CN117549020B - Assembly tool and assembly method of rocket rail attitude control power system - Google Patents
Assembly tool and assembly method of rocket rail attitude control power system Download PDFInfo
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- CN117549020B CN117549020B CN202310379115.5A CN202310379115A CN117549020B CN 117549020 B CN117549020 B CN 117549020B CN 202310379115 A CN202310379115 A CN 202310379115A CN 117549020 B CN117549020 B CN 117549020B
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- 238000000034 method Methods 0.000 title claims abstract description 16
- 238000005096 rolling process Methods 0.000 claims description 21
- 230000000149 penetrating effect Effects 0.000 claims description 3
- 230000008859 change Effects 0.000 claims description 2
- 238000010586 diagram Methods 0.000 description 4
- 230000008569 process Effects 0.000 description 3
- 239000000463 material Substances 0.000 description 2
- 230000007246 mechanism Effects 0.000 description 2
- 230000007547 defect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
Classifications
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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
- B23P19/001—Article feeders for assembling machines
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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
- B23P19/04—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 for assembling or disassembling parts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
- B25B—TOOLS OR BENCH DEVICES NOT OTHERWISE PROVIDED FOR, FOR FASTENING, CONNECTING, DISENGAGING OR HOLDING
- B25B11/00—Work holders not covered by any preceding group in the subclass, e.g. magnetic work holders, vacuum work holders
- B25B11/02—Assembly jigs
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B66—HOISTING; LIFTING; HAULING
- B66F—HOISTING, LIFTING, HAULING OR PUSHING, NOT OTHERWISE PROVIDED FOR, e.g. DEVICES WHICH APPLY A LIFTING OR PUSHING FORCE DIRECTLY TO THE SURFACE OF A LOAD
- B66F19/00—Hoisting, lifting, hauling or pushing, not otherwise provided for
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- Mechanical Engineering (AREA)
- Life Sciences & Earth Sciences (AREA)
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- Structural Engineering (AREA)
- Automatic Assembly (AREA)
Abstract
The invention provides an assembly fixture and an assembly method of a rocket rail attitude control power system, comprising the following steps: the rotating ring frame comprises a first supporting frame and a second supporting frame; the first support frame and the second support frame are hinged; the first rotating ring frame and the second rotating ring frame are arranged at intervals on two sides of the first supporting frame along the extending direction of the first supporting frame and are respectively connected with the first supporting frame in a rotating way; wherein, first support frame includes: a first working position and a second working position; in the first working position, the first support frame is parallel to the second support frame, and the extending directions of the two rotating ring frames are parallel to the ground; and under the second working position, the first support frame is vertical to the second support frame, and the extending directions of the two rotating ring frames are vertical to the ground. The transfer ring frame realizes assembly at multiple angles, and the support frame is used for converting horizontal and vertical positions. Simple structure, assembly efficiency is high.
Description
Technical Field
The invention relates to the technical field of assembly work, in particular to an assembly tool and an assembly method of a rocket rail attitude control power system.
Background
The orbit attitude control power system is one of key subsystems of the rocket. During the final flight of the rocket, the orbit attitude control power system provides control force and control moment for attitude control, orbit transfer and orbit correction. In order to realize the control in multiple directions, the rail attitude control power system has a relatively complex structure, and the structures are distributed in all directions of the rail attitude control power system. This requires multiple changes in angle and position of the track attitude control power system during assembly to complete the assembly.
In the prior art, the assembly fixture of the rail attitude control power system is mostly composed of a plurality of groups of simple supporting frames and hoisting fixtures. The rail attitude control power system is placed on different support frames through multiple times of lifting, so that assembly requirements of different angles and positions are met, multiple times of lifting operation is needed by using the tool, time and labor are consumed, assembly efficiency is low, multiple lifting points are needed to be mounted on the rail attitude control power system, and carrying capacity of a rocket is reduced.
