CN112265656B - Packaging and containing type on-orbit assembly device and method for long-length antenna - Google Patents
Packaging and containing type on-orbit assembly device and method for long-length antenna Download PDFInfo
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- CN112265656B CN112265656B CN202011009838.9A CN202011009838A CN112265656B CN 112265656 B CN112265656 B CN 112265656B CN 202011009838 A CN202011009838 A CN 202011009838A CN 112265656 B CN112265656 B CN 112265656B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G4/00—Tools specially adapted for use in space
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P19/00—Machines for simply fitting together or separating metal parts or objects, or metal and non-metal parts, whether or not involving some deformation; Tools or devices therefor so far as not provided for in other classes
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Abstract
The integrated storage type on-track assembly device and method facing the long-length antenna are characterized in that a one-way transmission mechanism, a two-way transmission mechanism and an assembly component are fixedly arranged on a supporting frame; each space-based radar board unit is fixedly connected with a one-way transmission mechanism respectively, the one-way transmission mechanism drives the plurality of space-based radar board units to move synchronously, and a limiting structure matched with the space-based radar board units is arranged on the one-way transmission mechanism and used for limiting the torsion and the shaking of the space-based radar board units; the bidirectional transmission mechanism drives the space-based radar plate unit positioned at the bottom of the laminated structure to be coplanar with the space-based radar plate unit positioned at the second from last at the bottom of the laminated structure, or drives a plurality of spliced space-based radar plate units to move reversely along the splicing direction; the assembly component is used for splicing and fixing the space-based radar panel unit positioned at the bottom of the laminated structure and the space-based radar panel unit positioned at the second from last at the bottom of the laminated structure into an integral plane structure. The invention has the characteristics of simple system composition, expandability, strong realizability and the like.
Description
Technical Field
The invention relates to a large-length antenna-oriented container-type on-orbit assembly device and method, and belongs to the technical field of antenna on-orbit assembly.
Background
The space-based radar can cover the world, is not influenced by factors such as regions, politics, strategies and the like, can realize various advantages such as all-weather continuous monitoring in the day and night and the like, and is widely valued by various countries.
However, due to the influence of rocket thrust, fairing envelope and mechanism complexity, the current deployment mechanism is difficult to meet the construction requirements of large-area and large-span space structures required by projects such as future deep space exploration, astronomical observation and space-based radar.
The on-orbit assembly is to assemble basic units such as a structural module, a functional module and the like which are subjected to single/multiple times of orbit input into a desired large-scale space system in sequence, and comprises on-orbit connection, construction and combination, on-orbit assembly and reconstruction of a spacecraft from the module to the functional module, on-orbit butt joint of large-scale independent cabin sections, and construction of a larger-scale large-scale space structure, and the on-orbit assembly has the characteristics of high structural efficiency, strong expansibility, gradual upgrading and the like.
Through searching the on-rail assembly technology, the invention patents of CN201720465377.3 space truss on rail assembly system using space robot, etc., all need the cooperation of space assembly robot or manipulator to realize, and the realization difficulty and cost are great.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the invention overcomes the defects of the prior art, provides a large-length antenna-oriented container storage type on-track assembly device and a method, wherein an antenna plate is stored in a container body with positioning and pressing functions by adopting a modular frame with consistent external interfaces to be transmitted into a track, and compared with an antenna transmitted by a traditional unfolding mechanism in a folding state, the device has the advantages of smaller transmitting volume, higher rigidity, realization of ordered transportation and positioning of the antenna plate through a two-degree-of-freedom motion platform system after the antenna plate is inserted into the track, and realization of high-precision positioning and quick linking of the antenna plate through a single-degree-of-freedom electric push rod and an interface on the antenna plate frame. The system is simple and reliable, low in cost and low in implementation difficulty.
The technical scheme of the invention is as follows:
towards large length antenna's collection dress formula of accomodating on-orbit assembly device, include: the device comprises a supporting frame, a one-way transmission mechanism, a two-way transmission mechanism and an assembly component;
a one-way transmission mechanism, a two-way transmission mechanism and an assembly component are fixedly arranged on the supporting frame;
the plurality of space-based radar plate units are stacked to form a stacked structure; each space-based radar board unit is fixedly connected with a one-way transmission mechanism respectively, the one-way transmission mechanism drives the plurality of space-based radar board units to synchronously move linearly along the normal direction of the board surface, and meanwhile, a limiting structure matched with the space-based radar board units is arranged on the one-way transmission mechanism to limit the torsion and the shaking of the space-based radar board units;
the bidirectional transmission mechanism drives the space-based radar plate unit positioned at the bottom of the laminated structure to be coplanar with the space-based radar plate unit positioned at the second from last at the bottom of the laminated structure, or drives a plurality of spliced space-based radar plate units to move reversely along the splicing direction;
the assembly component is used for splicing and fixing the space-based radar panel unit positioned at the bottom of the laminated structure and the space-based radar panel unit positioned at the second from last at the bottom of the laminated structure into an integral plane structure.
The device also comprises a fixed rope and an initiating explosive device;
before the space-based radar board units are assembled on the rails, a plurality of stacked space-based radar board units are fixedly connected through fixed cables and initiating explosive devices.
The unidirectional transmission mechanism comprises: the track motor, the track and the limiting guide rail are driven;
a plurality of tracks and limit guide rails are fixedly arranged on the support frame along the stacking direction;
a plurality of limit stops protruding outwards are arranged on the two symmetrical side walls of the space-based radar plate unit, and the tooth structure of the crawler belt is matched with the limit stops of the space-based radar plate unit; the driving crawler motor is used for driving a crawler to drive the space-based radar board unit to move from the top to the bottom along the stacking direction;
a plurality of limiting blocks protruding outwards are arranged on the two symmetrical side walls of the space-based radar panel unit, the cross sections of the limiting blocks are triangular, and the directions of the oblique sides of the limiting blocks on the two symmetrical side walls are opposite; and the limiting structure arranged on the limiting guide rail is matched with the limiting block of the space-based radar board unit.
The bidirectional transfer mechanism includes: the device comprises a driving friction wheel, a pressing wheel, a driving assembly and a positioning and limiting structure;
the driving assembly is fixedly connected with the space-based radar board unit positioned at the bottom of the laminated structure by using a magnet and moves to an assembling position;
the driving friction wheel is matched with the pressing wheel to drive the space-based radar board unit to move parallel to the board surface;
the positioning and limiting structure is used for limiting the movement position of the space-based radar board unit.
The drive assembly includes: the device comprises a cross slide rail, a first electric push rod, an electromagnetic chuck and an attached iron sheet;
the electromagnetic chuck is fixedly connected with a first electric push rod, and the first electric push rod can slide along the cross-shaped sliding rail;
the cross slide rail is fixedly connected with the supporting frame;
iron sheet grooves d for installing attached iron sheets are formed in the two symmetrical side walls of the space-based radar plate unit;
the electromagnetic chuck is matched with an attached iron sheet on the space-based radar board unit, so that the first electric push rod drives the space-based radar board unit to move to an assembly position.
The fitting assembly includes: the second electric push rod, the screw assembly, the base assembly, the pressing screw device and the limiting baffle plate;
the second electric push rod and the limit baffle are fixedly connected with the supporting frame; the pressing screw device is fixedly connected with the second electric push rod;
at the assembly position, the lap joint edges of the two space-based radar plate units are aligned through a limiting baffle;
the space-based radar board unit positioned below is fixedly provided with a base assembly, and the space-based radar board unit positioned above is fixedly provided with a screw assembly;
and the second electric push rod drives the pressing screw device to press the space-based radar board units positioned above to move downwards until the base component and the screw component are assembled in place, and the two space-based radar board units are spliced and fixed into an integral plane structure.
A raised line and a positioning conical column are processed on the lap joint edge of the space-based radar panel unit to serve as a positioning limiting structure;
the positioning and limiting structures at the lap joint edges of the two space-based radar plate units are matched with each other.
The method for assembling by using the container-type on-track assembling device for the long-length antenna comprises the following steps:
1) a raised line and a positioning conical column are processed on the lap joint edge of the space-based radar panel unit to serve as a positioning limiting structure;
2) the plurality of space-based radar plate units are stacked to form a stacked structure; each space-based radar board unit is fixedly connected with a one-way transmission mechanism;
3) before the space-based radar board units are assembled on the rails, a plurality of stacked space-based radar board units are fixedly connected by using fixed ropes and initiating explosive devices;
4) when the space-based radar board unit is assembled on the rail, unlocking and blasting the fixed rope and the initiating explosive device;
5) the one-way transmission mechanism drives the plurality of space-based radar plate units to synchronously move downwards linearly along the direction of the normal line of the plate surface;
6) the bidirectional transmission mechanism drives the space-based radar board unit positioned at the bottom of the laminated structure to be coplanar with the space-based radar board unit positioned at the second from last at the bottom of the laminated structure;
9) the driving assembly drives the space-based radar board unit to move to an assembling position;
10) the second electric push rod drives the pressing screw device to press the upper space-based radar board unit to move downwards until a base component of the lower space-based radar board unit and a screw component of the upper space-based radar board unit are assembled in place, and the two space-based radar board units are spliced and fixed into an integral plane structure;
11) and repeating the steps 5) -10) until the splicing work of the multiple sky-based radar plate units on the single side is completed, and driving the multiple sky-based radar plate units formed by splicing the single side to move in the opposite direction of the splicing direction by using a bidirectional transmission mechanism to complete the splicing work.
Compared with the prior art, the invention has the beneficial effects that:
1) with reference to fig. 1, the invention fully utilizes the space of the radar cabin and can carry more space-based radar boards. In addition, the design of the modularized space facility system is realized, the spacecraft is integrally decomposed and optimized into a plurality of relatively independent functional units, and the problems of coupling and simplification among the functional units are solved.
2) With reference to fig. 2, the design of the module unit connection technology of the invention refers to the mortise and tenon structure of the ancient Chinese building, and ensures higher connection strength. And the configuration design of the module units is unified, and the installation efficiency of the module units is improved.
3) Compared with other foreign technical schemes, the invention has relatively simple structure and does not need complex mechanisms such as mechanical arms and the like, thereby greatly improving the running speed of the whole device.
4) Referring to fig. 4, the present invention provides an interface technology with fast turn-on capability. The connection interface between the functional module and the structural module is designed to be universal and plug-and-play, so that the problems of reliable connection and quick conduction between module units are solved, and the module unit is large in tolerance and easy to operate.
5) The invention designs a plurality of limiting devices, and ensures high precision of the global and local system in the process of on-orbit assembly and operation in a complex space environment.
Drawings
FIG. 1 is a view of the construction of the assembly of the space-based radar of the present invention;
FIG. 2 is a schematic diagram of a space-based radar panel unit according to the present invention;
FIG. 3 is a diagram of the motion platform system of the present invention;
FIG. 4 is a block diagram of a quick connect system for a panel unit according to the present invention;
FIG. 5 is a block diagram of the board drive system of the present invention;
FIG. 6 illustrates the initiating explosive device of the present invention destroying the fixing cable;
FIG. 7 is the conveyance of a first plate according to the present invention;
FIG. 8 is a second sheet transport of the present invention;
FIG. 9 is a connection of a first plate to a second plate according to the present invention;
FIG. 10 illustrates the movement of two plates when the present invention is connected;
FIG. 11 shows the other plates being moved downward by the track of the present invention;
FIG. 12 shows the present invention after all panels have been connected;
FIG. 13 shows the body of the invention moved to the center of the radar plate.
Detailed Description
The invention is described in further detail below with reference to the figures and the detailed description.
The invention relates to a large-length antenna oriented container storage type on-orbit assembly technology, which has the characteristics of simple system composition, reliable implementation, high assembly precision, expandability, strong realizability and the like.
Towards large length antenna's collection dress formula of accomodating on-orbit assembly device, include: the device comprises a supporting frame 7, a one-way transmission mechanism, a two-way transmission mechanism and an assembly component;
a one-way transmission mechanism, a two-way transmission mechanism and an assembly component are fixedly arranged on the supporting frame 7;
a plurality of space-based radar plate units 8 are stacked to form a stacked structure; each space-based radar board unit 8 is fixedly connected with a one-way transmission mechanism respectively, the one-way transmission mechanism drives the plurality of space-based radar board units 8 to synchronously move linearly along the normal direction of the board surface, and meanwhile, a limiting structure matched with the space-based radar board units 8 is arranged on the one-way transmission mechanism to limit the torsion and the shaking of the space-based radar board units 8;
the bidirectional transmission mechanism drives the space-based radar plate unit 8 positioned at the bottom of the laminated structure to be coplanar with the space-based radar plate unit 8 positioned at the second last of the laminated structure, or drives the spliced and formed plurality of space-based radar plate units 8 to move reversely along the splicing direction;
the assembly component is used for splicing and fixing the space-based radar panel unit 8 positioned at the bottom of the laminated structure and the space-based radar panel unit 8 positioned at the second from last at the bottom of the laminated structure into an integral plane structure.
The invention relates to a container-type on-orbit assembly device for a long-length antenna, which further comprises a fixed rope and an initiating explosive device 10. The initiating explosive device 10 may be an initiating explosive device or a non-initiating explosive unlocking element, such as a hot knife or a fuse.
Before the space-based radar board units 8 are assembled on the rails, a plurality of stacked space-based radar board units 8 are fixedly connected through the fixed cables and the initiating explosive devices 10.
The unidirectional transmission mechanism comprises: the crawler motor 5, the crawler 6 and the limiting guide rail 9 are driven;
a plurality of crawler belts 6 and limiting guide rails 9 are fixedly arranged on the supporting frame 7 along the stacking direction;
a plurality of limit stops 13 protruding outwards are arranged on two symmetrical side walls of the space-based radar plate unit 8, and the tooth structure of the crawler 6 is matched with the limit stops 13 of the space-based radar plate unit 8; the driving track motor 5 is used for driving the track 6 to drive the space-based radar board unit 8 to move from top to bottom along the stacking direction;
a plurality of limiting blocks 14 protruding outwards are arranged on two symmetrical side walls of the space-based radar panel unit 8, the cross sections of the limiting blocks 14 are triangular, and the directions of bevel edges of the limiting blocks 14 on the two symmetrical side walls are opposite; the limiting structure arranged on the limiting guide rail 9 is matched with a limiting block 14 of the space-based radar board unit 8.
The bidirectional transfer mechanism includes: the device comprises a driving friction wheel 1, a pressing wheel 3, a driving assembly 11 and a positioning and limiting structure;
the driving assembly 11 is fixedly connected with the space-based radar board unit 8 at the bottom of the laminated structure by using a magnet and moves to an assembling position;
the driving friction wheel 1 is matched with the pressing wheel 3, and the space-based radar board unit 8 is driven to move parallel to the board surface;
the positioning and limiting structure is used for limiting the movement position of the space-based radar board unit 8.
The drive assembly 11 includes: a cross slide rail 15, a first electric push rod 16, an electromagnetic chuck 17 and an attached iron sheet 18;
the electromagnetic chuck 17 is fixedly connected with a first electric push rod 16, and the first electric push rod 16 can slide along the cross slide rail 15;
the cross slide rail 15 is fixedly connected with the supporting frame 7;
iron sheet grooves d for installing the attached iron sheets 18 are formed in the two symmetrical side walls of the space-based radar plate unit 8;
the electromagnetic chuck 17 is matched with an attached iron sheet 18 on the space-based radar board unit 8, so that the first electric push rod 16 drives the space-based radar board unit 8 to move to an assembly position.
The fitting assembly includes: the second electric push rod 4, a screw component 20, a base component 19, a pressing screw device 21 and a limit baffle 22;
the second electric push rod 4 and the limit baffle 22 are fixedly connected with the support frame 7; the pressing screw device 21 is fixedly connected with the second electric push rod 4;
in the assembly position, the overlapping edges of the two space-based radar plate units 8 are aligned through the limiting baffle 22;
the lower space-based radar board unit 8 is fixedly provided with a base assembly 19, and the upper space-based radar board unit 8 is fixedly provided with a screw assembly 20;
the second electric push rod 4 drives the pressing screw device 21 to press the space-based radar board units 8 on the upper side to move downwards until the base component 19 and the screw component 20 are assembled in place, and the two space-based radar board units 8 are spliced and fixed into an integral plane structure.
A raised line b and a positioning conical column c are processed on the lap joint edge of the space-based radar plate unit 8 to serve as positioning limiting structures;
the positioning and limiting structures at the lap joint edges of the two space-based radar plate units 8 are matched with each other.
The method for assembling by using the container-type on-track assembling device for the long-length antenna comprises the following steps:
1) a raised line b and a positioning conical column c are processed on the lap joint edge of the space-based radar plate unit 8 to serve as positioning limiting structures;
2) a plurality of space-based radar plate units 8 are stacked to form a stacked structure; each space-based radar board unit 8 is fixedly connected with a one-way transmission mechanism;
3) before the space-based radar board units 8 are assembled on the rails, a plurality of stacked space-based radar board units 8 are fixedly connected by using fixed ropes and initiating explosive devices 10;
4) when the space-based radar board unit 8 is assembled on the rail, the fixed rope and the initiating explosive device 10 are unlocked and blasted;
5) the one-way transmission mechanism drives the plurality of space-based radar plate units 8 to synchronously move downwards linearly along the direction of the normal line of the plate surface;
6) the bidirectional transmission mechanism drives the space-based radar board unit 8 positioned at the bottom of the laminated structure to be coplanar with the space-based radar board unit 8 positioned at the second last from the bottom of the laminated structure;
9) the driving component 11 drives the space-based radar board unit 8 to move to the assembling position;
10) the second electric push rod 4 drives the pressing screw device 21 to press the upper space-based radar board unit 8 to move downwards until the base component 19 of the lower space-based radar board unit 8 and the screw component 20 of the upper space-based radar board unit 8 are assembled in place, and the two space-based radar board units 8 are spliced and fixed into an integral plane structure;
11) and (5) repeating the steps and (10) until the splicing work of the plurality of sky-based radar plate units 8 on one side is completed, and driving the plurality of sky-based radar plate units 8 which are spliced and formed on one side to move in the opposite direction of the splicing direction by using a bidirectional transmission mechanism to complete the splicing work.
Examples
1. Integrated device design and construction thereof
The invention provides a large-length antenna oriented container storage type on-orbit assembly device, which comprises: support frame 7, unidirectional transport mechanism, bidirectional transport mechanism, assembly subassembly. A certain number of space-based radar plate units 8 are directly stacked, the movement of the space-based radar plate units in the horizontal direction is limited through limiting guide rails 9, and the space-based radar plate units are fixed through fixing ropes 10 before the whole device works. The remaining components are fixed directly to the support frame 7 as shown in figure 1.
2. Design of space-based radar panel unit
The space-based radar board unit 8 is composed of a board main body 12, a limit stop 13 and a limit block 14. The main board body 12 is provided with a quick connection screw mounting hole a, a convex strip b, a positioning conical column c and an iron sheet groove d. As shown in fig. 2.
The limit stop 13 and the limit block 14 are fixed on two sides of the space-based radar plate main body 12 through screws and are used for assisting the movement and fixation of the space-based radar plate; iron sheet grooves d are formed in the two sides of the plate, and iron sheets are embedded in the iron sheet grooves d and used for being matched with the electromagnetic chuck of the motion platform 11 to work; the convex strip b and the positioning conical column c are used for assisting the positioning of the connection of the two plates.
3. Motion platform system design
The driving assembly 11 is composed of a cross slide rail 15, a first electric push rod 16, an electromagnetic chuck 17 and an attached iron sheet 18. As shown in fig. 3.
The cross slide rail 15 is fixed on the supporting frame 7; the first electric push rod 16 is fixed on the cross slide rail 15; the first electric putter 16 can be moved with a certain accuracy by means of the cross slide 15; the electromagnetic chuck 17 is fixed to a ram head of the first electric ram 16 and is linearly movable by the first electric ram 16. The attaching iron piece 18 is fixed in the iron piece groove d of the side face of the space-based radar panel unit. When the moving platform works, the electromagnetic chuck 17 sucks the attached iron sheet 18 to indirectly suck the space-based radar board unit 8, so that the movement of the space-based radar board is controlled.
4. Design of board unit quick connection system
The board unit quick connect system consists of mechanical quick connect means (screw assembly 20, base assembly 19), press screw means 21 and limit stops 22. As shown in fig. 4.
The space-based radar panel a limits the extended position of the space-based radar panel a itself by means of 13 in cooperation with 23 on the frame. After assembly, 23 will move downwards to avoid.
A screw component 20 of the mechanical quick connecting device is placed into a mounting hole of the space-based radar board B in advance and is fixed through a clamp spring; the base assembly 19 of the mechanical quick-connect device is fixed in the mounting hole of the space-based radar panel a by screws.
For the location that sky basic radar panel B can be accurate, make things convenient for the connection of two boards, designed limit baffle 22, when day basic radar panel B moves along the x direction along with the motion platform, the board touches limit baffle 22 in order to prevent its excessive motion in this direction.
Before the space-based radar board A and the space-based radar board B are completely contacted through the moving platform 11, the positioning taper column c on the space-based radar board and the corresponding taper hole also play a certain positioning role.
The pressing screw device 21 is composed of a pressing metal head fixed by an electric push rod and a push rod head. After the space-based radar board A and the space-based radar board B are completely contacted, the pressing metal head moves downwards along with the work of the electric push rod until the pressing metal head contacts the screw component 20 of the mechanical quick connecting device, so that the pressing metal head and the base component 19 of the mechanical quick connecting device are acted.
5. Plate drive system design
The plate driving system is composed of a driving friction wheel 1, a limit stop 13, a limit baffle 23, an electric push rod 2 and a pinch roller 3. As shown in fig. 5.
And the plate driving system is used for moving the connected radar plates out of the box body for a certain distance to wait for reconnection and installation of the next radar plate. The limit baffle 23 and the electric push rod 2 can limit the horizontal movement of the limit stop 13 along with the extension and retraction of the electric push rod, and are used for positioning and accurate plate displacement. The pinch roller 3 has no power, and a torsion spring is arranged above a fixed rod of the pinch roller, so that the pinch roller has a certain downward pressure, and the driving friction wheel 1 can drive the plate to move through friction force.
The operation flow of the container type space-based radar on-orbit assembly device is as follows (for the convenience of observation, the supporting frame 7 is transparent in the following figures):
a) the initiating explosive device works to break the fixing rope 10 so that all the space-based radar panel units 8 can be moved as shown in fig. 6.
b) The electric push rod of the screw pressing device 21 is recovered; the driving friction wheel 1 works to drive the first plate to move by friction, as shown in fig. 7.
c) First electric putter 16 of drive assembly 11 takes electromagnet 17 to stretch out, and electromagnet 17 work adsorbs the attached iron sheet 18 of day basic radar board unit 8 side to indirectly adsorb day basic radar board unit 8, cross slide rail 15 work takes day basic radar board unit 8 to remove, and the location through limit baffle 22 and location awl post makes with the board initial joint of second, as shown in fig. 8.
