CN114226478A

CN114226478A - Automatic stretching device of energetic powder material copper pipe for aerospace initiating explosive device

Info

Publication number: CN114226478A
Application number: CN202111443315.XA
Authority: CN
Inventors: 汪辉强; 龚读; 王鹏飞; 周浩; 赵哲; 文京东
Original assignee: Sichuan Aerospace Chuannan Initiating Explosive Technology Ltd
Current assignee: Sichuan Aerospace Chuannan Initiating Explosive Technology Ltd
Priority date: 2021-11-30
Filing date: 2021-11-30
Publication date: 2022-03-25
Anticipated expiration: 2041-11-30
Also published as: CN114226478B

Abstract

The invention relates to an automatic stretching device of an energy-containing powder material copper pipe for an aerospace initiating explosive device, which comprises a stretching die, a stretching die and a stretching die, wherein the stretching die is used for enabling an aerospace cutting cable to pass through a die hole of the stretching die, so that cold drawing stretching of the aerospace cutting cable is realized; the pointing mechanism is used for pointing the end part of the aerospace cutting cable to be pointed so that the end part can penetrate through the die hole to facilitate stretching; the first stretching trolley and the second stretching trolley are respectively positioned at two sides of the stretching die and can move on the frame along the frame, the space cutting rope passes through the die hole, the first stretching trolley is used for carrying the space cutting rope in a stretching processing state to move towards one side of the stretching die, and the second stretching trolley is used for carrying the space cutting rope in the stretching processing state to move towards the other side of the stretching die and perform the stretching in turn, so that the space cutting rope is stretched under the extrusion of the die hole; the frame is used for installing a stretching die, a pointing mechanism and a stretching trolley and supporting the aerospace cutting rope in stretching and pointing.

Description

Automatic stretching device of energetic powder material copper pipe for aerospace initiating explosive device

Technical Field

The invention relates to aerospace cutting cable processing equipment, in particular to an automatic stretching device for an energy-containing powder material copper pipe for an aerospace initiating explosive device.

Background

The aerospace cutting rope is a metal pipe filled with explosives, an energy-gathering angle is arranged on the metal pipe, and high-temperature and high-pressure metal jet flow can be generated when the explosives are exploded to cut metal materials. At present, the aerospace cutting rope is processed mainly by filling explosives in a thicker metal tube, sealing the metal tube, gradually elongating the aerospace cutting rope by using a stretching die and a stretching machine, and gradually deforming the cross section of the aerospace cutting rope to a preset shape and size, so that the energy sprayed by an energy-gathering angle of the aerospace cutting rope during use can meet the cutting requirement.

The drawing processing of the aerospace cutting rope mainly comprises the steps of pointing the end part of the aerospace cutting rope, then drawing the aerospace cutting rope through a die hole, and repeating the steps until the aerospace cutting rope reaches a preset size. At present, due to the fact that the interior of the aerospace cutting rope has the explosive property, a stretcher is semi-automatic, operators need to pay attention to the temperature of the aerospace cutting rope during machining in real time to ensure safety, and in addition, the size of the aerospace cutting rope after being stretched every time is detected manually, so that the machining qualification every time is ensured, and the qualification rate of final finished products can be ensured. However, the semi-automatic mode has low efficiency, too large degree of dependence on human, and higher experience and technical requirements on operators, so that the cost is high, and the quality of the final finished product is unstable and the rejection rate is high due to excessive subjective judgment in the operation process.

Disclosure of Invention

The technical problem solved by the invention is as follows: the defects of the prior art are overcome, the automatic stretching device for the energy-containing powder material copper pipe for the aerospace initiating explosive device is provided, the aerospace cutting cable is processed in a full-automatic processing mode, and the temperature and shape change in the processing process can be monitored and controlled, so that numerical control processing is realized, and the qualification rate and the efficiency are improved.

The technical scheme for solving the technical problem is as follows: an automatic stretching device for an energy-containing powder material copper pipe for an aerospace initiating explosive device comprises a stretching die, a pointing mechanism, a first stretching trolley, a second stretching trolley and a rack; the stretching die and the pointing mechanism are arranged in the middle of the rack, and the stretching die is arranged in a direction vertical to the length direction of the rack;

the stretching die is used for enabling the aerospace cutting rope to be stretched to penetrate through a die hole of the stretching die, so that cold drawing stretching of the aerospace cutting rope is realized;

the pointing mechanism is used for pointing the end part of the aerospace cutting cable to be pointed so that the end part can penetrate through the die hole to facilitate stretching;

the first stretching trolley and the second stretching trolley are respectively positioned at two sides of the stretching die and can move on the frame along the frame, the space cutting rope passes through the die hole, the first stretching trolley is used for carrying the space cutting rope in a stretching processing state to move towards one side of the stretching die, and the second stretching trolley is used for carrying the space cutting rope in the stretching processing state to move towards the other side of the stretching die and perform the stretching in turn, so that the space cutting rope is stretched under the extrusion of the die hole;

the frame is used for installing a stretching die, a pointing mechanism and a stretching trolley, supporting the aerospace cutting cables in stretching and pointing and discharging the aerospace cutting cables after the aerospace cutting cables are processed. .

Preferably, the rack comprises two rack side plates, a rack supporting plate, a rack guide rail, a rack, a guide plate, a storage box, N supporting mechanisms and N guide plates, wherein N is an integral multiple of 2;

the rack is a box-shaped part, the two rack side plates are baffle plates which are arranged on the box-shaped part and perpendicular to the length direction of the rack, a rack supporting plate is arranged between the two rack side plates, a rack guide rail and a rack are arranged on the rack supporting plate, the rack guide rail and the rack are arranged in parallel, N guide plates are uniformly distributed on one side of the rack supporting plate along the length direction of the rack, and the guide plates are gradually inclined downwards from one end close to the rack supporting plate to one end of the storage box;

each guide plate is provided with a guide through groove, a support mechanism is arranged at a corresponding position below the guide through groove, the support mechanism can penetrate through the guide through groove to extend up and down on the guide plate, and when the aerospace cutting rope is machined, the support mechanism penetrates through the guide through groove to extend out of the guide plate and is used for supporting the cutting rope; after the aerospace cutting rope is processed, the supporting mechanism retracts below the guide plate, and the guide plate guides and rolls the processed aerospace cutting rope into the storage cavity of the storage box for storage.

Preferably, the supporting mechanism comprises a supporting wheel, a supporting frame, a supporting wheel seat, a supporting cylinder shaft, a supporting guide shaft and a supporting cylinder;

the supporting wheel is installed on the supporting wheel seat in a circumferential rotating mode, the supporting wheel seat is respectively assembled with one end of a supporting cylinder shaft and one end of a supporting guide shaft, the other end of the supporting cylinder shaft penetrates through a supporting frame top plate and then is installed in a supporting electric cylinder, the supporting electric cylinder is fixedly installed at the bottom of the rack, the other end of the supporting guide shaft penetrates through the supporting frame top plate and is assembled with the supporting frame top plate in an axial sliding mode, and the supporting electric cylinder can drive the supporting cylinder shaft to do axial telescopic motion after being started.