Disclosure of Invention
The invention provides an assembly tool and an assembly method of a rocket rail attitude control power system, which are used for solving the defects of time and labor waste and low assembly efficiency of the tool in the prior art, and realizing the technical effects of convenient use and improvement of assembly efficiency.
In a first aspect, the present invention provides an assembly fixture for a rocket rail attitude control power system, comprising: the rotating ring frame comprises a first supporting frame and a second supporting frame;
The first support frame and the second support frame are hinged;
the first rotating ring frame and the second rotating ring frame are arranged at intervals on two sides of the first supporting frame along the extending direction of the first supporting frame and are respectively connected with the first supporting frame in a rotating way;
wherein, first support frame includes: a first working position and a second working position;
In the first working position, the first support frame is parallel to the second support frame, and the extending directions of the two rotating ring frames are parallel to the ground;
And under the second working position, the first support frame is vertical to the second support frame, and the extending directions of the two rotating ring frames are vertical to the ground.
The assembly fixture of the rocket rail attitude control power system provided by the invention further comprises: the hinge seat is arranged between the first support frame and the second support frame and is close to the second rotating ring frame, and the first support frame is hinged with the second support frame through the hinge seat.
The assembly fixture of the rocket rail attitude control power system provided by the invention further comprises: the support frame locking seat is arranged between the first support frame and the second support frame and is close to the first rotating ring frame, and the first support frame is detachably connected with the second support frame through the support frame locking seat.
The assembly fixture of the rocket rail attitude control power system provided by the invention further comprises: the vertical cylinder is arranged between the first support frame and the second support frame, one end of the vertical cylinder is hinged with the first support frame and is close to the first rotating ring frame, the other end of the vertical cylinder is hinged with the second support frame and is close to the second rotating ring frame, and the vertical cylinder is used for pushing the first support frame to be converted between the first working position and the second working position.
The assembly fixture of the rocket rail attitude control power system provided by the invention further comprises: the first roller is arranged on the surface of the second support frame, which is far away from one side of the first support frame, and is used for adjusting the position of the second support frame.
The assembly fixture of the rocket rail attitude control power system provided by the invention further comprises: the second roller, the roller supporting seat and the swivel bracket locking seat are arranged between the swivel bracket and the first supporting frame;
The roller support seats are arranged on the first support frame at intervals, and the second rollers are arranged between the roller support seats and the swivel frame and used for supporting and rotating the swivel frame;
One end of the swivel stand locking seat is connected with the first supporting frame, the other end of the swivel stand locking seat is a clamping end, and the clamping end is abutted to the swivel stand and used for locking the rotating angle of the swivel stand and disassembling the swivel stand from the first supporting frame.
The invention provides an assembly fixture of a rocket rail attitude control power system, wherein a roller support seat comprises a rolling shaft, a lock nut and a support seat;
The supporting seat is arranged on the first supporting frame;
The rolling shaft penetrates through the supporting seat, and the second roller is sleeved on the rolling shaft;
The lock nut is arranged at one end of the rolling shaft and is used for fixing the rolling shaft on the supporting seat.
The assembly fixture of the rocket rail attitude control power system provided by the invention further comprises: the support platform is arranged on the second rotating ring frame;
and the supporting platform is contacted with the ground in the second working position and is used for supporting the rocket rail attitude control power system.
According to the assembly fixture for the rocket rail attitude control power system, which is provided by the invention, the third idler wheels are arranged on one side, away from the swivel frame, of the supporting platform and are used for moving the swivel frame and the rocket rail attitude control power system in the second working position.
In a second aspect, the invention further provides an assembly method of an assembly fixture of the rocket rail attitude control power system, which comprises the following steps:
Adjusting a first support frame to a first working position and locking the first support frame;
the rocket rail attitude control power component is arranged on two rotating ring frames;
Adjusting the swivel stand to a working angle and locking, and assembling the rocket rail attitude control power component;
repeatedly adjusting the angle of the rotating ring frame and locking, and continuously assembling until the assembly at the first working position is completed;
Unlocking the first support frame, overturning the first support frame to a second working position, and enabling the support platform to be in contact with the ground;
After the support platform is in stable contact with the ground, unlocking the swivel stand, and conveying the rocket rail attitude control power component to the next station by the support platform;
and continuously assembling the rocket rail attitude control power system on the supporting platform until the rocket rail attitude control power system is completed.