d) The electric push rod on the press screw device 21 is extended so that the press metal head contacts the screw assembly 20 of the quick link device. And continuously pressing to compress the disc spring until the disc spring is successfully locked. The first power push rod 16 is then retracted with the pressing metal head, as shown in fig. 9.
e) The limit baffle 22, the electric push rod 2 and the driving friction wheel 1 work in cooperation with the pinch roller 3, and the two plates are driven to move by friction force, as shown in fig. 10.
f) Since the limit stoppers 13 on the side surfaces of the space-based radar panel units 8 are embedded into the corresponding slots of the caterpillar band 6, the caterpillar band 6 rotates to drive the other space-based radar panel units 8 to move downwards so as to prepare for the driving assembly 11 to move the third panel, as shown in fig. 11.
g) All space-based radar panel units 8 are installed in sequence according to the above-described procedure, as shown in fig. 12.
h) After all the space-based radar panel units 8 are connected, the container body moves to the center of the radar panel through the driving friction wheels 1 and the pressing wheels 3 at the two ends of the container body, as shown in fig. 13.
Those skilled in the art will appreciate that the details of the invention not described in detail in the specification are within the skill of those skilled in the art.
Claims (8)
1. To big length antenna's collection dress formula of accomodating at rail assembly device, its characterized in that includes: a supporting frame (7), a one-way transmission mechanism, a two-way transmission mechanism and an assembly component;
a one-way transmission mechanism, a two-way transmission mechanism and an assembly component are fixedly arranged on the supporting frame (7);
a plurality of space-based radar plate units (8) are stacked to form a stacked structure; each space-based radar board unit (8) is fixedly connected with a one-way transmission mechanism respectively, the one-way transmission mechanism drives the plurality of space-based radar board units (8) to synchronously move linearly along the normal direction of the board surface, and meanwhile, a limiting structure matched with the space-based radar board units (8) is arranged on the one-way transmission mechanism to limit the torsion and the shaking of the space-based radar board units (8);
the bidirectional transmission mechanism drives the space-based radar board unit (8) positioned at the bottom of the laminated structure to be coplanar with the space-based radar board unit (8) positioned at the second from last at the bottom of the laminated structure, or drives the spliced and formed plurality of space-based radar board units (8) to move reversely along the splicing direction;
the assembly component is used for splicing and fixing the space-based radar panel unit (8) positioned at the bottom of the laminated structure and the space-based radar panel unit (8) positioned at the second from last at the bottom of the laminated structure into an integral plane structure.
2. The assembly device of claim 1, further comprising a fixing cable and an initiating explosive device (10);
before the space-based radar board units (8) are assembled on the rails, a plurality of stacked space-based radar board units (8) are fixedly connected through fixed cables and initiating explosive devices (10).
3. The assembly device of claim 1, wherein the one-way transmission mechanism comprises: a driving track motor (5), a track (6) and a limit guide rail (9);
a plurality of tracks (6) and limiting guide rails (9) are fixedly arranged on the supporting frame (7) along the stacking direction;
a plurality of limit stops (13) protruding outwards are arranged on two symmetrical side walls of the space-based radar plate unit (8), and a tooth structure of the crawler belt (6) is matched with the limit stops (13) of the space-based radar plate unit (8); the driving track motor (5) is used for driving the track (6) to drive the space-based radar board unit (8) to move from top to bottom along the stacking direction;
a plurality of limiting blocks (14) protruding outwards are arranged on two symmetrical side walls of the space-based radar panel unit (8), the cross sections of the limiting blocks (14) are triangular, and the directions of bevel edges of the limiting blocks (14) on the two symmetrical side walls are opposite; the limiting structure arranged on the limiting guide rail (9) is matched with a limiting block (14) of the space-based radar board unit (8).
4. The assembly device of claim 1, wherein the bidirectional transmission mechanism comprises: the device comprises a driving friction wheel (1), a pressing wheel (3), a driving assembly (11) and a positioning and limiting structure;
the driving assembly (11) is fixedly connected with a space-based radar board unit (8) positioned at the bottom of the laminated structure by using a magnet and moves to an assembling position;
the driving friction wheel (1) is matched with the pressing wheel (3) to drive the space-based radar board unit (8) to move parallel to the board surface;
the positioning and limiting structure is used for limiting the movement position of the space-based radar board unit (8).