Preferably, the supporting mechanism further comprises a supporting sensor, the supporting sensor is mounted on a top plate of the supporting frame, below the supporting wheel seat and close to the position of the supporting guide shaft, and the supporting frame is mounted on the machine frame; the support guide shaft is sequentially provided with a first support induction sheet, a second support induction sheet and a third support induction sheet along the axial direction of the support guide shaft, the first support induction sheet, the second support induction sheet and the third support induction sheet can respectively penetrate through the support sensor, so that the support sensor can induce the support induction sheet on the support guide shaft and input signals to the industrial personal computer, and the industrial personal computer judges the position of the current support wheel;

preferably, the third supporting induction sheet corresponds to a tip rolling state of the aerospace cutting cable, and the supporting wheel and the second aerospace cutting cable are pressed tightly at the moment, so that the second aerospace cutting cable is supported; the second supporting induction sheet corresponds to the stretching state of the space flight cutting cable, and the supporting wheel supports the first space flight cutting cable at the moment; the first supporting induction sheet enters a state below the guide plate corresponding to the supporting wheel, the supporting wheel carries the aerospace cutting rope to move downwards, then the aerospace cutting rope is separated from the supporting wheel through the blocking of the guide plate, and finally the aerospace cutting rope rolls down into the storage cavity to be stored.

Preferably, a supporting sensor frame is further installed on the top plate of the supporting frame, a supporting laser sensor is installed on the supporting sensor frame, and a light beam of the supporting laser sensor penetrates through the diversion through groove and is used for detecting the diameter of the stretched aerospace cutting cable.

Preferably, the first stretching trolley and the second stretching trolley have the same structure and respectively comprise a stretching vehicle seat, a stretching motor, a clamping jaw shell, a stretching sliding seat, a walking gear, a stretching sliding rail, a stretching seat plate and a clamping jaw shell plate;

the bottom of the stretching saddle is provided with a stretching sliding seat which is clamped with the rack guide rail and can be assembled in a sliding way; the stretching motor is mounted on the stretching saddle, a stretching motor shaft of the stretching motor penetrates through the stretching saddle and then is assembled with the walking gear, and the walking gear is in meshing transmission with the rack of the rack;

the clamping jaw shell consists of two clamping jaw transverse plates which are arranged in parallel up and down and a clamping jaw side plate which is connected with the side surfaces of the two clamping jaw transverse plates; the stretching saddle is also provided with a stretching slide rail, and the stretching slide rail is clamped with the clamping jaw transverse plate positioned below and can be assembled in a sliding manner; the drawing saddle is also provided with a saddle through groove, a drawing seat plate is further installed at one end, located at the saddle through groove, of the drawing saddle, a clamping jaw shell plate is installed at the position, corresponding to the saddle through groove, of the clamping jaw shell, the clamping jaw shell plate penetrates through the saddle through groove and can be assembled with the saddle through groove in a sliding mode, and the clamping jaw shell plate and the drawing seat plate are respectively assembled with two ends of a tension sensor;

the two stretching clamping jaws, the two stretching springs and the stretching cylinder are mounted in the clamping jaw shell, each stretching clamping jaw comprises a clamping block part and a clamping jaw arm, and the two clamping block parts penetrate through the clamping jaw shell and are clamped with the end part of the aerospace cutting cable, so that the aerospace cutting cable can be stretched; the middle part of the clamping jaw arm is respectively assembled with the two clamping jaw transverse plates in a circumferential rotating mode through a stretching rotating shaft, and one end, far away from the clamping block, of the clamping jaw arm is assembled with the clamping jaw wheel in a circumferential rotating mode through a clamping jaw wheel shaft; the two clamping jaw wheels are respectively pressed with the wedge-shaped inclined planes of the clamping jaw wedge-shaped blocks;

the clamping jaw wedge-shaped block is assembled with a stretching cylinder shaft of a stretching cylinder, and the stretching cylinder is arranged on the clamping jaw shell; the part of the clamping jaw arm between the stretching rotating shaft and the clamping block part is assembled with one end of a stretching spring, the other end of the stretching spring is assembled with a clamping jaw side plate close to the stretching spring, and the stretching spring is used for applying elastic force pulled to the clamping jaw side plate to the clamping jaw arm.

Preferably, the stretching die comprises a stretching die shell, a stretching support plate, a die rotating shaft, a die wheel, a clamping tooth, a die switching tooth, a switching motor shaft and a switching motor;

the stretching die shell is fixedly assembled with the stretching support plate, and the stretching support plate is fixedly assembled with the frame;

the two end faces of the stretching mould shell facing the two stretching trolleys are respectively provided with a stretching mould vertical plate, the stretching mould vertical plate is provided with an in-out through groove, and an aerospace cutting rope penetrates into or out of the in-out through groove; the die wheel is installed in the drawing die shell, the die wheel is sleeved on the die rotating shaft in a circumferential rotating mode, the die rotating shaft is respectively assembled with the two drawing die vertical plates in a circumferential rotating mode, a plurality of die holes distributed along the circumferential direction of the die wheel are formed in the die wheel, and the inner diameter of each die hole is gradually changed from large to small;

the side wall of the die wheel is provided with a latch, the latch is in meshing transmission with a die switching gear, the die switching gear is sleeved on a switching motor shaft, and one end of the switching motor shaft penetrates through one of the vertical plates of the stretching die and then is installed in the switching motor.

Preferably, a water distribution tank is arranged in the die shell and above the die wheel, the water distribution tank is hollow, the bottom of the water distribution tank is provided with a plurality of water distribution holes which penetrate through the water distribution tank, the interior of the water distribution tank is communicated with one end of a water inlet pipe, the other end of the water inlet pipe is communicated with an outlet of a water pump, and an inlet of the water pump is communicated with water in the water tank; a filter screen and a water tank are sequentially installed at the bottom of the stretching support plate, the filter screen is used for filtering small-particle impurities, and the water tank is used for storing cooling water.

Preferably, the die wheel is further provided with a plurality of positioning holes distributed along the circumferential direction of the die wheel, the positioning holes and the die holes corresponding to the positioning holes are on the same diameter line, and the positioning holes can be assembled with one end of the positioning telescopic shaft in an inserting manner, so that the die wheel is relatively fixed in the circumferential direction of the die wheel, the other end of the positioning telescopic shaft penetrates through the vertical plate of the stretching die close to the positioning telescopic shaft and then is installed in the positioning cylinder, and the positioning cylinder is installed on the vertical plate of the stretching die close to the positioning cylinder.

Preferably, a first transverse outer diameter sensor, a second transverse outer diameter sensor, a third transverse outer diameter sensor, a fourth transverse outer diameter sensor, a first temperature sensor, a second temperature sensor, a first vortex cooling pipe and a second vortex cooling pipe are respectively installed at the positions, close to the through grooves for the in-out of the vertical plate of the stretching die, of the aerospace cutting rope, and the first transverse outer diameter sensor, the second transverse outer diameter sensor, the third transverse outer diameter sensor and the fourth transverse outer diameter sensor are respectively located on the same cross section of the aerospace cutting rope, so that the shape change of the aerospace cutting rope on one circle of the cross section is respectively detected; the first temperature sensor and the second temperature sensor are respectively arranged on two sides of the aerospace cutting rope, and the first vortex cooling pipe and the second vortex cooling pipe are arranged on two sides of the aerospace cutting rope; the first temperature sensor and the second temperature sensor are used for detecting the temperature of the stretched aerospace cutting cable; the first vortex cooling pipe and the second vortex cooling pipe are used for blowing cold air flow to the aerospace cutting cable to accelerate cooling of the stretched aerospace cutting cable.

Preferably, the first transverse outer diameter sensor and the second transverse outer diameter sensor are respectively installed on the vertical plates of the stretching die close to the first transverse outer diameter sensor and the second transverse outer diameter sensor; and the third transverse outer diameter sensor, the fourth transverse outer diameter sensor, the first temperature sensor, the second temperature sensor, the first vortex cooling pipe and the second vortex cooling pipe are respectively arranged on the stretching support plates close to the third transverse outer diameter sensor, the fourth transverse outer diameter sensor, the first temperature sensor, the second temperature sensor, the first vortex cooling pipe and the second vortex cooling pipe.

Preferably, the pointing mechanism comprises a pointing module, the pointing module comprises a mold base, the mold base is mounted on the stretching support plate, a mold slide rail is mounted on the mold base, the mold slide rail is clamped with a mold slide block and can be assembled in a sliding mode, the mold slide block is mounted on a mold bottom plate, two mold side plates are further mounted on the mold bottom plate, mold top plates are mounted at the tops of the two mold side plates, the two mold side plates can be respectively assembled with the two pointing rotating shafts in a circumferential rotating mode, two ends of the two pointing rotating shafts penetrate through the two mold side plates and then are respectively assembled with different pointing gears, and the pointing gears on the two pointing rotating shafts, which correspond to each other, are in meshing transmission; the two rolling tip rotating shafts are respectively sleeved with a rolling tip roller, the rolling tip rollers are provided with a plurality of rolling tip grooves, the rolling tip grooves correspond to different die holes, and the inner diameters of the rolling tip grooves are distributed along the axial direction of the rolling tip rollers from large to small; one of the pointing rotating shafts is driven to rotate by a pointing motor;

preferably, a hinging seat is mounted on the top plate of the die and is hinged with one end of a pointing telescopic shaft of a pointing electric cylinder, the pointing electric cylinder is mounted on a pointing electric cylinder frame, and the pointing electric cylinder frame is assembled and fixed relative to the frame.

Preferably, the aerospace initiating explosive device is an automatic stretching device for a copper tube made of energy-containing powder materials, and further comprises a lifting mechanism, wherein the lifting mechanism comprises a lifting frame, the lifting frame is arranged on a rack, a transverse moving beam is arranged on the lifting frame, a transverse moving sliding beam and a transverse moving shaft plate are respectively arranged on the transverse moving beam, the transverse moving shaft plate and a transverse moving screw rod can be assembled in a circumferential rotating mode, the transverse moving screw rod penetrates through a transverse moving power block and is assembled with the transverse moving power block in a screwing mode through threads, the transverse moving power block is clamped and slidably sleeved on the transverse moving sliding beam, and one end of the transverse moving screw rod is assembled with an output shaft of a transverse moving motor;

the transverse moving power block is installed on the transverse moving frame, a transverse moving seat plate is further installed on the transverse moving frame, a lifting electric cylinder is installed on the transverse moving seat plate, a lifting electric cylinder shaft of the lifting electric cylinder penetrates through the transverse moving frame and then is assembled with a lifting seat, the lifting seat is further assembled with one end of a lifting guide shaft, and the other end of the lifting guide shaft penetrates through the transverse moving frame and can be axially assembled with the transverse moving frame in a sliding mode; the feeding device comprises a lifting seat, a feeding sliding seat, a feeding telescopic shaft plate, a feeding cylinder, a feeding shaft plate, a feeding sliding seat, a feeding sliding rail, a feeding shaft plate, a feeding cylinder and a feeding shaft plate, wherein the feeding sliding seat is arranged at the bottom of the lifting seat, is clamped and slidably sleeved on the feeding sliding rail, the feeding sliding rail is arranged on the feeding seat, the lifting seat is assembled with one end of the feeding telescopic shaft, the feeding telescopic shaft penetrates through the feeding shaft plate and then is arranged in the feeding cylinder, and the feeding shaft plate and the feeding cylinder are both arranged on the feeding seat; and one end of the feeding seat, which is far away from the feeding cylinder, is provided with a pointing clamping jaw, and the pointing clamping jaw is used for clamping an aerospace cutting cable in a pointing processing state. .

Preferably, the pointing clamping jaw comprises a clamping jaw seat and two clamping jaw blocks, the clamping jaw seat is mounted on the feeding seat, a clamping jaw sliding groove is formed in the clamping jaw seat, the clamping jaw sliding groove is clamped with a clamping jaw sliding block and can be assembled in a sliding mode, the clamping jaw sliding block is mounted on the clamping jaw block, a clamping block is mounted on the clamping jaw block, and the clamping block is used for clamping the second aerospace cutting cable; the two clamping jaw blocks are respectively assembled with a double-end air cylinder shaft, the double-end air cylinder shaft is arranged in a double-end air cylinder, the double-end air cylinder is arranged on an air cylinder frame, and the air cylinder frame is arranged on a clamping jaw seat.

Compared with the prior art, the invention has the beneficial effects that:

(1) the invention can realize full-automatic pointing, cold drawing and stretching, automatic discharging and size and temperature monitoring in the processing process of the aerospace cutting cable, thereby greatly improving the qualification rate of final finished products and having high production efficiency. According to the invention, a mode of comprehensively setting a pointing mechanism and a stretching die is adopted, and the aerospace cutting rope is lifted to realize pointing and stretching, and full-process automatic operation is realized, so that the safety is higher, and on the other hand, the full-automatic production can be realized after the scheme is combined with a mechanical arm, namely, the production can be realized within 24 hours, so that the productivity can be greatly improved, and the specifications of the final finished products are relatively consistent, and the qualification rate is high.

(2) The deformation quantity and the temperature of the aerospace cutting cable during cold-drawing stretching can be detected in real time by arranging the temperature sensor and the outer diameter sensor, and the cooling of the aerospace cutting cable is realized by blowing cold air to the aerospace cutting cable through the vortex cooling pipe, so that whether the size of the aerospace cutting cable meets the process requirement after each stretching can be detected, unqualified parts are corrected, defective products are abandoned, the processing efficiency is improved, and the cost is reduced.

(3) The automatic stretching type automatic detection device disclosed by the invention is used for processing and detecting in an automatic stretching mode, so that the processing consistency is ensured, the processing and detecting efficiency is improved, the labor intensity is reduced, the man-machine isolation is fundamentally realized, and the operation safety risk is avoided. Compared with the prior manual operation mode, the automatic control system has the advantages of high automation degree, high precision and high efficiency.

Drawings

FIG. 1 is a schematic front view of the structure of the embodiment of the present invention;

FIG. 2 is a schematic rear view of the structure of the embodiment of the present invention;

FIG. 3 is a schematic top view of an embodiment of the present invention;

FIG. 4 is a schematic partial view of the structure of an embodiment of the present invention;

FIG. 5 is a bottom view of the embodiment of the present invention;

FIG. 6 is a diagram of a support mechanism according to an embodiment of the present invention;

FIG. 7 is a partial view of a support mechanism according to an embodiment of the present invention;

FIG. 8 is a view of a guide shaft according to an embodiment of the present invention;

FIG. 9 is a drawing of a stretching cart according to an embodiment of the present invention;

FIG. 10 is a schematic view of a jaw housing of an embodiment of the present invention;

FIG. 11 is a front elevational view of a tip binding machine in accordance with an embodiment of the present invention;

FIG. 12 is a top plan view of a tip binding machine according to an embodiment of the present invention;

FIG. 13 is a partial view of a tip binding machine according to an embodiment of the present invention;

FIG. 14 is a partial view of a tip binding machine according to an embodiment of the present invention;

FIG. 15 is a view of the support mechanism and the tip binding machine in accordance with the present invention;

FIG. 16 is a schematic view of a pointing module according to an embodiment of the present invention;

FIG. 17 is a schematic view of a pointing jaw according to an embodiment of the present invention;

FIG. 18 is a front view of a drawing die according to an embodiment of the present invention;

FIG. 19 is a left side view of a drawing die according to an embodiment of the present invention;

FIG. 20 is a bottom view of a drawing die according to an embodiment of the present invention;

FIG. 21 is a partial view of a drawing die according to an embodiment of the present invention;

FIG. 22 is a partial view of a drawing die according to an embodiment of the present invention.

Detailed Description

The invention is further illustrated by the following examples.

The technical solution in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention.

In the description of the present invention, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention.

The first space cutting cable 01 and the second space cutting cable 02 of the embodiment are in two states during space cutting cable processing, the first space cutting cable 01 corresponds to a stretching processing state, and the second space cutting cable 02 corresponds to a pointing processing state.

Referring to fig. 1-22, the present embodiment provides a fully automatic stretching machine for processing an aerospace cutting rope, including:

the stretching die C is used for enabling the first aerospace cutting rope 01 to penetrate through the die hole C711, so that the first aerospace cutting rope is stretched;

the pointing mechanism B is used for pointing the end part of the second aerospace cutting rope 02 to enable the end part to penetrate through the die hole C711 so as to facilitate stretching;

and two stretching trolleys A are respectively positioned at two sides of the stretching die and are used for carrying the first aerospace cutting cables 01 to move, so that the first aerospace cutting cables 01 pass through the die holes C711 to be stretched.

The frame is used for installing a stretching die C, a tip rolling mechanism B and a stretching trolley A, supporting the aerospace cutting rope in the stretching and tip rolling processes, and discharging the aerospace cutting rope after the aerospace cutting rope is processed.

The drawing die C and the pointing mechanism B are mounted in the middle of the frame, the frame comprises two frame side plates 110, frame supporting plates 120 are respectively mounted on the portions, located on the two sides of the drawing die C, of the frame side plates 110, frame guide rails 210 and frame racks 220 are mounted on the frame supporting plates 120, a guide plate 140 is mounted on one side of each frame supporting plate 120, the guide plate 140 is used for guiding and rolling the processed space cutting rope into a storage cavity 131 of a storage box 130 to be stored, and the guide plate 140 is gradually inclined downwards from one end close to the frame supporting plates 120 to one end of the storage box 130, so that the guide plate 140 can guide the space cutting rope to roll into the storage cavity 131.

The guide plate 140 is provided with a guide through groove 141, the guide through groove 141 corresponds to the support mechanism 300, and the support mechanism 300 is used for supporting the aerospace cutting rope, so that the aerospace cutting rope can be kept stable during stretching and pointing processing.

The supporting mechanism 300 comprises a supporting wheel 310 and a supporting frame 330, wherein the supporting wheel 310 is circumferentially and rotatably mounted on a supporting wheel seat 320, the supporting wheel seat 320 is respectively assembled with one end of a supporting cylinder shaft 431 and one end of a supporting guide shaft 510, the other end of the supporting cylinder shaft 431 penetrates through a supporting frame top plate 331 and then is installed in a supporting cylinder 430, and the other end of the supporting guide shaft 510 penetrates through the supporting frame top plate 331 and is axially and slidably assembled with the supporting frame top plate 331; the supporting frame 330 is mounted on the frame, and the supporting cylinder 430 can drive the supporting cylinder shaft 431 to axially extend and retract after being started. The supporting guide shaft 510 is sequentially provided with a first supporting induction sheet 511, a second supporting induction sheet 512 and a third supporting induction sheet 513 along the axial direction, and the first supporting induction sheet 511, the second supporting induction sheet 512 and the third supporting induction sheet 513 can respectively penetrate through the supporting sensor 420, so that an Industrial Personal Computer (IPC) of the supporting light sensor box inputs signals and judges the current position of the supporting wheel 310. Specifically, the third supporting induction sheet 513 corresponds to a pinching state of the aerospace cutting cable, and at this time, the supporting wheel 310 is pressed against the second aerospace cutting cable 02, so as to support the second aerospace cutting cable; the second supporting induction sheet 512 corresponds to the aerospace cutting cable stretching state, and the supporting wheel supports the first aerospace cutting cable 01; the first support induction sheet 511 enters a state below the guide plate 140 corresponding to the support wheel 310, at this time, the support wheel 310 carries the space cutting rope to move downwards, then the space cutting rope is separated from the support wheel 310 by the blocking of the guide plate 140, and finally the space cutting rope rolls into the storage cavity 131 to be stored, so that the automatic material discharge of the space cutting rope is completed. In this embodiment, the support sensor 420 is a photoelectric sensor.

Preferably, a support sensor frame 340 is further installed on the support frame top plate 330, a support laser sensor 410 is installed on the support sensor frame 340, and a light beam of the support laser sensor 410 passes through the diversion through groove 141. During the use, in case tensile dolly A passes through and supports laser sensor 410 top, supports laser that laser sensor 410 sent and can be reflected, supports laser sensor 410 this moment and sends the signal to the industrial computer, and the industrial computer judges whether need support space flight cutting cable according to the moving direction of tensile dolly, if needs then start supporting the electric jar for second supports response piece 512 and arrives support sensor 420 department. When the aerospace cutting cable needs to be sharpened, the support electric cylinder synchronously rises along with the sharpening clamping jaw B250 after the sharpening clamping jaw B250 grabs the aerospace cutting cable, so that the aerospace cutting cable is effectively supported, and the aerospace cutting cable is stably lifted to the state of the second aerospace cutting cable 02.

Referring to fig. 1-5 and 9-10, the stretching trolley a comprises a stretching saddle a110, a stretching motor a210 and a jaw shell, wherein a stretching slide seat a111 is mounted at the bottom of the stretching saddle a110, and the stretching slide seat a111 is clamped with a rack guide rail 210 and can be assembled in a sliding manner; the stretching motor A210 is installed on the stretching saddle A110, a stretching motor shaft A211 of the stretching motor A210 penetrates through the stretching saddle A110 and then is assembled with the walking gear A310, and the walking gear A310 is in meshing transmission with the rack 220. When the stretching trolley A is used, the stretching motor A210 is started, so that the walking gear A310 is driven to rotate circumferentially, and the walking gear A310 is meshed with the rack 220, so that the whole stretching trolley A can slide along the rack guide rail 210.

The clamping jaw shell is composed of two clamping jaw transverse plates A140 which are arranged in parallel up and down and a clamping jaw side plate A130 which is connected with the side surfaces of the two clamping jaw transverse plates A140; the stretching saddle A110 is also provided with a stretching slide rail A120, and the stretching slide rail A210 is clamped with a clamping jaw transverse plate A140 positioned below and can be assembled in a sliding manner; the drawing saddle A110 is further provided with a saddle through groove A112, one end of the drawing saddle A110, located at the saddle through groove A112, is further provided with a drawing seat plate A113, a clamping jaw shell A142 is mounted at a position corresponding to the saddle through groove A112, the clamping jaw shell A142 penetrates through the saddle through groove A112 and is assembled with the clamping jaw shell A in a sliding mode, the clamping jaw shell A142 and the drawing seat plate A113 are respectively assembled with two ends of a tension sensor A230, during use, a drawing force of the aerospace cutting cable is detected through the tension sensor and is conveyed to an industrial personal computer, and therefore the drawing force is controlled within a preset process parameter interval, and the qualification rate of final finished products is guaranteed.

Two stretching clamping jaws A410 are installed in the clamping jaw shell, each stretching clamping jaw A410 comprises a clamping block part A411 and a clamping jaw arm A412, and the two clamping block parts A411 penetrate out of the clamping jaw shell and are clamped with the end part of the aerospace cutting cable, so that the aerospace cutting cable can be stretched; the middle part of the clamping jaw arm A412 is respectively assembled with two clamping jaw transverse plates A140 in a circumferential rotating mode through a stretching rotating shaft A610, and one end, far away from the clamping block part A411, of the clamping jaw arm A412 is assembled with a clamping jaw wheel A630 in a circumferential rotating mode through a clamping jaw wheel shaft A620; the two jaw wheels A630 are respectively pressed against the wedge-shaped inclined surfaces A421 of the jaw wedge-shaped block A420, thereby keeping the two jaw block portions A411 clamped with the aerospace cutting cable. The clamping jaw wedge block A420 is assembled with a stretching cylinder shaft A221 of a stretching cylinder A220, and the stretching cylinder A220 is installed on the clamping jaw shell. When the clamping jaw wedge-shaped block A420 is driven by the stretching cylinder A220 to move relative to the clamping jaw wheel A630, the distance between the two clamping jaw parts A411 and the clamping force of the aerospace cutting cable can be controlled. Preferably, the part of the jaw arm a412 between the tension rotating shaft a610 and the clamp block part a411 is assembled with one end of an extension spring a510, the other end of the extension spring a510 is assembled with the jaw side plate a130 close to the extension spring a510, and the extension spring a510 is used for applying an elastic force to the jaw arm a412, which pulls the jaw side plate a130, so that when the jaw wedge block a420 moves towards the tension cylinder a220, the two clamp block parts a411 can be driven to move far away from each other by the elastic force of the extension spring a510, thereby releasing the space cutting rope.

Two clamping jaw guide plates A141 are further installed between the two clamping jaw transverse plates A140, a clamping jaw guide groove A1411 is formed between the two clamping jaw guide plates A141, and the clamping jaw guide groove A1411 is clamped with the clamping jaw wedge-shaped block A420 and can be assembled in a sliding mode.

Referring to fig. 1-5 and 18-22, the stretching die C includes a stretching die shell C110 and a stretching support plate C120, the stretching die shell C110 is fixedly assembled with the stretching support plate C120, the stretching support plate C120 is fixedly assembled with the frame, a filter screen C150 and a water tank C130 are sequentially installed at the bottom of the stretching support plate C120, the filter screen C150 is used for filtering small particle impurities, and the water tank C130 is used for storing cooling water. Preferably, the screen C150 is drawably assembled with respect to the tension plate C120 to facilitate pulling the screen C150 out for cleaning after use.

The two end faces of the stretching die shell C110 facing the two stretching trolleys are respectively provided with a stretching die vertical plate C140, the stretching die vertical plate C140 is provided with an in-out through groove C141, and the aerospace cutting rope penetrates into or out of the in-out through groove C141. Install cloth water tank C430, mould wheel C710 from top to bottom in proper order in tensile mould shell C110, but mould wheel C710 circular rotation ground suit is on mould pivot C810, but mould pivot C810 respectively with two tensile mould riser C140 circular rotation assembly, still be provided with a plurality of locating hole C712, the mould hole C711 that distribute along its circumferencial direction on the mould wheel C710 respectively, the internal diameter of mould hole C711 is by big-to-little gradual change to thereby make the space flight cutting cable pass each mould hole in proper order and by tensile deformation gradually. The positioning hole C712 and the corresponding die hole C711 are on the same diameter line, and the positioning hole C712 can be assembled with one end of the positioning telescopic shaft C321 in an inserting manner, so that the die wheel C710 is fixed relatively in the circumferential direction of the die wheel C710, the other end of the positioning telescopic shaft C321 penetrates through the stretching die vertical plate C140 close to the positioning telescopic shaft C321 and then is loaded into the positioning cylinder C320, and the positioning cylinder C320 is installed on the stretching die vertical plate C140 close to the positioning cylinder C320; the side wall of the die wheel C710 is provided with a latch, the latch is in meshing transmission with the die switching gear C720, the die switching gear C720 is sleeved on the switching motor shaft C311, one end of the switching motor shaft C311 penetrates out of one of the stretching die vertical plates C140 and then is loaded into the switching motor C310, and the switching motor C310 can drive the die switching gear C720 to rotate circumferentially after being started, so that the die holes C711 correspond to the aerospace cutting cables and are sequentially stretched. In this embodiment, the switching motor C310 is a servo motor, and once it is started, the die wheel C710 can be driven to rotate by a fixed angle, so as to switch the next die hole to be opposite to the in-out through groove C141, and thus the die hole can be used for stretching.

The water distribution tank C430 is hollow and the bottom of the water distribution tank C430 is provided with a plurality of water distribution holes C431 which penetrate through the water distribution tank C, the inside of the water distribution tank C430 is communicated with one end of the water inlet pipe C410, the other end of the water inlet pipe C410 is communicated with an outlet of the water pump C340, and an inlet of the water pump C340 is communicated with water inside the water tank. During the use, the water pump is with in the water tank water pump income water distribution tank C430, and water drips in tensile mould shell C110 behind water distribution hole C431 evenly distributed to flow through mould wheel C710 in order to take away the heat on the mould wheel, thereby realize the cooling to space flight cutting cable, mould wheel, and water flows into the filter screen behind water trap C121, gets into the water tank circulation after filtering through the filter screen and uses. The water trap C121 is mounted on the tension support plate C120 below the tension die shell C110.

When different die holes C711 are required to be switched to process the aerospace cutting rope, the positioning cylinder C320 is started, the positioning telescopic shaft C321 is started to withdraw from the positioning hole C712, then the switching motor C310 is started, and the switching motor C310 drives the die wheel C710 to rotate by a certain angle to switch the die holes.

Preferably, in order to effectively control the temperature and the cross-sectional shape during the processing of the aerospace cutting rope, the embodiment is further improved as follows:

a first transverse outer diameter sensor C331, a second transverse outer diameter sensor C332, a third transverse outer diameter sensor C333, a fourth transverse outer diameter sensor C334, a first temperature sensor C351, a second temperature sensor C352, a first vortex cooling pipe C421 and a second vortex cooling pipe C422 are respectively installed on the aerospace cutting rope near the in-out through groove C141, and the first transverse outer diameter sensor C331, the second transverse outer diameter sensor C332, the third transverse outer diameter sensor C333 and the fourth transverse outer diameter sensor C334 are respectively located on the same cross section of the aerospace cutting rope, so that shape changes on one circle of the cross section of the aerospace cutting rope are respectively detected. Specifically, the first transverse outer diameter sensor C331, the second transverse outer diameter sensor C332, the third transverse outer diameter sensor C333 and the fourth transverse outer diameter sensor C334 are all laser sensors, and the laser sensors are used for detecting the change of the distance between the space cutting cable and the space cutting cable to judge whether the deformation of the cross section of the space cutting cable after being processed meets the requirement, so that the deformation after each stretching processing can be judged to meet the preset process parameters, the yield is effectively improved, the processing defects are found in time to be corrected or discarded in time, and the manufacturing cost is reduced. The first temperature sensor C351 and the second temperature sensor C352 are respectively arranged on two sides of the aerospace cutting rope, and the first vortex cooling pipe C421 and the second vortex cooling pipe C422 are arranged on two sides of the aerospace cutting rope; the first temperature sensor C351 and the second temperature sensor C352 are used for detecting the temperature of the stretched aerospace cutting cable, so that whether the temperature of the aerospace cutting cable is within set technological parameters is judged, the processing safety is ensured, and the qualification rate of a final finished product is improved. The first vortex cooling pipe C421 and the second vortex cooling pipe C422 are both used for blowing cold air flow to the aerospace cutting cable to accelerate cooling of the stretched aerospace cutting cable, so that the temperature of the aerospace cutting cable is controlled. In this embodiment, the first vortex cooling pipe C421 and the second vortex cooling pipe C422 are both vortex coolers, and the existing products can be directly adopted. Preferably, the first lateral outer diameter sensor C331 and the second lateral outer diameter sensor C332 are respectively mounted on the stretching die vertical plate C140 close to the first lateral outer diameter sensor C331 and the second lateral outer diameter sensor C332; the third transverse outer diameter sensor C333, the fourth transverse outer diameter sensor C334, the first temperature sensor C351, the second temperature sensor C352, the first scroll cooling pipe C421 and the second scroll cooling pipe C422 are respectively mounted on the tension support plate C120 close to the third transverse outer diameter sensor C, the fourth transverse outer diameter sensor C334, the first temperature sensor C351, the second temperature sensor C352, the first scroll cooling pipe C421 and the second scroll cooling pipe C422.

Referring to fig. 1-5 and 11-17, the pointing mechanism B includes a pointing module B600, the pointing module B600 includes a mold base B610, the mold base B610 is mounted on the stretching support plate C120, a mold slide rail B530 is mounted on the mold base B610, the mold slide rail B530 is engaged with and slidably assembled with a mold slide B540, the mold slide B540 is mounted on a mold bottom plate B620, two mold side plates B630 are further mounted on the mold bottom plate B620, a mold top plate B640 is mounted on tops of the two mold side plates B630, the two mold side plates B630 are respectively circumferentially and rotatably assembled with two pointing rotating shafts B430, two ends of the two pointing rotating shafts B430 penetrate through the two mold side plates B630 and are respectively assembled with different pointing gears B720, and the pointing gears B720 on the two pointing rotating shafts B430 and corresponding to each other are engaged for transmission; the two sharpening rotating shafts B430 are respectively sleeved with a sharpening roller B710, sharpening grooves B711 are formed in the sharpening rollers B710, the sharpening grooves B711 are multiple, the sharpening grooves B711 correspond to different die holes, and the inner diameters of the sharpening grooves B711 are distributed along the axial direction of the sharpening rollers B710 from large to small. Before the aerospace cutting rope needs to penetrate through a die hole, a corresponding tip rolling groove B711 is found, then the end portion of the aerospace cutting rope is placed in the tip rolling groove B711 for tip rolling, then the tip rolling end portion of the aerospace cutting rope penetrates through the die hole, and after the penetrating end is clamped by a stretching trolley, the stretching trolley pulls the aerospace cutting rope to penetrate through the die hole to achieve cold drawing stretching.

One of the pointing rotating shafts B430 is driven to rotate by a pointing motor B350, and the pointing motor B350 can drive the two pointing rotating shafts B430 to synchronously and reversely rotate after being started, so that pointing processing of the end part of the second aerospace cutting rope 02 is realized.

The die top plate B640 is provided with an articulated seat B641, the articulated seat B641 is articulated with one end of a sharpening telescopic shaft B341 of a sharpening electric cylinder B340, the sharpening electric cylinder B340 is arranged on a sharpening electric cylinder frame B120, and the sharpening electric cylinder frame B120 is arranged on a stretching die shell C110. After the pointing electric cylinder B340 is started, the pointing telescopic shaft B341 can be driven to axially move, so that the die bottom plate B620 is driven to slide along the die sliding rail B530, different pointing grooves B711 are adjusted to correspond to the second space cutting cable 02, and the end part of the second space cutting cable 02 is pointed through the different pointing grooves B711.

Preferably, since the pointing processing position of the pointing die B600 is higher than the position where the space cutting cable passes through the die hole, a lifting mechanism is required to grab the first space cutting cable 01, and then the lifting mechanism is cooperated by the supporting mechanism 300 to lift the first space cutting cable 01 to the second space cutting cable 02 for pointing processing. The lifting mechanism comprises a lifting frame B110, the lifting frame B110 is installed on a rack, a traverse beam B210 is installed on the lifting frame B110, a traverse sliding beam B211 and a traverse shaft plate B212 are respectively arranged on the traverse beam B210, the traverse shaft plate B212 and a traverse screw B410 can be assembled in a circumferential rotating mode, the traverse screw B410 penetrates through a traverse power block B222 and is assembled with the traverse power block B through threaded screwing, the traverse power block B222 is clamped and slidably sleeved on the traverse sliding beam B211, one end of the traverse screw B410 is assembled with an output shaft of a traverse motor B310, and the traverse motor B310 can drive the traverse screw B410 to rotate forwards and reversely after being started, so that the traverse power block B222 is driven to move axially along the traverse screw.

The transverse moving power block B222 is installed on a transverse moving frame B220, a transverse moving seat plate B221 is further installed on the transverse moving frame B220, a lifting electric cylinder B320 is installed on the transverse moving seat plate B221, a lifting electric cylinder shaft of the lifting electric cylinder B320 penetrates through the transverse moving frame B220 and then is assembled with a lifting seat B240, the lifting seat B240 is further assembled with one end of a lifting guide shaft B420, and the other end of the lifting guide shaft B420 penetrates through the transverse moving frame B220 and can be axially assembled with the lifting guide shaft B in a sliding mode. When the lifting device is used, the lifting electric cylinder drives the lifting cylinder shaft to stretch, so that the lifting seat B240 is driven to synchronously lift. The feeding slide seat B520 is installed at the bottom of the lifting seat B240, the feeding slide seat B520 is clamped and slidably sleeved on the feeding slide rail B510, the feeding slide rail B510 is installed on the feeding seat B230, the lifting seat B240 is assembled with one end of the feeding telescopic shaft B331, the feeding telescopic shaft B331 penetrates through the feeding shaft plate B231 and then is installed in the feeding cylinder B330, the feeding shaft plate B231 and the feeding cylinder B330 are both installed on the feeding seat B230, and when the feeding cylinder B330 drives the feeding telescopic shaft B331 to contract, the feeding shaft plate B231 is driven to move towards the lifting seat B240, so that the feeding seat B230 moves towards the pointing die B600.

A tip rolling clamping jaw B250 is arranged at one end, far away from the feeding cylinder B330, of the feeding seat B230, and the tip rolling clamping jaw B250 is used for clamping the second aerospace cutting rope 02; the tip-rolling clamping jaw B250 comprises a clamping jaw seat B251 and two clamping jaw blocks B253, the clamping jaw seat B251 is installed on a feeding seat B230, a clamping jaw sliding groove B2511 is arranged on the clamping jaw seat B251, the clamping jaw sliding groove B2511 is clamped with a clamping jaw sliding block B2531 and can be assembled in a sliding mode, the clamping jaw sliding block B2531 is installed on the clamping jaw block B253, a clamping block B2532 is installed on the clamping jaw block B253, and the clamping block B2532 is used for clamping an aerospace cutting cable.

The two clamping jaw blocks B253 are respectively assembled with the double-head cylinder shaft B361, the double-head cylinder shaft B361 is arranged in the double-head cylinder B360, and the double-head cylinder B360 can simultaneously drive the two double-head cylinder shafts B361 to synchronously draw close or keep away from each other after being started, so that the two clamping jaw blocks B253 are driven to mutually approach to clamp an aerospace cutting cable or mutually keep away from the aerospace cutting cable to release the aerospace cutting cable. The double-head cylinder B360 is arranged on a cylinder frame B252, and the cylinder frame B252 is arranged on a clamping jaw seat B251.

When pointing is needed, the lifting electric cylinder drives the pointing clamping jaw B250 to move downwards to the two clamping blocks B2532 which are respectively positioned at two sides of the first aerospace cutting cable, then the double-head cylinder is started, the double-head cylinder drives the two clamping blocks B2532 to clamp the first aerospace cutting cable, then the lifting electric cylinder drives the first aerospace cutting cable to move upwards and the supporting wheel to move upwards synchronously until the first aerospace cutting cable reaches the position of the second aerospace cutting cable 02, the pointing electric cylinder B340 is started, and the pointing electric cylinder B340 drives the pointing groove B711 to be opposite to the second aerospace cutting cable 02; then, the traversing motor B310 is started, the traversing motor B310 drives the second aerospace cutting rope 02 to move towards the die roller B710 through the traversing frame B220, and the end part of the second aerospace cutting rope 02 enters a pointing groove B711; starting a pointing motor to drive the two die rollers B710 to synchronously rotate reversely; the feeding cylinder is started, so that the feeding seat B230 is pushed to drive the second space flight cutting rope 02 to move towards the pointing groove B711, and the end part of the second space flight cutting rope enters the pointing groove B711 for pointing. And then the pointing motor is reversely rotated to extend the feeding telescopic shaft B331, so that the pointed aerospace cutting rope exits the pointing groove B711. And reversely rotating the transverse moving motor B310 to reset the space flight cutting cable, driving the space flight cutting cable to move downwards to reset by the lifting electric cylinder, clamping one end of the space flight cutting cable far away from the stretching mould by the stretching trolley, starting the feeding cylinder to drive the space flight cutting cable to move towards the mould hole, enabling the rolling tip part to pass through the mould hole, and then stretching the rolling tip part which is clamped and passed by another stretching unloading trolley. And the process is repeated until the stretching is finished. When a large error occurs in the stretching shape of the aerospace cutting rope during processing, the aerospace cutting rope needs to be stopped in time to wait for the detection of workers, and if the aerospace cutting rope is scrapped, the aerospace cutting rope needs to be directly discarded, so that the cost is prevented from being increased.

The foregoing detailed description of the preferred embodiments of the invention has been presented. It should be understood that numerous modifications and variations could be devised by those skilled in the art in light of the present teachings without departing from the inventive concepts. Therefore, the technical solutions available to those skilled in the art through logic analysis, reasoning and limited experiments based on the prior art according to the concept of the present invention should be within the scope of protection defined by the claims.

Claims

1. An automatic stretching device for an energy-containing powder material copper pipe for an aerospace initiating explosive device is characterized by comprising a stretching die, a pointing mechanism, a first stretching trolley, a second stretching trolley and a rack; the stretching die and the pointing mechanism are arranged in the middle of the rack, and the stretching die is arranged in a direction vertical to the length direction of the rack;

2. The automatic stretching device for the energy-containing powder material copper tube for the aerospace initiating explosive device according to claim 1, wherein the frame comprises two frame side plates, a frame supporting plate, a frame guide rail, a frame rack, a guide plate, a storage box, N supporting mechanisms and N guide plates, wherein N is an integral multiple of 2;

3. The automatic stretching device for the energy-containing powder material copper pipe for the aerospace initiating explosive device according to claim 1, wherein the supporting mechanism comprises a supporting wheel, a supporting frame, a supporting wheel seat, a supporting cylinder shaft, a supporting guide shaft and a supporting electric cylinder;

4. The automatic stretching device for the energy-containing powder material copper tube for the aerospace initiating explosive device according to claim 1, wherein the supporting mechanism further comprises a supporting sensor, the supporting sensor is mounted below a supporting wheel seat on a top plate of a supporting frame and close to a supporting guide shaft, and the supporting frame is mounted on a rack; support the guiding axle and install first support response piece, second in proper order along its axial and support response piece, third and support the response piece, first support response piece, second support response piece, third support response piece can pass respectively and support the sensor to make support the epaxial support response piece of sensor response support guiding, and to industrial computer input signal, the industrial computer judges current supporting wheel position.

5. The automatic stretching device for the energy-containing powder material copper pipe for the aerospace initiating explosive device according to claim 2, wherein the first stretching trolley and the second stretching trolley are identical in structure and comprise stretching vehicle seats, stretching motors, clamping jaw shells, stretching sliding seats, walking gears, stretching sliding rails, stretching seat plates and clamping jaw shell plates;

6. The automatic stretching device for the energetic powder material copper tube for the aerospace initiating explosive device according to claim 2, wherein the stretching die comprises a stretching die shell, a stretching support plate, a die rotating shaft, a die wheel, a latch, a die switching tooth, a switching motor shaft and a switching motor;

7. The automatic stretching device for the copper tube made of the energy-containing powder material for the aerospace initiating explosive device according to claim 6, wherein the device is characterized in that

The water distribution tank is hollow inside the die shell and is arranged above the die wheel, a plurality of water distribution holes are formed in the bottom of the water distribution tank, the inside of the water distribution tank is communicated with one end of the water inlet pipe, the other end of the water inlet pipe is communicated with an outlet of the water pump, and an inlet of the water pump is communicated with water inside the water tank; a filter screen and a water tank are sequentially installed at the bottom of the stretching support plate, the filter screen is used for filtering small-particle impurities, and the water tank is used for storing cooling water.

8. The automatic stretching device for the energy-containing powder material copper pipe for the aerospace initiating explosive device according to claim 7, wherein the die wheel is further provided with a plurality of positioning holes distributed along the circumferential direction of the die wheel, the positioning holes and the die holes corresponding to the positioning holes are on the same diameter line, and the positioning holes can be assembled with one end of the positioning telescopic shaft in an inserting manner, so that the die wheel is relatively fixed in the circumferential direction of the die wheel, the other end of the positioning telescopic shaft penetrates through the stretching die vertical plate close to the positioning telescopic shaft and then is arranged in the positioning cylinder, and the positioning cylinder is arranged on the stretching die vertical plate close to the positioning telescopic shaft.

9. The automatic stretching device for the copper tube made of the energy-containing powder material for the aerospace initiating explosive device according to claim 8, wherein the device is characterized in that

A first transverse outer diameter sensor, a second transverse outer diameter sensor, a third transverse outer diameter sensor, a fourth transverse outer diameter sensor, a first temperature sensor, a second temperature sensor, a first vortex cooling pipe and a second vortex cooling pipe are respectively arranged at the position, close to the through groove, of the vertical plate of the stretching die, of the aerospace cutting rope, and the first transverse outer diameter sensor, the second transverse outer diameter sensor, the third transverse outer diameter sensor and the fourth transverse outer diameter sensor are respectively positioned on the same cross section of the aerospace cutting rope, so that the shape change of the aerospace cutting rope on one circle of the cross section is respectively detected; the first temperature sensor and the second temperature sensor are respectively arranged on two sides of the aerospace cutting rope, and the first vortex cooling pipe and the second vortex cooling pipe are arranged on two sides of the aerospace cutting rope; the first temperature sensor and the second temperature sensor are used for detecting the temperature of the stretched aerospace cutting cable; the first vortex cooling pipe and the second vortex cooling pipe are used for blowing cold air flow to the aerospace cutting cable to accelerate cooling of the stretched aerospace cutting cable.

10. The automatic stretching device for the copper tube made of the energy-containing powder material for the aerospace initiating explosive device according to claim 9, wherein the device is characterized in that

The first transverse outer diameter sensor and the second transverse outer diameter sensor are respectively arranged on the vertical plates of the stretching die close to the first transverse outer diameter sensor and the second transverse outer diameter sensor; and the third transverse outer diameter sensor, the fourth transverse outer diameter sensor, the first temperature sensor, the second temperature sensor, the first vortex cooling pipe and the second vortex cooling pipe are respectively arranged on the stretching support plates close to the third transverse outer diameter sensor, the fourth transverse outer diameter sensor, the first temperature sensor, the second temperature sensor, the first vortex cooling pipe and the second vortex cooling pipe.

11. The automatic stretching device for the energy-containing powder material copper pipe for the aerospace initiating explosive device according to claim 2, wherein the pointing mechanism comprises a pointing module, the pointing module comprises a mold base, the mold base is mounted on the stretching support plate, a mold slide rail is mounted on the mold base, the mold slide rail is clamped with and slidably assembled with a mold slide block, the mold slide block is mounted on a mold bottom plate, two mold side plates are further mounted on the mold bottom plate, a mold top plate is mounted on the tops of the two mold side plates, the two mold side plates are respectively circumferentially and rotatably assembled with the two pointing rotating shafts, two ends of the two pointing rotating shafts penetrate through the two mold side plates and are respectively assembled with different pointing gears, and the pointing gears on the two pointing rotating shafts, which correspond to each other, are meshed for transmission; the two rolling tip rotating shafts are respectively sleeved with a rolling tip roller, the rolling tip rollers are provided with a plurality of rolling tip grooves, the rolling tip grooves correspond to different die holes, and the inner diameters of the rolling tip grooves are distributed along the axial direction of the rolling tip rollers from large to small; one of the pointing rotating shafts is driven to rotate by a pointing motor.