According to the invention, the two rotating ring frames are arranged at intervals to provide stable support for the rocket rail attitude control power system; the rotating ring frame is rotationally connected with the first supporting frame, so that the assembly of the rocket rail attitude control power system under different angles can be realized; the rotating ring frame is arranged on the first support frame, the first support frame is hinged with the second support frame, so that the first support frame can be overturned relative to the second support frame, and the rotating ring frame and the rocket track attitude control power system on the rotating ring frame are driven to overturned, so that the rocket track attitude control power system can be switched between a horizontal state and a vertical state. The angle and the position of the rocket rail attitude control power system need to be changed for a plurality of times in the assembly process, and the invention meets the requirements of all assembly positions of the rocket rail attitude control power system through a simple structure, has simple use, improves the assembly efficiency, and saves time and labor.
Furthermore, in the assembly method of the assembly fixture of the rocket rail attitude control power system, which is provided by the invention, the assembly fixture of the rocket rail attitude control power system is adopted, so that the assembly fixture also has the advantages.
Drawings
In order to more clearly illustrate the invention or the technical solutions of the prior art, the following description will briefly explain the drawings used in the embodiments or the description of the prior art, and it is obvious that the drawings in the following description are some embodiments of the invention, and other drawings can be obtained according to the drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic diagram of an assembly fixture for a rocket rail attitude control power system provided by the invention;
Fig. 2 is a schematic structural view of a second support frame according to the present invention;
Fig. 3 is a schematic structural view of a first support frame according to the present invention;
FIG. 4 is a cross-sectional view of the roller support provided by the present invention;
FIG. 5 is a schematic view of the structure of the support platform according to the present invention;
FIG. 6 is one of the schematic diagrams of the assembly method of the assembly fixture of the rocket rail attitude control power system provided by the invention;
FIG. 7 is a second schematic diagram of an assembly method of an assembly fixture of a rocket rail attitude control power system provided by the invention;
FIG. 8 is a third schematic diagram of an assembly method of an assembly fixture of a rocket rail attitude control power system provided by the invention.
Reference numerals:
1: a first turret; 2: a second swivel mount; 3: a support platform; 32: a third roller; 4: a first support frame; 41: a roller support seat; 411: a support base; 412: a rolling shaft; 414: a second roller; 416: a lock nut; 417: a bearing; 45: a swivel stand locking seat; 6: a vertical cylinder is started; 8: a hinge base; 9: a second support frame; 91: a support frame locking seat; 92: a first roller; 10: rocket rail attitude control power component.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the present invention more apparent, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings, and it is apparent that the described embodiments are some embodiments of the present invention, not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
In describing embodiments of the present invention, it should be noted that, unless explicitly stated and limited otherwise, the terms "coupled," "coupled," and "connected" should be construed broadly, and may be either a fixed connection, a removable connection, or an integral connection, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium. The specific meaning of the above terms in embodiments of the present invention will be understood in detail by those of ordinary skill in the art.
In the description of the embodiments of the present invention, it should be noted that the terms "center", "longitudinal", "lateral", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are merely for convenience in describing the embodiments of the present invention and simplifying the description, and do not indicate or imply that the apparatus or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the embodiments of the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present specification, a description referring to terms "one embodiment," "some embodiments," "examples," "specific examples," or "some examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the embodiments of the present invention. In this specification, schematic representations of the above terms are not necessarily directed to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, the different embodiments or examples described in this specification and the features of the different embodiments or examples may be combined and combined by those skilled in the art without contradiction.