5. The assembly device of claim 4, wherein the driving assembly (11) comprises: a cross slide rail (15), a first electric push rod (16), an electromagnetic chuck (17) and an attached iron sheet (18);
the electromagnetic chuck (17) is fixedly connected with a first electric push rod (16), and the first electric push rod (16) can slide along the cross slide rail (15);
the cross slide rail (15) is fixedly connected with the supporting frame (7);
iron sheet grooves (d) for mounting attached iron sheets (18) are formed in two symmetrical side walls of the space-based radar plate unit (8);
the electromagnetic chuck (17) is matched with an attached iron sheet (18) on the space-based radar plate unit (8), so that the first electric push rod (16) drives the space-based radar plate unit (8) to move to an assembly position.
6. The assembly device of claim 5, wherein the mounting assembly comprises: the second electric push rod (4), the screw component (20), the base component (19), the pressing screw device (21) and the limit baffle (22);
the second electric push rod (4) and the limit baffle (22) are fixedly connected with the support frame (7); the pressing screw device (21) is fixedly connected with the second electric push rod (4);
in the assembly position, the lap joint edges of the two space-based radar plate units (8) are aligned through a limiting baffle (22);
a base assembly (19) is fixedly installed on the lower space-based radar board unit (8), and a screw assembly (20) is fixedly installed on the upper space-based radar board unit (8);
the second electric push rod (4) drives the pressing screw device (21) to press the space-based radar board units (8) located above to move downwards until the base component (19) and the screw component (20) are assembled in place, and the two space-based radar board units (8) are spliced and fixed into an integral plane structure.
7. The assembly and storage type on-track assembly device for the long-length antenna according to claim 6, wherein a raised strip (b) and a positioning conical column (c) are processed on the overlapping edge of the space-based radar panel unit (8) to serve as positioning and limiting structures;
the positioning and limiting structures at the lap joint edges of the two space-based radar plate units (8) are matched with each other.
8. A method of assembling the assembly apparatus of claim 7, wherein the method comprises the steps of:
1) a raised line (b) and a positioning conical column (c) are processed on the lap joint edge of the space-based radar plate unit (8) to be used as a positioning limit structure;
2) a plurality of space-based radar plate units (8) are stacked to form a stacked structure; each space-based radar board unit (8) is fixedly connected with a one-way transmission mechanism respectively;
3) before the space-based radar board units (8) are assembled on the rails, a plurality of stacked space-based radar board units (8) are fixedly connected by using fixed ropes and initiating explosive devices (10);
4) when the space-based radar board unit (8) is assembled on the rail, the fixed rope and the initiating explosive device (10) are unlocked and blasted;
5) the one-way transmission mechanism drives the plurality of space-based radar plate units (8) to synchronously move downwards along the normal direction of the plate surface in a straight line manner;
6) the bidirectional transmission mechanism drives a space-based radar board unit (8) positioned at the bottom of the laminated structure to be coplanar with a space-based radar board unit (8) positioned at the second last from the bottom of the laminated structure;
9) the driving component (11) drives the space-based radar board unit (8) to move to the assembling position;
10) the second electric push rod (4) drives the pressing screw device (21) to press the space-based radar board unit (8) located above to move downwards until a base component (19) of the space-based radar board unit (8) located below and a screw component (20) of the space-based radar board unit (8) located above are assembled in place, and the two space-based radar board units (8) are spliced and fixed into an integral plane structure;
11) and (5) repeating the steps and the step (10) until the splicing work of the multiple sky-based radar plate units (8) on one side is completed, and driving the multiple sky-based radar plate units (8) which are spliced and formed on one side to move in the opposite direction of the splicing direction by using a bidirectional transmission mechanism to complete the splicing work.
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