CN103795907B - The main frame assembling device of space optical camera and assembly method - Google Patents

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

Main frame assembly device and assembly method of space optical camera

technical field

The invention relates to the field of aerospace technology, in particular to a main frame assembling device and an assembling method of a space optical camera.

Background technique

The main frame of the space optics camera is an important part of the space optics camera. Each reflector assembly and imaging sensor in the space optical camera needs to be installed on the main frame of the camera according to the optical position. As shown in Figure 1, the main frame of the camera is composed of a front frame 11, a rear frame 12, a plurality of carbon fiber struts 13 and a plurality of strut joints 14, when assembling the main frame of the camera, the rear frame 12 is first placed on the platform, Then all carbon fiber poles 13 two ends are coated with epoxy resin glue and glued with pole joints 14, as shown in Figure 2, the two ends of carbon fiber poles 13 are all glued with pole joints 14, utilize epoxy resin Due to the long curing time of the glue, adjust the positional relationship between the strut joint 14 and the front frame 11 and the rear frame 12 respectively, and then connect the strut joint 14 to the front frame 11 and the rear frame 12 with screws, and let it stand for epoxy The resin glue cures.

At present, the above-mentioned assembly method is used for the assembly of the main frame of the space optical camera. However, there are certain installation errors in the above-mentioned assembly process: as shown in FIG. There is a gap of 0.5 mm on one side, and there is a gap of 0.2 mm on one side between the carbon fiber strut 13 and the strut joint 14 for filling with epoxy resin glue. The poor control of these two kinds of installation errors will lead to the decrease of the position accuracy of the main frame of the camera, reduce the installation accuracy of each mirror assembly, and in severe cases will cause the position interference between the mirror assembly and the main frame of the camera; The adhesive layer between the rod 13 and the rod joint 14 is pressed to one side, resulting in an uneven adhesive layer, which will cause residual stress in the main frame of the camera. The main frame will have a certain residual stress release, which will change the optical position between the mirror components, reduce the stability of the main frame structure of the camera, and further reduce the imaging quality of the space optical camera.

Contents of the invention

In order to solve the problems of low assembly accuracy and poor structural stability of the main frame of the camera in the existing method for assembling the main frame of the space optical camera, thereby reducing the imaging quality of the space optical camera, the present invention provides a simple structure that can effectively improve the main frame of the camera. A main frame assembly device of a space optical camera with installation accuracy and structural stability and a high-precision space optical camera main frame assembly method realized by the device.

The technical scheme that the present invention adopts for solving technical problems is as follows:

The main frame assembly device of the space optics camera, including:

The fixed frame is welded by the square structure and the U-shaped structure through the hollow square steel pipe;

The screw fine-tuning mechanism, the screw leveling mechanism and the pressing mechanism installed on the square structure, the screw fine-tuning mechanism and the screw leveling mechanism are used to adjust the six degrees of freedom of the front frame, and the pressing mechanism is used to adjust the front frame The frame is fixed on the zigzag structure;

The connecting seat installed on the U-shaped structure is used for fixing the rear frame on the U-shaped structure.

The zigzag structure is formed by sequential welding of four hollow square steel pipes.

The U-shaped structure is formed by welding three hollow square steel pipes.

There are four connecting seats, two of which are symmetrically arranged on the U-shaped ends of the U-shaped structure, and the other two are symmetrically arranged on the top of the U-shaped structure.

There are six spiral fine-tuning mechanisms, four of which are symmetrically arranged on two opposite sides of the zigzag structure, and the remaining two are symmetrically arranged on the other two opposite sides of the zigzag structure.

There are three spiral leveling mechanisms, and the three spiral leveling mechanisms are respectively arranged on three sides of the zigzag structure.