Embodiments of the present invention are described in further detail below in conjunction with fig. 1-8. The following examples are illustrative of the invention but are not intended to limit the scope of the invention.
As shown in fig. 1, the invention provides an assembly fixture of a rocket rail attitude control power system, comprising: a swivel mount, a first support 4 and a second support 9. The rotating ring frame is arranged on one side of the first supporting frame 4, and the second supporting frame 9 is arranged on the other side of the first supporting frame 4. The rotating ring frame is rotatably connected with the first supporting frame 4, and the second supporting frame 9 is hinged with the first supporting frame 4.
The first rotating ring frame 1 and the second rotating ring frame 2 are respectively arranged on the two rotating ring frames, and the first rotating ring frame 1 and the second rotating ring frame 2 are arranged on the first supporting frame 4 at intervals and are both connected with the first supporting frame 4 in a rotating way. The rocket rail attitude control power system is arranged between the first rotating ring frame 1 and the second rotating ring frame 2, the top end of the rocket rail attitude control power system is connected with the first rotating ring frame 1, and the bottom end of the rocket rail attitude control power system is connected with the second rotating ring frame 2. The rotating ring frame is in a ring shape, can rotate 360 degrees relative to the first supporting frame 4 and drives the rail attitude control power system fixed on the rotating ring frame to rotate. The size of the rotating ring frame is adapted to the track attitude control power system.
One side of the second supporting frame 9 is contacted with the ground, and the other side is hinged with the first supporting frame 4. The first support 4 rotates about the hinge so that the first support 4 can be switched between a first operating position and a second operating position. Wherein the second support 9 is always parallel to the ground, regardless of the variation of the working position. When the first support frame 4 is in the first working position, the first support frame 4 and the second support frame 9 are parallel to each other, and the connecting line of the circle centers of the two rotating ring frames is parallel to the ground, namely the extending direction of the two rotating ring frames is parallel to the ground; when the first support frame 4 is in the second working position, the first support frame 4 and the second support frame 9 are mutually perpendicular, and the connecting line of the circle centers of the two rotating ring frames is perpendicular to the ground, namely the extending direction of the two rotating ring frames is perpendicular to the ground.
With continued reference to FIG. 1, in an alternative embodiment, the assembly fixture of the rocket rail attitude control power system further includes: and (5) erecting a cylinder 6. The vertical lifting cylinder 6 is arranged between the first support frame 4 and the second support frame 9, and one end of the vertical lifting cylinder 6 is hinged with the first support frame 4 and is close to the first rotating ring frame 1; the other end of the erection cylinder 6 is hinged with the second supporting frame 9 and is close to the second rotating ring frame 2. The first support frame 4 can be switched between the first operating position and the second operating position by pushing or retracting the lifting cylinder 6. Optionally, a lift is connected to the side of the erection cylinder 6 near the ground, and the lift is used to push or retract the erection cylinder 6 for turning over the first support frame 4.
As shown in fig. 2, in the embodiment described above, the assembly fixture of the rocket rail attitude control power system further includes: and a hinge seat 8. The articulated seat 8 is arranged between the first support frame 4 and the second support frame 9 and is close to the second swivel bracket 2, and the first support frame 4 is articulated with the second support frame 9 through the articulated seat 8. When the first support frame 4 is turned to the second working position, the second rotating ring frame 2 is close to the ground, the first rotating ring frame 1 is far away from the ground, and the rocket rail attitude control power system between the rotating ring frames is turned to a position vertical to the ground.
Further, the assembly fixture of the rocket rail attitude control power system further comprises: the support frame locking seat 91. The support frame locking seat 91 is disposed between the first support frame 4 and the second support frame 9 and is close to the first rotating ring frame 1, and the first support frame 4 is locked with the second support frame 9 through the support frame locking seat 91, so that the first support frame 4 is maintained at the first working position without overturning. Under the first working position, one side of the first support frame 4, which is close to the first rotating ring frame 1, is lapped on the support frame locking seat 91 and is locked by the support frame locking seat 91, so that the first support frame 4 cannot rotate, the rocket rail attitude control power system is guaranteed to be assembled in a horizontal state, and after the horizontal assembly is finished, the support frame locking seat 91 is unlocked, so that the first support frame 4 can be turned to a second working position for subsequent assembly in a vertical state.
With continued reference to fig. 2, in an alternative embodiment provided by the present invention, the assembly fixture of the rocket rail attitude control power system further includes: a first roller 92. The first roller 92 is disposed on the second support frame 9, and is located on a surface of the second support frame 9 on a side away from the first support frame 4. Pushing the first roller 92 can change the assembly fixture of the rocket rail attitude control power system and the position of the rocket rail attitude control power system thereon. Optionally, a brake mechanism is further provided on each first roller 92 for parking the assembly fixture of the rocket rail attitude control power system.
As shown in fig. 3, in an alternative embodiment provided by the present invention, the assembly fixture of the rocket rail attitude control power system further includes: a second roller 414 and a roller support 41. The second roller 414 and the roller supporting seat 41 are both disposed between the first supporting frame 4 and the swivel bracket, so as to realize rotational connection between the swivel bracket and the first supporting frame 4. The roller supporting seats 41 are arranged on the first supporting frame 4 at intervals, and a second roller 414 is arranged between the roller supporting seats 41 and the swivel bracket and is used for supporting and rotating the swivel bracket.
Specifically, two sets of roller supporting seats 41 are disposed on the first supporting frame 4, the two sets of roller supporting seats 41 are disposed at intervals on two sides of the first supporting frame 4, each set of roller supporting seats 41 comprises two roller supporting seats 41, and the two roller supporting seats 41 are disposed at intervals and form a supporting structure for supporting the rotating ring frame. The roller support 41 is provided with a second roller 414, and the rotating ring frame is abutted against the second roller 414. Rotating the second roller 414 may drive the swivel mount to rotate, changing the angle of the rocket rail attitude control power system.
Further, the assembly fixture of the rocket rail attitude control power system further comprises: swivel mount locking mount 45. One end of the swivel stand locking seat 45 is connected with the first support frame 4, and the other end of the swivel stand locking seat 45 is configured as a clamping end and is abutted with the swivel stand for locking the rotation angle of the swivel stand and dismounting the swivel stand from the first support frame 4.
Specifically, a swivel bracket locking seat 45 is provided on the first support frame 4, and the swivel bracket locking seat 45 is located in the middle of the set of roller support seats 41. One end of the swivel stand locking seat 45 is fixedly connected with the first supporting frame 4, and the other end is configured as a clamping end and is abutted with the swivel stand. The clamping end is U-shaped, and the swivel mount is inserted into the clamping end, and two sides of the clamping end are detachably connected with the swivel mount and used for fixing the swivel mount so that the swivel mount does not rotate. Optionally, bolts are used to secure both sides of the clamping end to the swivel mount. Also optionally, a through hole is provided in the swivel bracket near the clamping end, and locking pins are used to insert the clamping end and the through hole for securing the swivel bracket.
In actual use, the angle of the rocket rail attitude control power system is adjusted by rotating the second roller 414, and the angle of the rocket rail attitude control power system is fixedly adjusted by the swivel bracket locking seat 45. When the first support frame 4 is switched from the first working position to the second working position, the swivel bracket locking seat 45 is used for fixing the swivel bracket on the first support frame 4 so that the swivel bracket does not fall off from the first support frame 4.
As shown in fig. 4, in the embodiment described above, the roller support 41 includes a rolling shaft 412, a lock nut 416, and a support 411. The supporting seat 411 is disposed on the first supporting frame 4, the rolling shaft 412 is disposed through the supporting seat 411, and the penetrating direction of the rolling shaft 412 is in the same direction as the connecting line of the centers of the two swivel brackets. The locking nut 416 is disposed at one end of the rolling shaft 412 penetrating through the supporting seat 411, and is used for fixing the rolling shaft 412 on the supporting seat 411. The second roller 414 is sleeved on the rolling shaft 412, and rotates around the rolling shaft 412. Optionally, a bearing 417 is sleeved on the rolling shaft 412, and the bearing 417 is located between the second roller 414 and the rolling shaft 412, so as to reduce the friction coefficient in the rotation process and ensure the rotation precision.
