CN103808212A - Small missile launched by cannon - Google Patents
Small missile launched by cannon Download PDFInfo
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- CN103808212A CN103808212A CN201310748531.4A CN201310748531A CN103808212A CN 103808212 A CN103808212 A CN 103808212A CN 201310748531 A CN201310748531 A CN 201310748531A CN 103808212 A CN103808212 A CN 103808212A
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Abstract
A small missile launched by a cannon comprises a missile part and a cannonball part, wherein the missile part comprises a missile warhead section, a separating section, a boosting section and an air jetting section, the cannonball part is located at the lower end of the missile part, and the air jetting section, the boosting section, the separating section and the missile warhead section are sequentially upwards arranged on the cannonball part, the cannonball part is used for launching the missile part at high initial speed, and the missile part is used for continuing to inject air to accelerate the launched missile in the flying process. The small missile is characterized in that the air jetting section comprises an air jetting channel, a missile ignition and anti-extinguishing device, a missile ignition and anti-extinguishing head and an air jetting channel air inlet; the boosting section comprises missile boosting gunpowder, a boosting gunpowder barrel, a missile side air inlet channel, a missile separating igniter, a missile separating gunpowder igniting wire and a missile gunpowder upper press plate which can slide up and down in the boosting gunpowder barrel; the separating section comprises missile separating gunpowder, a missile separating gunpowder igniter and a missile separating gunpowder barrel.
Description
Technical field
The present invention relates to big gun and send out small 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 continuously lower attack or the interception guided missile of launch cost, 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, rising gun tube in wartime 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 big gun that can utilize fast artillery to launch continuously low cost wide range miniature missile and send out small missile.
Big gun is sent out small missile, comprise guided missile part and shell part, guided missile part 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 strikes target with larger range and lethality; It is characterized in that:
1, shell part 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 multiple 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 the bottom end opening that advances 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, sent out while at a high speed getting bore by big gun in guided missile part, 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 guided missile igniting is pressed onto certain pressure with the pressure sensor in anti-extinguishing means, 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 wash open at the bottom of guided missile and cover and separate 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 multiple 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, guided missile separates pyrophoric ignition wire 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 to be guided missile side-inlet in the junction of a segregation section and bullet section outermost opening upwards, 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 enter into jet channel and the mixed combustion of guided missile propulsion gunpowder by jet channel air inlet, 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, to have the opening of multiple symmetries near the propulsive charge bucket bucket wall of propulsive charge bucket upper plate 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 that guided missile separates gunpowder, guided missile separates cartridge and separates powder flask with guided missile, in the time that 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 guided missile separate cartridge and produce Pulse Electric spark, ignite guided missile and separate gunpowder, make bullet section and segregation section, advance section, jet section of separation, the blast that separates gunpowder due to guided missile separates bullet section fast with advancing section, and when guided missile separates gunpowder explosion, advance section still with the flight at high speed forward of guided missile part, so guided missile separates the blast of gunpowder in separating bullet section and 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, and the shell dryness-fire medicine in shell separates gunpowder for not needing oxygenation fuel with the guided missile in guided missile.
3, the shell dryness-fire dose in diameter and the shell of guided missile and shell determines 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; Guided missile propulsion powder volume in the diameter of guided missile, initial velocity and the guided missile that guided missile big gun is sent out determines 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 do High Rotation Speed along guided missile part central shaft 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 in the time of 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 its cost compared with guided missile is low, reaction is fast and can launch continuously, its far firing range, lethality compared with shell 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, guided missile separates pyrophoric ignition wire 11, guided missile separates gunpowder 12, guided missile separates cartridge 13, air layer 14 on propulsive charge, guided missile side-inlet 15, thermal insulation layer 16 at the bottom of bullet, 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: big gun is sent out small missile, comprise guided missile part and shell part E, guided missile part 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 strikes target with larger range and lethality, 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 multiple 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 the propulsive charge bucket bell mouth that advances 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, sent out while at a high speed getting bore by big gun in guided missile part, 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 guided missile igniting is pressed onto certain pressure with the pressure sensor in anti-extinguishing means 3, 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 separates 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 in the time that 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 multiple 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, guided missile separates pyrophoric ignition wire 10 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 flow to jet channel 4 from middle bell mouth, 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 to be guided missile side-inlet 14 in the junction of a segregation section B and bullet section A outermost opening upwards, 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 enter into jet channel 4 and 8 mixed combustions of guided missile propulsion gunpowder by jet channel air inlet 27, 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, to have the opening of multiple symmetries near the propulsive charge bucket bucket wall of propulsive charge bucket upper plate 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 that guided missile separates gunpowder 11, guided missile separates cartridge 12 and separates powder flask with guided missile, in the time that 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 guided missile separate cartridge 12 and produce Pulse Electric spark, ignite guided missile and separate gunpowder 11, make bullet section A and segregation section B, advance section C, jet section of D separates, because guided missile separates the blast of gunpowder 11, by bullet section A, C is quick separates with advancing section, and when guided missile separation gunpowder 11 explodes, advance section C still with the flight at high speed forward of guided missile part, so guided missile separates the blast of gunpowder 11 in separating bullet section A and 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, and the shell dryness-fire medicine 23 in shell separates gunpowder 11 for not needing oxygenation fuel with the guided missile in guided missile.
