院长春光学精密机械与物理研究所 | Method for controlling thickness of optical remote sensor space truss rod adhesive glue layer |
| 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 |
| CN206177256U (en) * | 2016-11-02 | 2017-05-17 | 中北大学 | Deep hole straightness accuracy detection device |
| CN110231689A (en) * | 2019-06-11 | 2019-09-13 | 中国科学院长春光学精密机械与物理研究所 | Push away the ultralight carbon fiber lattice supporting framework of solidifying integrated high-resolution space optics load |
| CN110764338A (en) * | 2019-10-30 | 2020-02-07 | 长光卫星技术有限公司 | Light-duty space camera owner load device that possesses focusing function |
| CN112032521A (en) * | 2020-08-26 | 2020-12-04 | 中国科学院西安光学精密机械研究所 | Truss supporting structure |
| CN112433338A (en) * | 2020-11-27 | 2021-03-02 | 中国科学院西安光学精密机械研究所 | Swing mirror assembly, swing mirror assembly assembling and adjusting system and assembling and adjusting method |
Non-Patent Citations (2)
| Title |
|---|
| 同轴空间相机碳纤维复合材料桁架结构的研制;张雷，姚劲松，贾学志;《光学精密工程》;20120915;第20卷(第9期);第2.2节，4.1节，附图5 * |
| 空间相机桁架式支撑结构的集成优化设计;袁健，沙巍，陈长征;《红外与激光工程》;20151215;第44卷(第12期);3661-3665 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN112965324A (en) | 2021-06-15 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN112946852B (en) | Primary and secondary mirror system adjustment method | |
| CN104898252A (en) | Aerial camera Cassegrain primary and secondary mirror supporting structure | |
| CN103969788A (en) | Lateral flexible supporting structure of space optical remote sensor circulator reflector | |
| CN111650717B (en) | Surface-shaped high-stability reflector assembly and assembling method thereof | |
| CN113917669B (en) | Off-axis reflection type telescopic system and installation and adjustment detection device and method thereof | |
| CN109586045B (en) | Lightweight Ka frequency band reflecting surface antenna and manufacturing method thereof | |
| CN111650716B (en) | Surface-shaped high-stability reflector and assembling method thereof | |
| CN111624729B (en) | Fast reflector | |
| CN109263057A (en) | A kind of bonding and assembly method of precision carbon fiber truss | |
| CN111121713B (en) | Method for establishing process reference for precision measurement of outer bearing barrel type structure cabin | |
| CN112965324B (en) | Carbon fiber truss body assembling and adjusting device and process based on gluing error compensation | |
| CN115308874A (en) | Non-interference gravity unloading mechanism of large-diameter reflector | |
| CN112433338B (en) | Swing mirror assembly, swing mirror assembly assembling and adjusting system and assembling and adjusting method | |
| CN112269237B (en) | Large objective lens centering structure for airborne sighting device | |
| CN115826176A (en) | Object lens centering structure of continuous zooming thermal infrared imager and assembling and adjusting method | |
| CN102556367A (en) | Method for assembling structures of light product platforms | |
| CN115728905A (en) | Reflector surface shape regulating and controlling device | |
| CN112130277A (en) | Flexible supporting structure suitable for space camera reflector | |
| CN114280875B (en) | Stress-free connecting device for optical-mechanical structure of space camera and assembling method | |
| CN108286639B (en) | Coaxial optical dual-camera splicing structure | |
| CN117406375B (en) | Flexibly supported optical lens and assembly method thereof | |
| CN112246561B (en) | Radial adjusting and fastening device for machining of ultra-precise optical grazing incidence reflector | |
| CN109407334B (en) | On-orbit blocking mirror assembling device | |
| CN109752903B (en) | Truss structure for remote sensing camera and assembling method thereof | |
| CN114211760B (en) | System and method for measuring and adjusting satellite carbon fiber truss cementing assembly gap |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |