CN116329987A - Missile casing is with processing frock - Google Patents
Missile casing is with processing frock Download PDFInfo
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- CN116329987A CN116329987A CN202310582933.5A CN202310582933A CN116329987A CN 116329987 A CN116329987 A CN 116329987A CN 202310582933 A CN202310582933 A CN 202310582933A CN 116329987 A CN116329987 A CN 116329987A
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
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- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
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Abstract
The invention relates to the technical field of tool fixtures, in particular to a processing tool for a missile shell, which comprises a guided missile shell and further comprises: the cavity adaptation component comprises a box body, wherein the inner bottom surface of the box body is provided with a sliding groove in a matrix mode, a sliding rod is slidably arranged in the sliding groove, a spring is arranged on one side of the sliding rod and arranged at the bottom of the sliding groove, electromagnets are arranged at the bottom of the sliding groove and connected in parallel, one side of each electromagnet is connected with an electric cabinet, and the electric cabinet is connected with a computer through a sensor. Because the missile is a conical or cylindrical irregular cavity as a whole, the end faces at two sides of the missile are generally of a cavity structure, so that a cavity adapting assembly is designed for cavities with different structural shapes, and the matrix control effect is realized by the cavity adapting assembly.
Description
Technical Field
The invention relates to the technical field of tool fixtures, in particular to a processing tool for a missile shell.
Background
The aviation and aerospace parts often adopt thin-wall special-shaped structures, so that the purpose of reducing weight is to reduce energy consumption of an aircraft in the flight process and exert the super-strong capability of the aircraft. The high precision, difficult clamping and difficult processing are the main characteristics in the processing of the parts, so that a special tool is required to be designed to realize the stable clamping of the parts.
A processing tool for missile shells, which is disclosed in Chinese patent publication No. CN112846859A, wherein the processing tool comprises a pressing mechanism and a propping mechanism; the compressing mechanism comprises a base and a compressing component arranged on the base, wherein the base is arranged in a cavity at the lower part of the missile shell, and the compressing component is used for compressing on a rib plate in the inner cavity of the missile shell; the propping mechanism comprises a supporting part and a propping part arranged on the supporting part, and the propping part is used for circumferentially propping against the missile shell from the outer wall of the missile shell. The compressing mechanism is embedded into the inner cavity of the lower part of the missile shell, the lower part of the missile shell is compressed on the processing platform, the supporting part is used for supporting the propping part to the upper part of the missile shell, and the propping part on the supporting part is used for propping the upper part of the missile shell from the peripheral wall of the missile shell, so that the stable clamping of the missile shell is realized, and the processing precision of the inner wall of the upper part of the missile shell is further ensured.
However, the missile clamping tool in the prior art can only be used for adaptively mounting missiles with specific shapes in the clamping process, and once the appearance structures of different batches of missiles are different, the adaptive clamping effect cannot be achieved by the tool in the prior art, and finally the processing progress is affected.
Disclosure of Invention
The invention aims to provide a processing tool for missile shells, which aims to solve the problems in the background technology.
The technical scheme of the invention is as follows: the utility model provides a missile casing is with processing frock, includes and leads the shell case still includes:
the cavity adapting assembly comprises a box body, wherein a sliding groove is formed in the inner bottom surface of the box body in a matrix mode, and a sliding rod is slidably arranged in the sliding groove.
Further technical scheme still includes:
the inner expansion assembly comprises an insertion pipe which is inserted and installed inside the bullet guide shell, a plurality of collision assemblies are installed on the periphery of the insertion pipe, a straight rod is hinged between all the collision assemblies, a sliding sleeve is slidably installed on one side of the insertion pipe, an inclined rod is hinged to one side of the sliding sleeve, the inclined rod is hinged to one side of the collision assembly, a locking piece is installed on the surface of the sliding sleeve, a sealing sleeve is installed on one side of the insertion pipe, a hose is installed on one side of the sealing sleeve, an air valve is installed on one side of the hose, and an air pump is installed on one side of the air valve.
Further technical scheme, contradict the subassembly including switch on and install the ball support at the intubate side, set up first gas pocket between ball support and the intubate, the inside articulated ball valve of installing of ball support is provided with the second gas pocket with the position that first gas pocket corresponds on the ball valve, installs first trachea in one side of ball valve, and first tracheal inside slidable mounting has the piston, and the piston rod is installed in one side connection of piston, and extrusion piece is installed to one side of piston rod.
Further technical scheme, the material of extrusion piece is hard rubber, and the structure of extrusion piece is fan-shaped pie-shaped structure, and one side of slide bar is provided with the arc flange, and the interval between all conflict subassemblies is unanimous, and the length of piston rod is unanimous with the length of first gas tube.
Further technical scheme still includes:
the lower pressure assembly comprises a limiting disc arranged on one side of the insertion pipe, the limiting disc is lapped at one end of the missile shell, a self-locking bolt is screwed on one side of the limiting disc, a telescopic rod is arranged on one side of the insertion pipe, an outer cover is arranged on the outer side of the part, connected with the insertion pipe, of the telescopic rod, and a support is fixedly arranged on one side of the outer cover and one side of the telescopic rod.
Further technical scheme still includes:
the outer facade subassembly, outer facade subassembly is including setting up the slide rail in box one side, and the inside slidable mounting of slide rail has the slider, and the bolt is installed to one side of slider, and bolt fixed mounting is in one side of box, and the track is installed to one side of slider, and orbital inside slidable mounting has the voussoir, and the cylinder is installed to one side of voussoir, and the output of cylinder is connected at the surface of voussoir.
Further technical scheme, outer facade subassembly is still including installing the miniature air pump in voussoir one side, and the valve is installed to one side of miniature air pump, and the second trachea is installed in the switch-on of one side of valve, and the second trachea runs through and installs in the inside of voussoir, and the telescopic movable rod of installing in the tracheal inside of second, and the spheroid is installed to one side of movable rod, and the spheroid is contradicted and is installed at the surface of leading the shell case.
Further technical scheme, the structure of slide rail is right circular, and the slider is provided with the arc outer fringe with the position of slide rail contact, and the structure of slider is the T type, and the extension part overlap joint of slider is at the surface of slide rail, and the structure of voussoir is the I shape, and the thin limit joint of voussoir is in orbital inside, and the number of outer facade subassembly is three, adopts regular triangle structure to set up the clearance between the outer facade subassembly.
Further technical scheme, the spring is installed to one side of slide bar, and the spring is installed in the bottom of spout, and the electro-magnet is installed to the bottom of spout, connects in parallel each other between the electro-magnet, and the electric cabinet is installed in one side switch-on of electro-magnet, and the electric cabinet passes through the sensor to be connected with the computer.
The invention provides a processing tool for a missile shell through improvement, which has the following improvement and advantages compared with the prior art; the device aims at the technical problems existing in the missile hull clamping process in the prior art, and provides a corresponding solution:
firstly, because the missile wholly takes the shape of a conical or cylindrical irregular cavity, the end faces at two sides of the irregular cavity are generally of a cavity structure, so that a cavity adapting assembly is designed aiming at cavities with different structural shapes, the matrix control effect is realized by the assembly, and the specific principle is as follows: a plurality of sliding grooves with consistent intervals are formed in the box body in a matrix mode, sliding rods are arranged in the sliding grooves one by one, and the sliding rods are connected to the bottoms of the sliding grooves through springs. In order to realize the control of the sliding bars, an electromagnet is arranged at the bottom of each sliding groove, and can attract the sliding bars in the electrified state, so that the sliding bars move downwards, and the situation that the sliding bars are powered off is opposite; the electromagnets on the lower side of each sliding rod are independently communicated in the electric cabinet in a parallel mode, the electric cabinet is externally connected with a computer through a signal converter, the size and the shape of the cavity part of the bullet guide shell are scanned and calculated in advance through the computer, and then the electromagnets on specific positions are controlled to be electrified through electric signals. At this time, the sliding rod contacted with the solid part of the cavity moves downwards, and the peripheral sliding rods are kept in place; after the whole set of operation is finished, the slide bar is in fit with the inside of the cavity, and the depth of the slide bar in interference can be changed through the action of the spring according to the structure inside the cavity, so that the slide bar inside the cavity is completely matched with different positions on the inner surface, and the shell case is positioned in the horizontal direction.
Secondly, further, as the sliding rod positioned at the outer side of the missile shell can influence the processing of the outer edge of the shell if the sliding rod extends out, the sliding rod at the outer side of the missile shell can still be controlled to move downwards through the electric cabinet, and the part to be processed is exposed.
Thirdly, further, because only the bottom of shell case is carried out the centre gripping, hardly avoid the shell case to appear rotatory and phenomenon of turning on one's side, then we set up interior inflation subassembly, and interior inflation subassembly is just used and is got promptly, also can realize the effect of inner structure adaptation centre gripping: the intubate that the middle part set up is used for ventilating pressurization, and the inside atmospheric pressure of intubate exports the inside of ball support through first air vent, installs the second gas pocket that corresponds the position on the ball valve of ball support inside for receive the atmospheric pressure. The output air pressure can act on the piston in the first air pipe, so that the piston rod is pushed to be unfolded outwards, and the extrusion blocks at the end face part are abutted against different positions in the cartridge case to realize positioning. Because the extrusion piece is hard rubber material, and set up to fan-shaped structure for the extrusion piece has better butt adaptation effect.
Fourthly, because the inner expansion assembly is directly inserted into the shell, the inner expansion assembly must be capable of contracting itself, otherwise the inner expansion assembly is difficult to disassemble and assemble. The sliding sleeve is slidably arranged on the surface of the cannula, the inclined rod and the straight rod are respectively hinged between the sliding sleeve and the abutting component, the abutting component and the abutting component, when the sliding sleeve is moved, the abutting component utilizes the hinging action of the ball valve and the ball support, the effect similar to opening and closing of the umbrella is achieved, and then the inner expansion component is extracted and put in.
Fifthly, because the weights of different cartridge cases are different, the cartridge cases need to be pressurized, so that the cartridge cases are more stably butted in the cavity adapting assembly. The limiting disc is pressed down through the telescopic rod, and then the pressing effect of the shell case is realized. The integral positioning effect of the inner expansion assembly is realized through the self-locking bolt. The positioning effect of the pressing component is achieved through the outer cover and the support.
Because of the processing requirement, the large cavity end of the shell sometimes needs to be processed, the missile shell needs to be inversely installed, and rollover of the missile shell is easy to occur only under the clamping action of the cavity adapting assembly during inversely installation. Therefore, the outer vertical surface component is arranged, the round sliding rail is arranged on the periphery of the box body, and the clamp can be clamped at any position of the outer edge of the shell. The clamping height of the wedge block in the track is controlled through the air cylinder; the movable rod inside the second air pipe is pushed to move outwards by the miniature air pump, so that the ball body is abutted against the outer edge surface of the shell case, and the auxiliary clamping effect is realized. The wedge block in the assembly adopts an I-shaped structure, so that the precision in the sliding clamping process is higher. The T-shaped structure of the sliding block can be better matched with the sliding rail, the effect of stable clamping is achieved by matching with the bolts, and the rail is prevented from being turned over wholly.
Drawings
The invention is further explained below with reference to the drawings and examples:
FIG. 1 is a schematic perspective view of the present invention;
FIG. 2 is a schematic perspective view of a cavity adapter assembly of the present invention;
FIG. 3 is a schematic longitudinal cross-sectional view of the cavity adapter assembly of the present invention;
FIG. 4 is a schematic perspective view of an inner expansion assembly according to the present invention;
FIG. 5 is a schematic cross-sectional view of an inner expansion assembly according to the present invention;
FIG. 6 is a schematic view of the partial cross-sectional structure of FIG. 5A in accordance with the present invention;
FIG. 7 is a schematic perspective view of a hold-down assembly of the present invention;
fig. 8 is a schematic perspective view of an outer facade element according to the invention.
Reference numerals illustrate: 1. A bullet guide shell; 2. a cavity adapting assembly; 3. an inner expansion assembly; 4. pressing down the assembly; 5. an outer facade assembly; 6. a case; 7. a chute; 8. a slide bar; 9. a spring; 10. an electromagnet; 11. an electric control box; 12. a cannula; 13. a sliding sleeve; 14. a diagonal rod; 15. a collision component; 16. a straight rod; 17. a limiting disc; 18. a self-locking bolt; 19. a locking member; 20. a ball support; 21. a first air hole; 22. a ball valve; 23. a second air hole; 24. a first air tube; 25. a piston; 26. a piston rod; 27. extruding a block; 28. sealing sleeve; 29. a hose; 30. an air valve; 31. an air pump; 32. a telescopic rod; 33. an outer cover; 34. a bracket; 35. a slide rail; 36. a slide block; 37. a bolt; 38. a track; 39. wedge blocks; 40. a micro air pump; 41. a valve; 42. a second air pipe; 43. a movable rod; 44. a sphere; 45. and (3) a cylinder.
Detailed Description
The following detailed description of the present invention clearly and fully describes the technical solutions of the embodiments of the present invention, and it is apparent that the described embodiments are only some embodiments of the present invention, but 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 the description of the present invention, it should be noted that, directions or positional relationships indicated by terms such as "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., are based on directions or positional relationships shown in the drawings, are merely for convenience of description and simplification of description, and do not indicate or imply that the apparatus or element to be referred to must have a specific direction, be constructed and operated in the specific direction, and thus should not be construed as limiting the present invention; the terms "first," "second," "third," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying relative importance, and furthermore, unless explicitly specified and limited otherwise, the terms "mounted," "connected," "coupled," and the like are to be construed broadly, and may be fixedly coupled, detachably coupled, or integrally coupled, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present invention will be understood in specific cases by those of ordinary skill in the art.
Example 1
The invention provides a processing tool for a missile shell through improvement, which comprises the following technical scheme:
as shown in fig. 1-3, a processing tool for a missile shell, including a missile shell 1, further includes:
the cavity adaptation component 2, the cavity adaptation component 2 includes box 6, spout 7 is seted up to the interior bottom surface of box 6 in the mode of matrix, and the inside slidable mounting slide bar 8 of spout 7, spring 9 are installed to one side of slide bar 8, and spring 9 installs in the bottom of spout 7, and electro-magnet 10 is installed to the bottom of spout 7, connects in parallel each other between electro-magnet 10, and electric cabinet 11 is installed in the switch-on of one side of electro-magnet 10, and electric cabinet 11 passes through the sensor and is connected with the computer.
Because the missile wholly takes the shape of a conical or cylindrical irregular cavity, the end faces at two sides of the irregular cavity are generally of a cavity structure, so that a cavity adapting assembly 2 is designed for cavities with different structural shapes, the assembly achieves the matrix control effect, and the specific principle is as follows: a plurality of sliding grooves 7 with consistent intervals are formed in the box body 6 in a matrix mode, sliding rods 8 are arranged in the sliding grooves one by one, and the sliding rods 8 are connected to the bottom of the sliding grooves 7 through springs 9. In order to realize the control of the slide bars 8, an electromagnet 10 is arranged at the bottom of each slide groove 7, the electromagnet 10 can attract the slide bars 8 in the electrified state, so that the slide bars 8 move downwards, and the reverse is realized when the power is off; the electromagnets 10 at the lower side of each sliding rod 8 are independently communicated in the electric cabinet 11 in a parallel connection mode, the electric cabinet 11 is externally connected with a computer through a signal converter, the size and shape of the cavity part of the bullet-guiding shell 1 are scanned and calculated in advance through the computer, and then the electromagnets 10 at specific positions are controlled to be electrified through electric signals.
When the tool is used, firstly, the whole bullet guide shell 1 is placed on the surface of the cavity adapting assembly 2, and under the combined action of the spring 9 and the sliding rod 8, the sliding rod 8 positioned in the cavity of the bullet guide shell is automatically adapted to the special-shaped structure in the cavity. Then starting the electromagnet 10 of the corresponding extruded downward-moving part, so that the slide rod 8 of the part always keeps the downward-pressing state, and rebound is avoided; in addition, when the outer vertical surface of the shell is required to be processed, the peripheral slide bars 8 can be moved downwards by controlling the electromagnet 10 to adsorb the peripheral slide bars 8 of the shell, so that the processing part of the outer vertical surface of the shell is exposed; at this time, the sliding rod 8 contacted with the solid part of the cavity moves downwards, and the peripheral sliding rod 8 is kept in place; since the sliding grooves 7 at the bottoms of all the sliding rods 8 are arranged in a matrix mode, and the electromagnets 10 at the bottoms are connected in parallel, the coordinate control mode is carried out by a computer: the coordinates of the electromagnets 10 of each part are respectively input on a computer, and then three-dimensional modeling of the cartridge case is input into the matrix according to the scanning mode of the cavity of the cartridge case in advance, so that the coordinates of the electromagnets 10 where the sliding rod 8 to be adsorbed is positioned are confirmed; the electromagnet 10 with corresponding coordinates is controlled to be electrified through the computer and the electric cabinet 11, so that the sliding rod 8 is adsorbed to move downwards, and finally the whole plate surface is exposed out of the groove which is matched with the clamping groove, so that the cartridge case is completely clamped; after the whole set of operation is finished, the slide bar 8 is in fit with the inside of the cavity, and the depth of the slide bar 8 in interference can be changed through the action of the spring 9 according to the structure inside the cavity, so that the slide bar 8 in the cavity is completely matched with different positions on the inner surface, and the cartridge case is positioned in the horizontal direction.
Further, since the sliding rod 8 located at the outer side of the bullet guiding shell 1 may affect the processing of the outer edge of the shell if it extends, we can still control the sliding rod 8 at the outer side of the bullet guiding shell 1 to move downwards through the electric control box 11, so as to expose the portion to be processed.
Example two
Based on the first embodiment of the application, the second embodiment of the application provides another missile shell processing tool. The second embodiment is merely a preferred manner of the first embodiment, and implementation of the second embodiment does not affect the implementation of the first embodiment alone. A second embodiment of the present invention will be further described with reference to the drawings and embodiments.
As shown in fig. 1 to 8, a processing tool for a missile shell further includes:
the inner expansion assembly 3, the inner expansion assembly 3 comprises a cannula 12 which is inserted and installed in the bullet guide shell 1, a collision assembly 15 is installed on the periphery of the cannula 12, a straight rod 16 is hinged between the collision assemblies 15, a sliding sleeve 13 is slidably installed on one side of the cannula 12, a diagonal rod 14 is hinged on one side of the sliding sleeve 13, the diagonal rod 14 is hinged on one side of the collision assembly 15, a locking piece 19 is installed on the surface of the sliding sleeve 13, a sealing sleeve 28 is installed on one side of the cannula 12, a hose 29 is installed on one side of the sealing sleeve 28, an air valve 30 is installed on one side of the hose 29, and an air pump 31 is installed on one side of the air valve 30; the abutting component 15 comprises a ball support 20 which is installed on the side edge of the insertion tube 12 in a conducting mode, a first air hole 21 is formed between the ball support 20 and the insertion tube 12, a ball valve 22 is hinged inside the ball support 20, a second air hole 23 is formed in a position, corresponding to the first air hole 21, on the ball valve 22, a first air tube 24 is installed on one side of the ball valve 22, a piston 25 is installed inside the first air tube 24 in a sliding mode, a piston rod 26 is installed on one side of the piston 25 in a connecting mode, and an extrusion block 27 is installed on one side of the piston rod 26; the material of extrusion piece 27 is hard rubber, and the structure of extrusion piece 27 is fan-shaped pie-shaped structure, and one side of slide bar 8 is provided with the arc flange, and the interval between the conflict subassembly 15 is unanimous, and the length of piston rod 26 is unanimous with the length of first gas tube 24.
In the embodiment of this scheme, because only carry out the centre gripping to the bottom of shell case, the phenomenon that rotatory and turn on one's side appears in the shell case hardly is avoided, then we have set up interior inflation subassembly 3, and interior inflation subassembly 3 is just in time got, also can realize the effect of inner structure adaptation centre gripping: the cannula 12 arranged in the middle part is used for ventilation and pressurization, the air pressure in the cannula 12 is output to the inside of the ball support 20 through the first air hole 21, and the ball valve 22 arranged in the ball support 20 is provided with the second air hole 23 at the corresponding position for receiving the air pressure. The output air pressure acts on the piston 25 in the first air tube 24, so as to push the piston rod 26 to expand outwards, and the extrusion block 27 at the end face is abutted against different positions in the cartridge case to realize positioning. Because the extrusion piece 27 is made of hard rubber material and is arranged into a fan-shaped structure, the extrusion piece 27 has a good abutting adaptation effect.
Further, since the inner expansion module 3 is directly inserted into the inside of the case, it must be able to contract itself, otherwise it is difficult to disassemble and assemble. The sliding sleeve 13 is slidably arranged on the surface of the insertion tube 12, the inclined rod 14 and the straight rod 16 are respectively hinged between the sliding sleeve 13 and the abutting component 15 and between the abutting component 15 and the abutting component 15, when the sliding sleeve 13 is moved, the abutting component 15 utilizes the hinging action of the ball valve 22 and the ball support 20, the effect similar to opening and closing of an umbrella is achieved, and then the inner expansion component 3 is extracted and put in.
Processing frock is used to guided missile casing still includes:
the lower pressure component 4, the lower pressure component 4 comprises a limit disc 17 arranged on one side of the insertion tube 12, the limit disc 17 is lapped at one end of the missile shell 1, a self-locking bolt 18 is screwed and installed on one side of the limit disc 17, a telescopic rod 32 is installed on one side of the insertion tube 12, an outer cover 33 is installed on the outer side of the connecting part of the telescopic rod 32 and the insertion tube 12, and a bracket 34 is fixedly installed on one side of the outer cover 33 and one side of the telescopic rod 32.
In the embodiment of the present solution, because of the different weights of the different shells, we need to pressurize the shells so that they are more stably docked inside the cavity adapter assembly 2. The limiting disc 17 is pressed down through the telescopic rod 32, and then the pressing effect of the cartridge case is realized. The positioning effect of the whole inner expansion assembly 3 is achieved through the self-locking bolts 18. The positioning effect of the hold-down assembly 4 is achieved by the housing 33 and the bracket 34.
Processing frock is used to guided missile casing still includes: the outer vertical surface assembly 5, the outer vertical surface assembly 5 comprises a sliding rail 35 arranged on one side of the box body 6, a sliding block 36 is slidably arranged in the sliding rail 35, a bolt 37 is arranged on one side of the sliding block 36, the bolt 37 is fixedly arranged on one side of the box body 6, a track 38 is arranged on one side of the sliding block 36, a wedge 39 is slidably arranged in the track 38, a cylinder 45 is arranged on one side of the wedge 39, and the output end of the cylinder 45 is connected to the surface of the wedge 39; the facade component 5 further comprises a micro air pump 40 arranged on one side of the wedge 39, a valve 41 is arranged on one side of the micro air pump 40, a second air pipe 42 is connected on one side of the valve 41, the second air pipe 42 is arranged in the wedge 39 in a penetrating mode, a movable rod 43 is arranged in the second air pipe 42 in a telescopic mode, a ball 44 is arranged on one side of the movable rod 43, and the ball 44 is arranged on the outer surface of the bullet-guiding shell 1 in a abutting mode.
The utility model provides a missile casing is with processing frock, the structure of slide rail 35 is right circular, and the position that slider 36 and slide rail 35 contacted is provided with the arc outer fringe, and the structure of slider 36 is the T type, and the extension part overlap joint of slider 36 is on the surface of slide rail 35, and the structure of voussoir 39 is the I shape, and the thin limit joint of voussoir 39 is in the inside of track 38, and the number of facade subassembly 5 is three, adopts regular triangle structure to set up the clearance between the facade subassembly 5.
In the embodiment of the present solution, due to the need of machining, it is sometimes necessary to machine the large cavity end of the shell, which requires inverted installation of the missile shell 1, and at this time, the missile shell 1 is easy to rollover only under the clamping effect of the cavity adapting component 2. Therefore, the outer vertical surface assembly 5 is provided, and the circular sliding rail 35 is arranged on the periphery of the box body 6, so that the clamp can be clamped at any position of the outer edge of the cartridge case. The clamping height of wedge 39 inside track 38 is controlled by cylinder 45; the movable rod 43 in the second air pipe 42 is pushed to move outwards by the micro air pump 40, so that the ball 44 is abutted against the outer edge surface of the cartridge case, and the holding effect is realized. The wedge 39 in the assembly is of an I-shaped structure, so that the accuracy in the sliding clamping process is higher. The T-shaped structure of the sliding block 36 can be better matched with the sliding rail 35, and the effect of stable clamping is realized by matching with the bolt 37, so that the rail 38 is prevented from being turned over integrally.
Finally, it should be noted that: the foregoing description is only illustrative of the preferred embodiments of the present invention, and although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that modifications may be made to the embodiments described, or equivalents may be substituted for elements thereof, and any modifications, equivalents, improvements or changes may be made without departing from the spirit and principles of the present invention.
Claims (9)
1. The utility model provides a missile casing is with processing frock, includes and leads shell case (1), its characterized in that still includes:
the cavity adaptation component (2), the cavity adaptation component (2) comprises a box body (6), a sliding groove (7) is formed in the inner bottom surface of the box body (6) in a matrix mode, and a sliding rod (8) is slidably arranged in the sliding groove (7).
