CN110030886B - Rocket shell propellant automatic pouring device and rocket shell decomposing equipment - Google Patents
Rocket shell propellant automatic pouring device and rocket shell decomposing equipment Download PDFInfo
- Publication number
- CN110030886B CN110030886B CN201910428974.2A CN201910428974A CN110030886B CN 110030886 B CN110030886 B CN 110030886B CN 201910428974 A CN201910428974 A CN 201910428974A CN 110030886 B CN110030886 B CN 110030886B
- Authority
- CN
- China
- Prior art keywords
- rocket projectile
- rocket
- supporting plate
- projectile body
- propellant
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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- 239000003380 propellant Substances 0.000 title claims abstract description 39
- 230000007246 mechanism Effects 0.000 claims abstract description 84
- 238000003825 pressing Methods 0.000 claims description 38
- 230000007306 turnover Effects 0.000 claims description 26
- 239000003814 drug Substances 0.000 claims description 2
- 238000004064 recycling Methods 0.000 claims description 2
- 230000006378 damage Effects 0.000 abstract description 2
- 238000000926 separation method Methods 0.000 abstract description 2
- 238000000354 decomposition reaction Methods 0.000 abstract 1
- 238000000034 method Methods 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 239000000463 material Substances 0.000 description 2
- 239000007921 spray Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000005422 blasting Methods 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 230000036541 health Effects 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000035945 sensitivity Effects 0.000 description 1
- 231100000331 toxic Toxicity 0.000 description 1
- 230000002588 toxic effect Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B33/00—Manufacture of ammunition; Dismantling of ammunition; Apparatus therefor
- F42B33/06—Dismantling fuzes, cartridges, projectiles, missiles, rockets or bombs
Abstract
The invention discloses an automatic propellant pouring device for rocket shells and rocket shell decomposing equipment, which belong to the technical field of ammunition destruction, wherein the automatic propellant pouring device for rocket shells comprises a lathe bed, a spindle box, a spin-unloading mechanism and a clamping mechanism, and the spindle box and the spin-unloading mechanism are connected with the lathe bed through a horizontal shifting mechanism; the spin-unloading mechanism is connected with the driving part through a spindle box, and the clamping mechanism is arranged on the opposite side of the spin-unloading mechanism. According to the invention, the rocket projectile body is clamped by the clamping mechanism, and meanwhile, the jet pipe of the rocket projectile is clamped by the rotary unloading mechanism and is rotary unloaded by the driving part, so that the separation of the rocket projectile body and the jet pipe can be easily realized; the rocket projectile decomposing equipment with the rocket projectile propellant automatic pouring device can realize assembly line operation, and greatly improves the working efficiency. The invention has the advantages of compact structure and high decomposition efficiency, can greatly reduce the labor intensity of operators, and improves the safety coefficient and the degree of automation.
Description
Technical Field
The invention belongs to the technical field of ammunition destruction, and particularly relates to an automatic propellant pouring device for rocket shells and rocket shell decomposing equipment.
Background
The pouring out of the propellant of the scrapped rocket projectile is an important process for realizing the emptying separation of the energetic material and the projectile inert material, and is still in the stage of manual work at present. Because the propellant has the characteristics of blasting, the sensitivity is high, the manual emptying operation has great potential safety hazard, the safety accident is easy to occur, the manual operation is high in operation intensity and low in operation efficiency, and the personnel are in long-term close contact with the propellant, so that toxic and harmful gas volatilizes, and the occupational safety and the health of the operators are not facilitated.
Disclosure of Invention
The invention aims to provide an automatic propellant pouring device for rocket shells and rocket shell decomposing equipment, and aims to solve the technical problems that in the prior art, manual pouring of propellant in the shells has great potential safety hazard, high operation intensity and low efficiency.
