CN203785559U - Small cannon launched guided missile - Google Patents
Small cannon launched guided missile Download PDFInfo
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- CN203785559U CN203785559U CN201320887261.0U CN201320887261U CN203785559U CN 203785559 U CN203785559 U CN 203785559U CN 201320887261 U CN201320887261 U CN 201320887261U CN 203785559 U CN203785559 U CN 203785559U
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- guided missile
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- missile
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Abstract
The utility model discloses a small cannon launched guided missile which comprises a guided missile part and a cannonball part. The guided missile part comprises a missile head section, a separation section, a propelling section and an air injection section. The cannonball part is located at the lower end of the guided missile part, and the air injection section, the propelling section, the separation section and the missile head section are sequentially arranged upwards. The cannonball part is used for enabling the guided missile part to be blasted off at a high initial speed, and the guided missile part is used for enabling the launched guided missile to continuously inject air to fly in an acceleration mode in the flying process. The small cannon launched guided missile is characterized in that the air injection section comprises an air injection channel, guided missile ignition and extinguishing-preventing devices, guided missile ignition and extinguishing-preventing heads and an air injection channel air inlet; the propelling section comprises guided missile propelling gunpowder, a propelling gunpowder keg, a guided missile lateral air inlet channel, a guided missile separation ignition device, a guided missile separation gunpowder ignition wire and an upper guided missile gunpowder pressing plate which can slide up and down in the propelling gunpowder keg; the separation section comprises guided missile separation gunpowder, a guided missile separation gunpowder ignition device and a guided missile separation gunpowder keg.
Description
Technical field
The present invention relates to small-sized big gun and send out guided missile, be applicable to all small-sized short-range guided missiles, belong to guided missile sciemtifec and technical sphere.
Background technology
Whole world missile development speed is exceedingly fast now, numerous in variety, but guided missile has a fatal weakness, that is exactly complex structure, with high costs, launch preparation time is long, particularly for the short-range guided missile of some hundreds of kms, need the reaction time extremely short, and need fast lower attack or the interception guided missile of launch cost continuously, but various countries also do not develop and have so small-sized short-range guided missile cheaply fast reaction performance and that can launch continuously, the present invention utilizes big gun to send out the short distance miniature missile of form transmitting, it is quick that this can realize the reaction that big gun sends out, transmitting and cheaply short-range assault or interception function continuously, its attack range substantially exceeds shell, but its cost is significantly less than again short-range guided missile, simultaneously, it can realize again fast reaction and the continuous advantage of launching that big gun is sent out, in addition this big gun transmitting apparatus can be hidden at ordinary times similar workshop size within doors and the workshop that disguises oneself as, thereby can hide enemy's satellite sounding, in wartime, rising gun tube sticks up on the roof, aim at unfriendly target transmitting attack continuously fast, this artillery is installed hiding workshop and is belonged to medium-sized workshop, it is long is no more than 100 meters, be widely no more than 30 meters, height and be no more than 10 meters, and two such artilleries can be installed to putting in every workshop, if sending out speed, such artillery big gun can reach per minute 6 ~ 10 guided missiles of firing, be arranged on border and coastal, its attack and defense ability aerial and ground will improve greatly.
Summary of the invention
The object of this invention is to provide a kind of small-sized big gun that can utilize fast artillery to launch continuously low-cost wide range miniature missile and send out guided missile.
Small-sized big gun is sent out guided missile, comprise guided missile part and shell part, guided missile partly comprises bullet section, segregation section, propelling section and jet section, shell part is in the lower end of guided missile part, be upwards jet section successively, advance section, segregation section and bullet section, the effect of shell part is that guided missile part is launched with higher initial velocity, and the effect of guided missile part is that the guided missile that big gun sends out continues jet acceleration flight in flight course, and finally with larger range and lethality, strikes target; It is characterized in that:
1, shell partly comprises the shell bottom of lowermost end, it above shell bottom, is shell ignition charge, it above shell ignition charge, is shell dryness-fire medicine, between shell ignition charge and shell dryness-fire medicine, there is one deck shell ignition charge dividing plate, in shell ignition charge dividing plate, have a plurality of shell ignition charge partition board holes, the effect in these holes is burning things which may cause a fire disaster can be delivered to shell dryness-fire medicine igniting projectile dryness-fire medicine at shell ignition charge explosion time, it above shell dryness-fire medicine, is cover at the bottom of guided missile, the part covering at the bottom of guided missile is jet section, jet section comprises jet channel, guided missile igniting and anti-extinguishing means, guided missile igniting and anti-head and the jet channel air inlet of extinguishing, jet channel is up-small and down-big cone-shaped, cone osculum is connected with advancing the bottom end opening of section, the large mouth of cone is puff prot, there are two guided missile igniting and anti-extinguishing means in jet channel lower semisection both sides, in guided missile part, by big gun, sent out while getting bore at a high speed, at the bottom of the guided missile of guided missile part bottommost, cover is pushed by the explosive force of shell ignition charge, and two guided missiles that push guided missile jet channel both sides are lighted a fire and anti-extinguishing means, when the pressure sensor in guided missile igniting and anti-extinguishing means is pressed onto certain pressure, start conductive switch, electronic impulse power supply in device for opening, thereby make guided missile igniting and the anti-head that extinguishes produce continuously electronic impulse electric spark, then light the guided missile propulsion gunpowder and the air mixture that flow in jet channel, and at the bottom of washing guided missile open, cover is separated with jet channel, the lasting Pulse Electric spark in both sides is that the guided missile propulsion gunpowder in guided missile propulsion section and air mixture are continued to the burning things which may cause a fire disaster of igniting, in addition, guided missile igniting is guided missile igniting and an anti-red heat overcoat that extinguishes with the anti-head skin that extinguishes, the igniting of this guided missile is enclosed within outward when guided missile propulsion gunpowder and air mixture burn rapidly and keeps red heat always with an anti-red heat of extinguishing, and this red heat can be lighted guided missile propulsion gunpowder and air mixture, jet channel upper semisection has the jet channel air inlet of a plurality of symmetries, the axis of these jet channel air inlets becomes 15 ° ~ 60 ° angles with jet channel axis, make from the air of jet channel air inlet spirt can and the solid fuel mixing Jet with downward flow direction that flows to of the cone osculum of jet channel upper end, advance section to comprise guided missile propulsion gunpowder, the propulsive charge bucket of splendid attire guided missile propulsion gunpowder, the guided missile side air intake duct in propulsive charge bucket bucket wall outside, guided missile burble point firearm, the separated pyrophoric ignition wire of guided missile and a guided missile gunpowder top board that energy slides up and down in propulsive charge bucket, space between guided missile gunpowder top board and propulsive charge bucket upper plate is air layer on propulsive charge, the lower end of propulsive charge bucket is an infundibulate, make guided missile propulsion gunpowder flow to jet channel from middle bell mouth, the funnel downside of propulsive charge bucket lower end is end ventilation interlayer, jet channel air inlet is connected with end ventilation interlayer, ventilation interlayer in the end is connected with the guided missile side air intake duct in propulsive charge bucket bucket wall outside again, the total air inlet of air of guided missile side air intake duct is that guided missile side-inlet is at the outermost opening making progress in the junction of segregation section and bullet section, make guided missile in flight is advanced, can continuously make air-flow blow into guided missile side-inlet, and enter into end ventilation interlayer along guided missile side air intake duct, finally by jet channel air inlet, enter into jet channel and the mixed combustion of guided missile propulsion gunpowder, produce a large amount of high-speed gas Jet with downward flow directions, guided missile part is pushed forward fast, simultaneously, in order to make guided missile propulsion gunpowder stably and with certain pressure flow to jet channel gunpowder entrance equably, on propulsive charge, near the propulsive charge bucket bucket wall of propulsive charge bucket upper plate, to have the opening of a plurality of symmetries be air layer air inlet on propulsive charge to air layer, make guided missile side inlet duct flow warp high-speed air flow some enter into air layer on propulsive charge, and push guided missile gunpowder top board, make guided missile gunpowder top board press down guided missile propulsion gunpowder from the outflow with pressure of jet channel gunpowder entrance, and the air mixing detonation spraying into jet channel air inlet, segregation section comprises the separated gunpowder of guided missile, the separated cartridge of guided missile powder flask separated with guided missile, when guided missile propulsion gunpowder is nearly finished, guided missile gunpowder top board is the funnel top edge to propulsive charge bucket bottom by air pressure, and when being pressed to pressure sensor on guided missile burble point firearm and being pressed onto certain pressure, start conductive switch, electronic impulse power supply in device for opening, make the separated cartridge of guided missile produce Pulse Electric spark, ignite the separated gunpowder of guided missile, make bullet section and segregation section, advance section, jet section of separation, because the blast of the separated gunpowder of guided missile is separated fast with propelling section by bullet section, and in the separated gunpowder explosion of guided missile, advance section still with the flight at high speed forward of guided missile part, so the blast of the separated gunpowder of guided missile is in separated bullet section and when advancing section, make to advance section to be slowed down, and bullet section is accelerated, thereby this separation makes bullet section obtain larger flying speed.