2. The missile hull machining tool of claim 1, further comprising: interior inflation subassembly (3), interior inflation subassembly (3) are including pegging graft and are installed inside intubate (12) at guide shell (1), a plurality of conflict subassembly (15) are installed to the periphery of intubate (12), all articulated between conflict subassembly (15) install straight-bar (16), one side slidable mounting of intubate (12) has sliding sleeve (13), inclined rod (14) are installed in articulated one side of sliding sleeve (13), inclined rod (14) are installed in one side of contradicting subassembly (15) in articulated, surface mounting of sliding sleeve (13) has retaining member (19), seal cover (28) are installed to one side of intubate (12), hose (29) are installed to one side of seal cover (28), pneumatic valve (30) are installed to one side of hose (29), air pump (31) are installed to one side of pneumatic valve (30).
3. The missile hull machining tool of claim 2, wherein: the utility model provides a ball valve, including opening and installing ball support (20) at intubate (12) side, first air vent (21) have been seted up between ball support (20) and intubate (12), ball valve (22) are installed in the inside articulated of ball support (20), the position that corresponds with first air vent (21) on ball valve (22) is provided with second gas vent (23), first trachea (24) are installed to one side of ball valve (22), the inside slidable mounting of first trachea (24) has piston (25), piston rod (26) are installed in connection of one side of piston (25), extrusion piece (27) are installed to one side of piston rod (26).
4. A missile hull machining tool according to claim 3, wherein: the material of extrusion piece (27) is hard rubber, the structure of extrusion piece (27) is fan-shaped pie-shaped structure, one side of slide bar (8) is provided with the arc flange, all the interval between conflict subassembly (15) is unanimous, the length of piston rod (26) is unanimous with the length of first gas tube (24).
5. The missile hull machining tool of claim 2, further comprising: the utility model provides a push down subassembly (4), push down subassembly (4) including setting up limiting plate (17) in intubate (12) one side, limiting plate (17) overlap joint is in the one end of guided missile shell (1), self-locking bolt (18) are installed in one side screwing of limiting plate (17), telescopic link (32) are installed to one side of intubate (12), dustcoat (33) are installed in the position outside that telescopic link (32) are connected with intubate (12), dustcoat (33) have support (34) with one side fixed mounting of telescopic link (32).
6. The missile hull machining tool of claim 1, further comprising: the utility model provides a facade subassembly (5), facade subassembly (5) is including setting up slide rail (35) in box (6) one side, the inside slidable mounting of slide rail (35) has slider (36), bolt (37) are installed to one side of slider (36), bolt (37) fixed mounting is in one side of box (6), track (38) are installed to one side of slider (36), the inside slidable mounting of track (38) has voussoir (39), cylinder (45) are installed to one side of voussoir (39), the surface at voussoir (39) is connected to the output of cylinder (45).
7. The missile hull machining tool of claim 6, wherein: the utility model discloses a miniature air pump, including outer facade subassembly (5), including wedge (39), install miniature air pump (40) in wedge (39) one side, valve (41) are installed to one side of miniature air pump (40), second trachea (42) are installed in the switch-on of one side of valve (41), second trachea (42) run through and install in the inside of wedge (39), movable rod (43) are installed in the inside flexible of second trachea (42), spheroid (44) are installed to one side of movable rod (43), spheroid (44) contradict and install the surface at bullet-guiding shell (1).
8. The missile hull machining tool of claim 7, wherein: the structure of slide rail (35) is the right circular, the position that slider (36) and slide rail (35) contacted is provided with the arc outer fringe, the structure of slider (36) is the T type, the extension part overlap joint of slider (36) is on the surface of slide rail (35), the structure of voussoir (39) is the I shape, the thin limit joint of voussoir (39) is in the inside of track (38), the number of facade subassembly (5) is three, adopt regular triangle structure to set up the clearance between facade subassembly (5).
9. The missile hull machining tool of claim 1, wherein: the automatic sliding device is characterized in that a spring (9) is arranged on one side of the sliding rod (8), the spring (9) is arranged at the bottom of the sliding groove (7), an electromagnet (10) is arranged at the bottom of the sliding groove (7), the electromagnets (10) are connected in parallel, an electric cabinet (11) is arranged on one side of the electromagnet (10) in a connected mode, and the electric cabinet (11) is connected with a computer through a sensor.
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| CN202310582933.5A CN116329987B (en) | 2023-05-23 | 2023-05-23 | Missile casing is with processing frock |
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| CN202310582933.5A CN116329987B (en) | 2023-05-23 | 2023-05-23 | Missile casing is with processing frock |
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| CN116329987B CN116329987B (en) | 2023-08-04 |
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| CN116329987B (en) | 2023-08-04 |
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