As shown in fig. 5, in an alternative embodiment, the assembly fixture of the rocket rail attitude control power system further includes: and a support platform 3. The support platform 3 is arranged on one side of the second rotating ring frame 2 away from the first rotating ring frame 1. When the first support frame 4 is in the second working position, the support platform 3 is in contact with the ground and is used for supporting the rocket rail attitude control power system.
In the embodiment described above, the third roller 32 is provided on the support platform 3, and the third roller 32 is provided on the side of the support platform 3 remote from the turret. Alternatively, the support platform 3 is configured as a polygon, with a third roller 32 provided at each corner. Further, the third rolling configuration is a universal wheel. Optionally, a brake mechanism is disposed on the third roller 32 to realize the parking of the rocket rail attitude control power system in the second working position. In the second working position, the support platform 3, the swivel bracket and the rocket rail attitude control power system can be separated from the first support frame 4 by unlocking the swivel bracket locking seat 45, the third roller 32 is pushed, and the transfer of the rocket rail attitude control power system is realized in a vertical state.
In a second aspect, the invention also provides an assembly method of the assembly fixture of the rocket rail attitude control power system, and the assembly fixture of the rocket rail attitude control power system is adopted. The method comprises the following steps:
s1, adjusting the first support frame 4 to a first working position, and locking the first support frame 4;
S2, placing the rocket rail attitude control power component 10 on two rotating ring frames;
s3, adjusting the rotating ring frame to a working angle and locking, and assembling the rocket rail attitude control power component 10;
S4, repeatedly adjusting the angle of the rotating ring frame and locking, and continuously assembling until the assembly at the first working position is completed;
s5, unlocking the first support frame 4, overturning the first support frame 4 to a second working position, and enabling the support platform 3 to be in contact with the ground;
S6, after the support platform 3 is in stable contact with the ground, unlocking the rotating ring frame, and conveying the rocket rail attitude control power component 10 to the next station by the support platform 3;
and S7, continuously assembling the rocket rail attitude control power system on the support platform 3 until the rocket rail attitude control power system is completed.
Specifically, as shown in fig. 6, the first support frame 4 is adjusted to the first working position, and the first support frame 4 is locked by the support frame locking seat 91. Two ends of the rocket rail attitude control power component 10 are respectively and fixedly connected with two swivel brackets. The second roller 414 is rotated to rotate the swivel bracket, so as to adjust the angle of the rocket rail attitude control power component 10 to a working angle, and the rocket rail attitude control power component 10 is locked by the swivel bracket locking seat 45, so that the rocket rail attitude control power component 10 is assembled. The angle of the rotating ring frame is repeatedly adjusted and locked, and the full-angle assembly of the rocket rail attitude control power component 10 in the first working position is completed.
As shown in fig. 7, the support frame locking seat 91 is unlocked, and the first support frame 4 is pushed to the second working position by the erection cylinder 6, and the third roller 32 of the support platform 3 is in contact with the ground.
As shown in fig. 8, after the support platform 3 is in stable contact with the ground, the turret locking seat 45 is unlocked, and the first roller 92 or the third roller 32 is pushed, so that the turret, the support platform 3 and the rocket rail attitude control power component 10 are separated from the first support frame 4. The supporting platform 3 is pushed to convey the rocket rail attitude control power component 10 to the next station. The rocket rail attitude control power component 10 in the vertical state is assembled until the rocket rail attitude control power system is completed.