In order to solve the technical problems, the invention adopts the following technical scheme:
the automatic propellant pouring device for the rocket projectile comprises a frame, a supporting plate, a turnover mechanism and a clamping mechanism for clamping the rocket projectile body, wherein the rocket projectile body is placed on the supporting plate, and the clamping mechanism and the turnover mechanism are both connected with the frame; the support plate is arranged at the top of the frame, one end of the support plate is rotationally connected with the top of the frame, and the turnover mechanism is arranged at the bottom of the support plate; one side of the frame is provided with a collecting component for recycling the propellant, and the collecting component is arranged at one end of the frame connected with the supporting plate; the turnover mechanism and the clamping mechanism are electrically connected with a control cabinet in the central control room.
Preferably, the clamping mechanism comprises a pressing plate for pressing the rocket projectile body and a lifting mechanism for driving the pressing plate to lift, and the pressing plate is arranged above the supporting plate; the pressing plate is arranged at the top of the movable end of the lifting mechanism, the movable end of the lifting mechanism penetrates through the supporting plate, and the lifting mechanism is arranged below the supporting plate; the lifting mechanism is electrically connected with the control cabinet.
Preferably, the lifting mechanism and the turnover mechanism are air cylinders or hydraulic cylinders; the lower surface of the supporting plate is rotationally connected with the top of the movable end of the turnover mechanism, the movable end of the turnover mechanism penetrates through the supporting plate, and the cylinder body of the turnover mechanism is rotationally connected with the frame.
Preferably, a pair of clamping grooves for limiting the rocket projectile body are formed in the supporting plate, and the two clamping grooves are arranged at intervals and used for limiting the front and rear parts of the rocket projectile body simultaneously.
Preferably, the supporting plate is provided with two pairs of clamping grooves which are arranged in parallel and used for limiting two rocket projectile bodies which are arranged in parallel; the pressing plate is arranged in the middle of the two pairs of clamping grooves.
Preferably, the pressing plate is connected with the movable end of the lifting mechanism through a rotating mechanism, the rotating mechanism comprises a rotating motor and a rotating shaft, the pressing plate is fixed at the tail end of the rotating shaft, an output shaft of the rotating motor is coaxially fixed with the rotating shaft, and the rotating motor is fixed at the movable end of the lifting mechanism; the rotating motor is electrically connected with the control cabinet.
The invention also provides rocket projectile decomposing equipment comprising the rocket projectile propellant automatic pouring device.
The beneficial effects of adopting above-mentioned technical scheme to produce lie in: compared with the prior art, the automatic propellant pouring device for the rocket projectile clamps the rocket projectile body on the supporting plate through the clamping mechanism, and meanwhile, the overturning mechanism can incline the rocket projectile body by a certain angle, so that the propellant in the rocket projectile body can be conveniently poured into the collecting part on one side; rocket projectile decomposing equipment with the rocket projectile propellant automatic pouring device can realize assembly line production, and greatly improves working efficiency. The invention has the advantages of compact structure and high working safety coefficient, and a worker can remotely control in a central control room, so that the personal safety of the operator can be ensured, and the working efficiency and the degree of automation are improved.
Drawings
The invention will be described in further detail with reference to the drawings and the detailed description.
Fig. 1 is a schematic structural view of an automatic propellant pouring device for rocket projectiles according to an embodiment of the present invention;
in the figure: 1-frame, 2-layer board, 3-tilting mechanism, 4-rocket projectile body, 5-clamp plate, 6-elevating system, 7-draw-in groove, 8-backup pad.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and fully with reference to the accompanying drawings, in which it is evident that the embodiments described are only some, but not all embodiments of the invention. 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.
The automatic propellant pouring device for the rocket projectile comprises a frame 1, a supporting plate 2, a turnover mechanism 3 and a clamping mechanism for clamping the rocket projectile body 4, wherein the rocket projectile body 4 is placed on the supporting plate 2, and the clamping mechanism and the turnover mechanism 3 are connected with the frame 1; the support plate 2 is arranged at the top of the frame 1, one end of the support plate 2 is rotationally connected with the top of the frame 1, and the turnover mechanism 3 is arranged at the bottom of the support plate 2; a collecting component for recovering the propellant is arranged on one side of the frame 1, and the collecting component is arranged at one end of the frame 1 connected with the supporting plate 2; the turnover mechanism 3 and the clamping mechanism are electrically connected with a control cabinet in the central control room. The collecting part adopts a collecting box or a conveying belt, so that the propellant can be conveniently and timely recovered. The rocket projectile body is placed on the supporting plate and clamped firmly by the clamping mechanism, and the overturning mechanism is driven to pour the propellant in the rocket projectile body into the collecting box or the conveying belt at one side, so that the automatic pouring of the propellant is completed. By using the technical scheme to replace manual operation, operators can operate in the central control room, so that the personal safety of the operators is ensured, and meanwhile, the degree of automation and the working efficiency are improved.
As a preferable technical scheme, the clamping mechanism comprises a pressing plate 5 for pressing the rocket projectile body 4 and a lifting mechanism 6 for driving the pressing plate 5 to lift, wherein the pressing plate 5 is arranged above the supporting plate 2; the pressing plate 5 is arranged at the top of the movable end of the lifting mechanism 6, the movable end of the lifting mechanism 6 penetrates through the supporting plate 2, and the lifting mechanism 6 is arranged below the supporting plate 2; the lifting mechanism 6 is electrically connected with the control cabinet. The pressing plate is lifted by the lifting mechanism, and when the rocket projectile body of the warhead and the spray pipe is arranged on the supporting plate after the disassembly, the pressing plate falls along with the lifting mechanism to press and fix the rocket projectile body on the pressing plate, so that the rocket projectile body can be conveniently and firmly fixed and then overturned to pour the propellant.
In one embodiment of the present invention, the lifting mechanism 6 and the tilting mechanism 3 are air cylinders or hydraulic cylinders; the lower surface of the supporting plate 2 is rotationally connected with the top of the movable end of the turnover mechanism 3, the movable end of the turnover mechanism 3 penetrates through the supporting plate 2, and the cylinder body of the turnover mechanism 3 is rotationally connected with the frame 1.
In order to conveniently limit the rocket projectile body, the supporting plate 2 is provided with a pair of clamping grooves 7 for limiting the rocket projectile body 4, and the two clamping grooves 7 are arranged at intervals and used for limiting the front and rear parts of the rocket projectile body 4 simultaneously. The front and rear parts of the rocket projectile body are simultaneously fixed by the two clamping grooves, so that the rocket projectile body is prevented from twisting in the overturning process, and the smooth dumping of the propellant is ensured.
In order to further improve the working efficiency, the supporting plate 2 is provided with two pairs of clamping grooves 7 which are arranged in parallel and are used for limiting two rocket projectile bodies 4 which are arranged in parallel; the pressing plate 5 is arranged in the middle of the two pairs of clamping grooves 7. The two pairs of clamping grooves limit the two rocket projectile bodies at the same time, and the two ends of the pressing plate are used for being fixed at the same time, so that the two rocket projectile propellants can be dumped at one time, and the working efficiency is improved.
Wherein, a horizontal shaft is arranged at one end of a top supporting plate 8 of the frame 1, a notch is processed at the middle part of the other end, the two side end parts of the supporting plate 2 are rotationally connected with the horizontal shaft through a connecting double ear, a supporting seat is arranged at the bottom surface of the supporting plate, and the end part of a piston rod of the turnover mechanism is rotationally connected with the supporting seat; the piston rod of the turnover mechanism can move in the opening of the supporting plate to realize lifting of the supporting plate. By means of the structure, the stability of the supporting plate in the overturning process can be guaranteed.
Further optimizing the technical scheme, the pressing plate 5 is connected with the movable end of the lifting mechanism 6 through the rotating mechanism, the rotating mechanism comprises a rotating motor and a rotating shaft, the pressing plate 5 is fixed at the tail end of the rotating shaft, an output shaft of the rotating motor is coaxially fixed with the rotating shaft, and the rotating motor is fixed at the movable end of the lifting mechanism 6; the rotating motor is electrically connected with the control cabinet. When the propellant in the rocket projectile body is dumped, the pressing plate is rotated to be vertical to the length direction of the rocket projectile body, so that two rocket projectile bodies can be conveniently pressed simultaneously; after the propellant is poured, the pressing plate is rotated to be consistent with the length direction of the rocket projectile body, so that the rocket projectile can be conveniently loaded and unloaded.
The invention also provides rocket projectile decomposing equipment with the rocket projectile propellant automatic pouring device. All rocket projectile decomposing equipment comprising the rocket projectile propellant automatic pouring device with the structure are within the protection scope of the invention. The rocket projectile decomposing device comprises two conveying belts driven by a power mechanism, and paired clamping grooves for supporting rocket projectile bodies are arranged on the two conveying belts at intervals; the backup pad of frame is fixed in the piston rod tip of lift pneumatic cylinder, and the lift pneumatic cylinder passes through the support frame to be fixed in on the base, and the base passes through the bolt fastening subaerial. When the rocket projectile body is conveyed forwards along with the conveying belt, the piston rod of the lifting hydraulic cylinder retracts to drive the frame and the pressing plate on the frame to descend, so that the pressing plate and the supporting plate are lower than the conveying belt; when the rocket projectile body moves to the medicine pouring station, a piston rod of the lifting hydraulic cylinder extends out, the supporting plate ascends to support the rocket projectile body by means of a clamping groove on the supporting plate, then the pressing plate ascends and rotates to be perpendicular to the rocket projectile body, and then the pressing plate descends to compress the rocket projectile body in the clamping groove and overturn, so that the propellant in the rocket projectile body can be conveniently poured into a collecting part on the side face.
In conclusion, the automatic propellant pouring device for the rocket projectile has the advantages of being simple and compact in structure and convenient and fast to operate, the decomposing efficiency of the rocket projectile can be greatly improved, the propellant in the rocket projectile can be poured out easily by means of the automatic propellant pouring device for the rocket projectile, workers can complete the decomposing and pouring of the rocket projectile only by operating in a central control room, the labor intensity of operators is reduced, the rotary discharging working efficiency of the spray pipe is improved, the working safety coefficient and the automation degree of equipment are improved, and the automatic propellant pouring device is convenient to popularize and apply.
In the foregoing description, numerous specific details are set forth in order to provide a thorough understanding of the present invention, but the present invention may be practiced in other ways other than those described herein, and persons skilled in the art will readily appreciate that the present invention is not limited to the specific embodiments disclosed above.
Claims (4)
1. An automatic propellant pouring device for rocket shells, which is characterized in that: the rocket projectile body clamping device comprises a frame, a supporting plate, a turnover mechanism and a clamping mechanism for clamping the rocket projectile body, wherein the rocket projectile body is placed on the supporting plate, and the clamping mechanism and the turnover mechanism are both connected with the frame; the support plate is arranged at the top of the frame, one end of the support plate is rotationally connected with the top of the frame, and the turnover mechanism is arranged at the bottom of the support plate; one side of the frame is provided with a collecting component for recycling the propellant, and the collecting component is arranged at one end of the frame connected with the supporting plate; the turnover mechanism and the clamping mechanism are electrically connected with a control cabinet in the central control room; the clamping mechanism comprises a pressing plate for pressing the rocket projectile body and a lifting mechanism for driving the pressing plate to lift, and the pressing plate is arranged above the supporting plate; the pressing plate is arranged at the top of the movable end of the lifting mechanism, the pressing plate is connected with the movable end of the lifting mechanism through the rotating mechanism, the movable end of the lifting mechanism penetrates through the supporting plate, and the lifting mechanism is arranged below the supporting plate; the lifting mechanism is electrically connected with the control cabinet; the lower surface of the supporting plate is rotationally connected with the top of the movable end of the turnover mechanism, and the movable end of the turnover mechanism penetrates through the supporting plate; the lifting mechanism is a lifting hydraulic cylinder, the turnover mechanism is a turnover hydraulic cylinder, and the cylinder body of the turnover hydraulic cylinder is rotationally connected with the frame; the supporting plate is provided with a pair of clamping grooves for limiting the rocket projectile body, and the two clamping grooves are arranged at intervals and are used for limiting the front and rear parts of the rocket projectile body simultaneously; when the rocket projectile body is conveyed forwards along with the conveying belt, the piston rod of the lifting hydraulic cylinder retracts to drive the frame and the pressing plate on the frame to descend, so that the pressing plate and the supporting plate are lower than the conveying belt; when the rocket projectile body moves to the medicine pouring station, a piston rod of the lifting hydraulic cylinder extends out, the supporting plate ascends to support the rocket projectile body by means of a clamping groove on the supporting plate, then the pressing plate ascends and rotates to be perpendicular to the rocket projectile body, and then the pressing plate descends to compress the rocket projectile body in the clamping groove and is overturned by the overturning hydraulic cylinder, so that the propellant in the rocket projectile body can be conveniently dumped into a collecting part on the side face.
2. An automatic propellant-dispensing device for rocket projectiles according to claim 1, wherein: two pairs of clamping grooves which are arranged in parallel are arranged on the supporting plate and are used for limiting two rocket projectile bodies which are arranged in parallel; the pressing plate is arranged in the middle of the two pairs of clamping grooves.
3. An automatic propellant-dispensing device for rocket projectiles according to claim 1, wherein: the rotating mechanism comprises a rotating motor and a rotating shaft, the pressing plate is fixed at the tail end of the rotating shaft, an output shaft of the rotating motor is coaxially fixed with the rotating shaft, and the rotating motor is fixed at the movable end of the lifting mechanism; the rotating motor is electrically connected with the control cabinet.
4. A rocket projectile decomposing device comprising a rocket projectile propellant automatic pouring device according to any one of claims 1 to 3.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910428974.2A CN110030886B (en) | 2019-05-22 | 2019-05-22 | Rocket shell propellant automatic pouring device and rocket shell decomposing equipment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910428974.2A CN110030886B (en) | 2019-05-22 | 2019-05-22 | Rocket shell propellant automatic pouring device and rocket shell decomposing equipment |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110030886A CN110030886A (en) | 2019-07-19 |
| CN110030886B true CN110030886B (en) | 2024-03-22 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910428974.2A Active CN110030886B (en) | 2019-05-22 | 2019-05-22 | Rocket shell propellant automatic pouring device and rocket shell decomposing equipment |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110030886B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114383466B (en) * | 2022-01-27 | 2023-09-29 | 唐山市安航电子科技有限公司 | Automatic change bird bullet control system that drives |
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| FR2857357B1 (en) * | 2003-07-10 | 2005-08-19 | Snpe Materiaux Energetiques | METHOD AND INSTALLATION FOR DESTRUCTION OF SOLID PROPERGOL ENGINES |
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| KR19980077305A (en) * | 1997-04-18 | 1998-11-16 | 김정국 | Cylindrical Heavy Weight Tilting Device |
| DE19916751A1 (en) * | 1999-04-14 | 2000-10-19 | Fac Frank Abels Consult & Tech | Equipment for dismantling artillery and mortar ammunition filled with explosive material involves closed chamber in which is a rotary machine with rotatable clamp chuck for retention of ammunition |
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| Publication number | Publication date |
|---|---|
| CN110030886A (en) | 2019-07-19 |
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