2, guided missile propulsion gunpowder is for needing oxygenation fuel, the shell dryness-fire medicine in shell with the separated gunpowder of guided missile in guided missile for not needing oxygenation fuel.
3, the diameter of guided missile and shell and the shell dryness-fire dose in shell determine the initial velocity of shell transmitting small missile, and the shell dryness-fire medicine in larger, the shell of the diameter of guided missile and shell is more, and explosive force is stronger, and the initial velocity that small missile big gun is sent out is just larger; The diameter of guided missile, initial velocity that guided missile big gun is sent out and the guided missile propulsion powder volume in guided missile determine the range of small missile, and the guided missile propulsion gunpowder in higher, the guided missile of the diameter of guided missile initial velocity larger, that guided missile big gun is sent out is more, and the range of small missile is just far away.
4, to send out the transmitting artillery of guided missile be fixed installation to this big gun, and the length of gun tube and the diameter of small missile ratio will reach 30:1 ~ 50:1.
5, to send out guided missile be anury flyer lead bullet to big gun, and big gun is sent out guided missile and got after bore guided missile part and along guided missile part central shaft, do High Rotation Speed and advance.
The present invention compared with prior art has the following advantages:
1, the present invention utilizes artillery transmitting miniature missile, make guided missile can obtain larger initial velocity when transmitting, thereby make guided missile carry less fuel in flight accelerator and can again obtain larger acceleration, and then can strengthen widely the range of this miniature missile.
2, this small-sized big gun is sent out guided missile and is had the features such as reaction speed is fast, low cost of manufacture, strike far firing range, can also realize transmitting fast continuously, thereby can aspect fixed point strike unfriendly target or interception enemy missile, there is larger advantage, in other words it is compared with guided missile that cost is low, reaction is fast and can launch continuously, it compares far firing range with shell, lethality is large, can reach 300km ~ 800 km.
Accompanying drawing explanation
Fig. 1 is the schematic diagram of the embodiment of the present invention;
Fig. 2 is middle M enlarged diagram embodiment illustrated in fig. 1;
Fig. 3 is middle N enlarged diagram embodiment illustrated in fig. 1;
Fig. 4 is middle P enlarged diagram embodiment illustrated in fig. 1;
Fig. 5 is middle Q enlarged diagram embodiment illustrated in fig. 1;
Fig. 6 is the red heat schematic diagram of lighting a fire shown in Fig. 1.
In Fig. 1-6: 1, cover 2 at the bottom of guided missile, space 3 in end cover, guided missile igniting and anti-extinguishing means 4, jet channel 5, end ventilation interlayer 6, guided missile burble point firearm 7, guided missile side air intake duct 8, guided missile propulsion gunpowder 9, tub 10, the separated pyrophoric ignition wire 11 of guided missile, the separated gunpowder 12 of guided missile, the separated cartridge 13 of guided missile, on propulsive charge, air layer 14, guided missile side-inlet 15, at the bottom of bullet, thermal insulation layer 16, bullet side thermal insulation layer 17, bullet gunpowder 18, bullet shell 19, shell bottom 20, shell ignition charge 21, shell ignition charge partition board hole 22, shell ignition charge dividing plate 23, shell dryness-fire medicine 24, shell shell 25, guided missile touch point firearm 26, guided missile igniting extinguishes 27 with anti-, jet channel air inlet 28, jet channel gunpowder entrance 29, guided missile presses harness 30, air layer air inlet 31 on guided missile gunpowder, guided missile gunpowder top board 32, jet channel wall 33, guided missile igniting and the anti-head anodal 34 that extinguishes, guided missile igniting and an anti-red heat overcoat 35 that extinguishes, guided missile igniting and the anti-negative pole 36 that extinguishes, guided missile igniting and an anti-positive discharge point 37 that extinguishes, guided missile igniting and an anti-negative discharge point A that extinguishes, bullet section B, segregation section C, advance section D, jet section of E, shell part.
The specific embodiment
In the embodiment shown in Fig. 1-6: small-sized big gun is sent out guided missile, comprise guided missile part and shell part E, guided missile partly comprises bullet section A, segregation section B, advances section C and jet section of D, shell part E is in the lower end of guided missile part, upwards jet section of D, propelling section C, segregation section B and bullet section A successively, the effect of shell part E is that guided missile part is launched with higher initial velocity, the effect of guided missile part is that the guided missile that big gun sends out continues jet acceleration flight in flight course, and finally with larger range and lethality, strikes target, it is characterized in that: shell part E comprises the shell bottom 19 of lowermost end, shell bottom 19 is shell ignition charge 20 above, shell ignition charge 20 is shell dryness-fire medicine 23 above, between shell ignition charge 20 and shell dryness-fire medicine 23, there is one deck shell ignition charge dividing plate 22, in shell ignition charge dividing plate 22, have a plurality of shell ignition charge partition board holes 21, the effect in these holes is burning things which may cause a fire disaster can be delivered to shell dryness-fire medicine 23 igniting projectile dryness-fire medicine 23 at shell ignition charge 20 explosion times, shell dryness-fire medicine 23 is cover 1 at the bottom of guided missile above, at the bottom of guided missile, cover 1 part covering is jet section of D, jet section of D comprises jet channel 4, guided missile igniting and anti-extinguishing means 3, guided missile igniting extinguishes 26 and jet channel air inlet 27 with anti-, jet channel 4 is up-small and down-big cone-shaped, cone osculum is connected with advancing the propulsive charge bucket bell mouth of section C, the large mouth of cone is puff prot, there are two guided missile igniting and anti-extinguishing means 3 in jet channel 4 lower semisection both sides, in guided missile part, by big gun, sent out while getting bore at a high speed, at the bottom of the guided missile of guided missile part bottommost, cover 1 is pushed by the explosive force of shell ignition charge 20, and two guided missiles that push guided missile jet channel 4 both sides are lighted a fire and anti-extinguishing means 3, when the pressure sensor in guided missile igniting and anti-extinguishing means 3 is pressed onto certain pressure, start conductive switch, electronic impulse power supply in device for opening, thereby make guided missile igniting extinguish 26 and produce continuously electronic impulse electric spark with anti-, then light the guided missile propulsion gunpowder 8 and the air mixture that flow in jet channel 4, and at the bottom of washing guided missile open, cover 1 is separated with jet channel 4, the lasting Pulse Electric spark in both sides is that the guided missile propulsion gunpowder in guided missile propulsion section C 8 and air mixture are continued to the burning things which may cause a fire disaster of igniting, in addition, guided missile igniting is guided missile igniting and an anti-red heat overcoat 34 that extinguishes with anti-26 skin that extinguish, this guided missile igniting keeps red heat with an anti-red heat overcoat 34 that extinguishes when guided missile propulsion gunpowder 8 and air mixture burn rapidly always, and this red heat can be lighted guided missile propulsion gunpowder 8 and air mixture, jet channel 4 upper semisections have the jet channel air inlet 27 of a plurality of symmetries, the axis of these jet channel air inlets 27 becomes 15 ° ~ 60 ° angles with jet channel 4 axis, make from the air of jet channel air inlet 27 spirts can and the solid fuel mixing Jet with downward flow direction that flows to of the cone osculum of jet channel 4 upper ends, advance section C to comprise guided missile propulsion gunpowder 8, the propulsive charge bucket of splendid attire guided missile propulsion gunpowder 8, the guided missile side air intake duct 7 in propulsive charge bucket bucket wall outside, guided missile burble point firearm 6, the separated pyrophoric ignition wire 10 of guided missile and a guided missile gunpowder top board 31 that energy slides up and down in propulsive charge bucket, space between guided missile gunpowder top board 31 and propulsive charge bucket upper plate is air layer 13 on propulsive charge, the lower end of propulsive charge bucket is an infundibulate, make guided missile propulsion gunpowder 8 can flow to from middle bell mouth jet channel 4, the funnel downside of propulsive charge bucket lower end is end ventilation interlayer 5, jet channel air inlet 27 is connected with end ventilation interlayer 5, ventilation interlayer 5 in the end is connected with the guided missile side air intake duct 7 in propulsive charge bucket bucket wall outside again, the total air inlet of air of guided missile side air intake duct 7 is that guided missile side-inlet 14 is at the outermost opening making progress in the junction of segregation section B and bullet section A, make guided missile in flight is advanced, can continuously make air-flow blow into guided missile side-inlet 14, and enter into end ventilation interlayer 5 along guided missile side air intake duct 7, finally by jet channel air inlet 27, enter into jet channel 4 and 8 mixed combustions of guided missile propulsion gunpowder, produce a large amount of high-speed gas Jet with downward flow directions, guided missile part is pushed forward fast, simultaneously, in order to make guided missile propulsion gunpowder 8 stably and with certain pressure flow to jet channel gunpowder entrance 28 equably, on propulsive charge, near the propulsive charge bucket bucket wall of propulsive charge bucket upper plate, to have the opening of a plurality of symmetries be air layer air inlet 30 on propulsive charge to air layer 13, some enters into air layer 13 on propulsive charge to make high-speed air flow that guided missile side air intake duct 7 flows through, and push guided missile gunpowder top board 31, make guided missile gunpowder top board 31 press down guided missile propulsion gunpowder 8 from 28 outflows with pressure of jet channel gunpowder entrance, and the air mixing detonation spraying into jet channel air inlet 27, segregation section B comprises the separated gunpowder 11 of guided missile, the separated cartridge 12 of guided missile powder flask separated with guided missile, when guided missile propulsion gunpowder 8 is nearly finished, guided missile gunpowder top board 31 is the funnel top edge to propulsive charge bucket bottom by air pressure, and when being pressed to pressure sensor on guided missile burble point firearm 6 and being pressed onto certain pressure, start conductive switch, electronic impulse power supply in device for opening, make the separated cartridge 12 of guided missile produce Pulse Electric spark, ignite the separated gunpowder 11 of guided missile, make bullet section A and segregation section B, advance section C, jet section of D separation, because the blast of the separated gunpowder 11 of guided missile is separated fast with propelling section C by bullet section A, and in separated gunpowder 11 blasts of guided missile, advance section C still with the flight at high speed forward of guided missile part, so the blast of the separated gunpowder 11 of guided missile is at separated bullet section A and when advancing section C, make to advance section C to slow down, and bullet section A is accelerated, thereby this separation makes bullet section, A has obtained larger flying speed.
Guided missile propulsion gunpowder 8 is for needing oxygenation fuel, the shell dryness-fire medicine 23 in shell with the separated gunpowder 11 of guided missile in guided missile for not needing oxygenation fuel.
The diameter of guided missile and shell and the shell dryness-fire medicine in shell 23 amounts determine the initial velocity of shells transmitting small missiles, i.e. shell dryness-fire medicine more than 23 in larger, the shell of the diameter of guided missile and shell, and explosive force is stronger, and the initial velocity that small missile big gun is sent out is just larger; The diameter of guided missile, initial velocity that guided missile big gun is sent out and 8 amounts of the guided missile propulsion gunpowder in guided missile determine the range of small missiles, i.e. guided missile propulsion gunpowder more than 8 in higher, the guided missile of the diameter of guided missile initial velocity larger, that guided missile big gun is sent out, and the range of small missile is just far away.
The transmitting artillery that this big gun is sent out guided missile is fixed installation, and the length of gun tube and the diameter of small missile ratio will reach 30:1 ~ 50:1.
It is anury flyer lead bullet that big gun is sent out guided missile, and big gun is sent out guided missile and got after bore guided missile part and along guided missile part central shaft, do High Rotation Speed and advance.
Claims (2)
1. small-sized big gun is sent out guided missile, comprise guided missile part and shell part (E), guided missile partly comprises bullet section (A), segregation section (B), advances section (C) and jet section (D), shell part (E), in the lower end of guided missile part, is upwards jet section (D), propelling section (C), segregation section (B) and bullet section (A) successively, it is characterized in that: shell part (E) comprises the shell bottom (19) of lowermost end, shell bottom (19) is shell ignition charge (20) above, shell ignition charge (20) is shell dryness-fire medicine (23) above, between shell ignition charge (20) and shell dryness-fire medicine (23), there is one deck shell ignition charge dividing plate (22), in shell ignition charge dividing plate (22), have a plurality of shell ignition charge partition board holes (21), shell dryness-fire medicine (23) is cover (1) at the bottom of guided missile above, the part that at the bottom of guided missile, cover (1) covers is jet section (D), jet section (D) comprises jet channel (4), guided missile igniting and anti-extinguishing means (3), guided missile igniting and anti-head (26) and the jet channel air inlet (27) of extinguishing, jet channel (4) is up-small and down-big cone-shaped, cone osculum is connected with advancing the propulsive charge bucket bell mouth of section (C), the large mouth of cone is puff prot, there are two guided missile igniting and anti-extinguishing means (3) in jet channel (4) lower semisection both sides, in guided missile part, by big gun, sent out while getting bore at a high speed, at the bottom of the guided missile of guided missile part bottommost, cover (1) is pushed by the explosive force of shell ignition charge (20), and two guided missiles that push guided missile jet channel (4) both sides are lighted a fire and anti-extinguishing means (3), when the pressure sensor in guided missile igniting and anti-extinguishing means (3) is pressed onto certain pressure, start conductive switch, electronic impulse power supply in device for opening, jet channel (4) upper semisection has the jet channel air inlet (27) of a plurality of symmetries, and the axis of these jet channel air inlets (27) becomes 15 ° ~ 60 ° angles with jet channel (4) axis, advance section (C) to comprise guided missile propulsion gunpowder (8), the propulsive charge bucket of splendid attire guided missile propulsion gunpowder (8), the guided missile side air intake duct (7) in propulsive charge bucket bucket wall outside, guided missile burble point firearm (6), the separated pyrophoric ignition wire (10) of guided missile and a guided missile gunpowder top board (31) that energy slides up and down in propulsive charge bucket, space between guided missile gunpowder top board (31) and propulsive charge bucket upper plate is air layer on propulsive charge (13), the lower end of propulsive charge bucket is an infundibulate, the funnel downside of propulsive charge bucket lower end is end ventilation interlayer (5), jet channel air inlet (27) is connected with end ventilation interlayer (5), end ventilation interlayer (5) is connected with the guided missile side air intake duct (7) in propulsive charge bucket bucket wall outside again, the total air inlet of air of guided missile side air intake duct (7) is that guided missile side-inlet (14) is at the outermost opening making progress in junction of segregation section (B) and bullet section (A), it is air layer air inlet (30) on propulsive charge that the propulsive charge bucket bucket wall of the close propulsive charge bucket upper plate of air layer on propulsive charge (13) has the opening of a plurality of symmetries, segregation section (B) comprises the separated gunpowder (11) of guided missile, the separated cartridge (12) of guided missile powder flask separated with guided missile.
2. small-sized big gun as claimed in claim 1 is sent out guided missile, it is characterized in that: it is anury flyer lead bullet that big gun is sent out guided missile, and big gun is sent out guided missile and got after bore guided missile part and along guided missile part central shaft, do High Rotation Speed and advance.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320887261.0U CN203785559U (en) | 2013-12-31 | 2013-12-31 | Small cannon launched guided missile |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320887261.0U CN203785559U (en) | 2013-12-31 | 2013-12-31 | Small cannon launched guided missile |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203785559U true CN203785559U (en) | 2014-08-20 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320887261.0U Expired - Fee Related CN203785559U (en) | 2013-12-31 | 2013-12-31 | Small cannon launched guided missile |
Country Status (1)
| Country | Link |
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| CN (1) | CN203785559U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107228603A (en) * | 2017-07-13 | 2017-10-03 | 王海龙 | A kind of multistage acceleration emitter and emitter |
| CN107328315A (en) * | 2017-07-13 | 2017-11-07 | 王海龙 | A kind of delayed exploding without dead angle canister shot and Shotgun |
| CN107356163A (en) * | 2017-07-13 | 2017-11-17 | 王海龙 | A kind of emitter and emitter |
-
2013
- 2013-12-31 CN CN201320887261.0U patent/CN203785559U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107228603A (en) * | 2017-07-13 | 2017-10-03 | 王海龙 | A kind of multistage acceleration emitter and emitter |
| CN107328315A (en) * | 2017-07-13 | 2017-11-07 | 王海龙 | A kind of delayed exploding without dead angle canister shot and Shotgun |
| CN107356163A (en) * | 2017-07-13 | 2017-11-17 | 王海龙 | A kind of emitter and emitter |
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Granted publication date: 20140820 Termination date: 20141231 |
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