According to the invention, the two rotating ring frames are arranged at intervals to provide stable support for the rocket rail attitude control power system; the rotating ring frame is rotationally connected with the first supporting frame 4, so that the assembly of the rocket rail attitude control power system under different angles can be realized; the rotating ring frame is arranged on the first support frame 4, the first support frame 4 is hinged with the second support frame 9, so that the first support frame 4 can be overturned relative to the second support frame 9, and the rotating ring frame and the rocket rail attitude control power system on the rotating ring frame are driven to overturne, so that the rocket rail attitude control power system can be switched between a horizontal state and a vertical state. The angle and the position of the rocket rail attitude control power system need to be changed for a plurality of times in the assembly process, and the invention meets the requirements of all assembly positions of the rocket rail attitude control power system through a simple structure, has simple use, improves the assembly efficiency, and saves time and labor.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present invention, and are not limiting; although the invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit and scope of the technical solutions of the embodiments of the present invention.
Claims (9)
1. The utility model provides an assembly fixture of rocket rail appearance accuse driving system which characterized in that includes: the rotating ring frame comprises a first supporting frame (4), a second supporting frame (9), a second roller (414), a roller supporting seat (41) and a rotating ring frame locking seat (45);
The first support frame (4) and the second support frame (9) are hinged;
The first rotating ring frame (1) and the second rotating ring frame (2) are arranged at intervals on two sides of the first supporting frame (4) along the extending direction of the first supporting frame (4) and are respectively connected with the first supporting frame (4) in a rotating way;
the second roller (414), the roller supporting seat (41) and the swivel bracket locking seat (45) are arranged between the swivel bracket and the first supporting frame (4);
The roller support seats (41) are arranged on the first support frame (4) at intervals, and the second rollers (414) are arranged between the roller support seats (41) and the swivel frame and used for supporting and rotating the swivel frame;
One end of the swivel stand locking seat (45) is connected with the first supporting frame (4), and the other end of the swivel stand locking seat (45) is a clamping end and is abutted with the swivel stand to lock the rotating angle of the swivel stand and disassemble the swivel stand from the first supporting frame (4);
wherein the first support frame (4) comprises: a first working position and a second working position;
in the first working position, the first supporting frame (4) is parallel to the second supporting frame (9), and the extending directions of the two rotating ring frames are parallel to the ground;
in the second working position, the first supporting frame (4) is vertical to the second supporting frame (9), and the extending directions of the two rotating ring frames are vertical to the ground.
2. The assembly fixture of a rocket rail attitude control power system according to claim 1, further comprising: the hinge seat (8), hinge seat (8) set up in between first support frame (4) with second support frame (9), and be close to second pivot frame (2), first support frame (4) are through hinge seat (8) with second support frame (9) are articulated.
3. The assembly fixture of a rocket rail attitude control power system according to claim 2, further comprising: the support frame locking seat (91), support frame locking seat (91) set up in between first support frame (4) with second support frame (9), and be close to first rotating ring frame (1), first support frame (4) pass through support frame locking seat (91) with second support frame (9) can dismantle and be connected.
4. A rocket rail attitude control power system assembly fixture according to claim 3, further comprising: the vertical cylinder (6), set up in play erect jar (6) with between second support frame (9) first support frame (4), play erect jar (6) one end with first support frame (4) are articulated, and are close to first rotating ring frame (1), play erect jar (6) the other end with second support frame (9) are articulated, and are close to second rotating ring frame (2) for promote first support frame (4) first operating position with change between the second operating position.
5. The assembly fixture of a rocket rail attitude control power system according to claim 1, further comprising: the first roller (92), first roller (92) set up in second support frame (9) keep away from the surface of first support frame (4) one side is used for adjusting the position of second support frame (9).
6. Assembly fixture of a rocket rail attitude control power system according to any one of claims 1 to 5, wherein said roller support (41) comprises a rolling shaft (412), a lock nut (416) and a support (411);
the supporting seat (411) is arranged on the first supporting frame (4);
the rolling shaft (412) is arranged on the supporting seat (411) in a penetrating mode, and the second roller (414) is sleeved on the rolling shaft (412);
the lock nut (416) is disposed at one end of the rolling shaft (412), and is used for fixing the rolling shaft (412) on the supporting seat (411).