The main frame assembly method of the space optics camera comprises the following steps:

Step 1. Place the rear frame on the platform, put the U-shaped structure of the fixed frame on the rear frame, and fix the rear frame and the U-shaped structure of the fixed frame together through the connecting seat;

Step 2. Place the front frame on the square structure of the fixed frame, adjust the front frame with six degrees of freedom through the screw fine-tuning mechanism and the spiral leveling mechanism, and press the front frame and the square structure of the fixed frame tightly through the pressing mechanism fixed;

Step 3: Set the carbon fiber strut and the strut joint together, and then carry out trial assembly with the front frame and the rear frame, fine-tune the connection position between the strut joint and the front frame and the rear frame, so that the carbon fiber strut can be placed on the strut Rotation within the joint;

Step 4. After the trial assembly of each group of carbon fiber struts and strut joints is completed, remove the carbon fiber struts and strut joints one by one, apply epoxy glue, and reassemble and fix them with the front frame and rear frame;

Step 5. After the main frame of the camera is assembled, use a laser rangefinder to recheck the positional relationship between the front frame and the rear frame. If there is an out-of-tolerance, fine-tune it through the screw fine-tuning mechanism and the screw leveling mechanism until The position accuracy of the front frame and the rear frame meets the design requirements of the main frame of the space optical camera, and the epoxy resin glue is left to be cured.

In the second step, the specific steps of adjusting the six degrees of freedom of the front frame through the screw fine-tuning mechanism and the screw leveling mechanism are: using a laser range finder to measure the three high-precision orthogonal detection reference planes of the front frame and the rear frame respectively. The actual position relationship, the deviation between the theoretical position and the actual position is obtained through calculation, the azimuth and two horizontal translations of the front frame of the camera main frame are fine-tuned through the screw fine-tuning mechanism, and the camera main frame is fine-tuned through the screw leveling mechanism. The front frame of the frame is fine-tuned to the three degrees of freedom of the pitch angle, yaw angle, and translation in the height direction. After several iterations of measurement and adjustment, the position accuracy of the front frame and the rear frame is adjusted to the design requirements of the main frame of the space optical camera. .

The beneficial effects of the present invention are:

Using the device of the present invention to assemble the main frame of the camera can ensure that the positional accuracy between the front frame and the rear frame meets the design requirements, improves the assembly accuracy of the main frame of the camera, and the positional accuracy of the main frame of the camera meets the design requirements, reducing the optical installation of the mirror. The difficulty of adjustment; each carbon fiber rod and rod joint can be assembled independently, reducing the difficulty of on-site operation; the adhesive layer between the carbon fiber rod and the rod joint is evenly distributed, and the main frame of the camera will not produce residual stress during the assembly process. The structural stability of the main frame of the camera is improved. The invention can be used in fields such as aerospace and frame structure assembly of precision structures.

Description of drawings

Fig. 1 is a structural schematic diagram of the main frame of the camera;

Fig. 2 is a cross-sectional view of a carbon fiber strut and a strut joint bonded by epoxy resin;

Fig. 3 is a schematic structural view of the main frame assembly device of the space optical camera of the present invention;

Fig. 4 is the three-dimensional structure schematic diagram after adopting the device of the present invention to assemble the main frame of the space optical camera;

Fig. 5 is a view in the opposite direction to the schematic diagram of the three-dimensional structure shown in Fig. 4;

Fig. 6 is the right view of the three-dimensional structural schematic diagram shown in Fig. 5;

FIG. 7 is a front view of the schematic three-dimensional structure shown in FIG. 5 .

In the figure: 11, front frame, 12, rear frame, 13, carbon fiber strut, 14, strut joint, 21, fixed frame, 22, connecting seat, 23, screw fine-tuning mechanism, 24, screw leveling mechanism, 25, Compression mechanism.

detailed description

The present invention will be described in further detail below in conjunction with the accompanying drawings.

As shown in FIG. 3 , the main frame assembly device of the space optical camera of the present invention includes a fixed frame 21 , a connecting seat 22 , a screw fine-tuning mechanism 23 , a screw leveling mechanism 24 and a pressing mechanism 25 .

According to the different structural forms of the main frame of the camera and the characteristics of each adjustment mechanism and fixed structure, the fixed frame 21 is designed as an upper and lower two-layer structure. The structure is a U-shaped structure welded by three hollow square steel pipes, and the mouth-shaped structure and the U-shaped structure are welded together by four hollow square steel pipes.

Four connecting seats 22 are installed on the U-shaped structure of the fixed frame 21, two of which are symmetrically arranged on the hollow square steel pipes at both ends of the U-shaped structure, and the remaining two connecting seats 22 are symmetrically arranged on the U-shaped structure On the hollow square steel pipe at the top, the connecting seat 22 is used to connect the rear frame 12 of the camera main frame with the U-shaped structure of the fixed frame 21.

Six spiral fine-tuning mechanisms 23 are installed on the square structure of the fixed frame 21, wherein four spiral fine-tuning mechanisms 23 are symmetrically arranged on two opposite side hollow square steel pipes of the square structure, and the remaining two spiral fine-tuning mechanisms 23 are symmetrically arranged on On the other two opposite hollow square steel pipes of the zigzag structure, six helical fine-tuning mechanisms 23 can fine-tune the front frame 11 of the main frame of the camera in azimuth and three degrees of freedom in translation in two horizontal directions.

Three spiral leveling mechanisms 24 are installed on the square structure of the fixed frame 21, and the three spiral leveling mechanisms 24 are respectively arranged on three hollow square steel pipes of the square structure, and the three spiral leveling mechanisms 24 can adjust the main frame of the camera The front frame 11 is fine-tuned in three degrees of freedom of pitch angle, yaw angle and height direction translation. The front frame 11 is fine-tuned by the screw fine-tuning mechanism 23 and the screw leveling mechanism 24 , and then the front frame 11 and the square structure of the fixed frame 21 are fixed together by four pressing mechanisms 25 .

As shown in Fig. 4, Fig. 5, Fig. 6 and Fig. 7, the method for assembling the main frame of the space optical camera using the device of the present invention is realized by the following steps:

(1) Place the rear frame 12 of the main frame of the camera on the platform, and at the same time put the U-shaped structure of the fixed frame 21 on the rear frame 12, and fix the U-shaped structure of the rear frame 12 and the fixed frame 21 on the Together;

(2) Place the front frame 11 of the camera main frame on the square structure of the fixed frame 21, and adjust the front frame 11 with six degrees of freedom through the screw fine-tuning mechanism 23 and the screw leveling mechanism 24:

Use the laser range finder to measure the actual position relationship of the three high-precision orthogonal detection reference planes of the front frame 11 and the rear frame 12 respectively, and obtain the deviation between the theoretical position and the actual position through calculation, and adjust the front frame of the main frame of the camera through the screw fine-tuning mechanism 23 11 fine-tuning the three degrees of freedom of the azimuth and two horizontal translations, and fine-tuning the three degrees of freedom of the front frame 11 of the camera main frame through the screw leveling mechanism 24, the pitch angle, the yaw angle and the translation of the height direction, After several iterative measurements and adjustments, the position accuracy of the front frame 11 and the rear frame 12 is adjusted to the design requirements of the main frame of the space optical camera, which can ensure the distance between the front frame 11 and the rear frame 12 during the entire assembly process. The positional relationship will not change, ensuring installation accuracy;

(3) After adjusting the positions of the front frame 11 and the rear frame 12, press and fix the square structure of the front frame 11 and the fixed frame 21 through the pressing mechanism 25;

(4) Set the carbon fiber pole 13 and the pole joint 14 of the main frame of the camera together, and then carry out trial assembly with the front frame 11 and the rear frame 12, and fine-tune the distance between the pole joint 14 and the front frame 11 and the rear frame 12 The connection position ensures that the carbon fiber strut 13 can be easily rotated in the strut joint 14 without any stagnation or tension;

(5) After the trial assembly of each group of carbon fiber struts 13 and strut joints 14 is completed, remove the carbon fiber struts 13 and strut joints 14 one by one, apply epoxy glue, and reconnect the front frame 11 and the rear frame 12. Assembly fixed;

(6) After the main frame of the camera is assembled, recheck the positional relationship between the front frame 11 and the rear frame 12 with a laser rangefinder. Carry out fine-tuning until the position accuracy of the front frame 11 and the rear frame 12 meets the design requirements of the main frame of the space optical camera;

(7) Wait for the epoxy resin to cure.

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.