7. The assembly fixture of a rocket rail attitude control power system according to claim 6, further comprising: the support platform (3) is arranged on the second rotating ring frame (2);
And in the second working position, the supporting platform (3) is contacted with the ground and is used for supporting the rocket rail attitude control power system.
8. The assembly fixture of the rocket rail attitude control power system according to claim 7, wherein a third roller (32) is arranged on one side of the supporting platform (3) far away from the swivel frame and is used for moving the swivel frame and the rocket rail attitude control power system in the second working position.
9. An assembly method of an assembly fixture of a rocket rail attitude control power system according to any one of claims 1 to 8, comprising:
adjusting the first support frame (4) to a first working position and locking the first support frame (4);
The rocket rail attitude control power component (10) is placed on two rotating ring frames;
Adjusting the swivel stand to a working angle and locking, and assembling the rocket rail attitude control power component (10);
repeatedly adjusting the angle of the rotating ring frame and locking, and continuously assembling until the assembly at the first working position is completed;
unlocking the first support frame (4), overturning the first support frame (4) to a second working position, and enabling the support platform (3) to be in contact with the ground;
After the support platform (3) is in stable contact with the ground, unlocking the swivel stand, and conveying the rocket rail attitude control power component (10) to the next station by the support platform (3);
And continuously assembling on the supporting platform (3) until the rocket rail attitude control power system is completed.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202310379115.5A CN117549020B (en) | 2023-04-11 | 2023-04-11 | Assembly tool and assembly method of rocket rail attitude control power system |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310379115.5A CN117549020B (en) | 2023-04-11 | 2023-04-11 | Assembly tool and assembly method of rocket rail attitude control power system |
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| CN117549020A CN117549020A (en) | 2024-02-13 |
| CN117549020B true CN117549020B (en) | 2024-04-19 |
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| CN202310379115.5A Active CN117549020B (en) | 2023-04-11 | 2023-04-11 | Assembly tool and assembly method of rocket rail attitude control power system |
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| CN111023899A (en) * | 2019-11-05 | 2020-04-17 | 蓝箭航天空间科技股份有限公司 | Rocket transferring and erecting system |
| CN114771397A (en) * | 2022-04-18 | 2022-07-22 | 重庆零壹空间航天科技有限公司 | Supporting device for large rocket transportation and using method thereof |
| CN115215274A (en) * | 2022-08-18 | 2022-10-21 | 北京中科宇航技术有限公司 | System for controlling speed and automatically adjusting speed in rocket erecting and laying process |
| CN115773695A (en) * | 2022-12-14 | 2023-03-10 | 东方空间技术(山东)有限公司 | Offshore thermal launching method for medium-large solid carrier rocket |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7900547B2 (en) * | 2008-01-17 | 2011-03-08 | The Boeing Company | System and method for preparing a launch device |
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|---|---|---|---|---|
| US6186039B1 (en) * | 1998-02-25 | 2001-02-13 | Kistler Aerospace Corporation | Spacecraft launch system and method |
| CN110397520A (en) * | 2019-08-12 | 2019-11-01 | 西北工业大学 | Tilt adjustable rocket engine ground run rack |
| CN111023899A (en) * | 2019-11-05 | 2020-04-17 | 蓝箭航天空间科技股份有限公司 | Rocket transferring and erecting system |
| CN114771397A (en) * | 2022-04-18 | 2022-07-22 | 重庆零壹空间航天科技有限公司 | Supporting device for large rocket transportation and using method thereof |
| CN115215274A (en) * | 2022-08-18 | 2022-10-21 | 北京中科宇航技术有限公司 | System for controlling speed and automatically adjusting speed in rocket erecting and laying process |
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|---|---|
| CN117549020A (en) | 2024-02-13 |
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