Shell dryness-fire medicine in diameter and the shell of guided missile and 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; Guided missile propulsion gunpowder in the diameter of guided missile, initial velocity and the guided missile that guided missile big gun is sent out 8 amounts 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 do High Rotation Speed along guided missile part central shaft and advance.
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Claims (4)
1. big gun is sent out small missile, comprise guided missile part and shell part (E), guided missile part comprises bullet section (A), segregation section (B), advance section (C) and jet section (D), shell part (E) is in the lower end of guided missile part, upwards jet section (D) successively, advance section (C), segregation section (B) and bullet section (A), 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 strike target with larger range and lethality, 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 multiple 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 time, 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 the propulsive charge bucket bell mouth that advances 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, sent out while at a high speed getting bore by big gun in guided missile part, 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 guided missile igniting is pressed onto certain pressure with the pressure sensor in anti-extinguishing means (3), start conductive switch, electronic impulse power supply in device for opening, thereby make guided missile igniting and the anti-head (26) that extinguishes produce continuously electronic impulse electric spark, 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) separates with jet channel (4), the lasting Pulse Electric spark in both sides is that the guided missile propulsion gunpowder (8) in guided missile propulsion section (C) 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-head (26) skin that extinguishes, this guided missile igniting keeps red heat, this red heat can light guided missile propulsion gunpowder (8) and air mixture with an anti-red heat overcoat (34) that extinguishes in the time that guided missile propulsion gunpowder (8) and air mixture burn rapidly always, jet channel (4) upper semisection has the jet channel air inlet (27) of multiple 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) spirt can and the solid fuel mixing Jet with downward flow direction that flows to of the cone osculum of jet channel (4) upper end, 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), guided missile separates pyrophoric ignition wire (10) 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, make guided missile propulsion gunpowder (8) flow to jet channel (4) from middle bell mouth, 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) to be guided missile side-inlet (14) in the junction of segregation section (B) and bullet section (A) outermost opening upwards, 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 enter into jet channel (4) and guided missile propulsion gunpowder (8) mixed combustion by jet channel air inlet (27), 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, it is air layer air inlet (30) on propulsive charge that air layer on propulsive charge (13) has the opening of multiple symmetries near the propulsive charge bucket bucket wall of propulsive charge bucket upper plate, some enters into air layer on propulsive charge (13) 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 jet channel gunpowder entrance (28) outflow with pressure, and the air mixing detonation spraying into jet channel air inlet (27), segregation section (B) comprises that guided missile separates gunpowder (11), guided missile separates cartridge (12) and separates powder flask with guided missile, in the time that 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 guided missile separate cartridge (12) and produce Pulse Electric spark, ignite guided missile and separate gunpowder (11), make bullet section (A) and segregation section (B), advance section (C), jet section (D) separates, the blast that separates gunpowder (11) due to guided missile separates bullet section (A) fast with advancing section (C), and when guided missile separates gunpowder (11) blast, advance section (C) still with the flight at high speed forward of guided missile part, so guided missile separates the blast of gunpowder (11) in separating bullet section (A) and advancing section (C), make to advance section (C) to be slowed down, and bullet section (A) is accelerated, thereby this separation makes bullet section, and (A) obtained larger flying speed, guided missile propulsion gunpowder (8) is for needing oxygenation fuel, and the shell dryness-fire medicine (23) in shell separates gunpowder (11) for not needing oxygenation fuel with the guided missile in guided missile.
2. big gun as claimed in claim 1 is sent out small missile, it is characterized in that: shell dryness-fire medicine (23) amount in diameter and the shell of guided missile and shell determines the initial velocity of shell transmitting small missile, the diameter that is guided missile and shell is larger, shell dryness-fire medicine (23) in shell is more, explosive force is stronger, and the initial velocity that small missile big gun is sent out is just larger; Guided missile propulsion gunpowder (8) amount in the diameter of guided missile, initial velocity and the guided missile that guided missile big gun is sent out determines the range of small missile, the diameter initial velocity larger, that guided missile big gun is sent out that is guided missile is higher, guided missile propulsion gunpowder (8) in guided missile is more, and the range of small missile is just far away.
3. big gun as claimed in claim 1 is sent out small missile, it is characterized in that: 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.
4. big gun as claimed in claim 1 is sent out small 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 do High Rotation Speed along guided missile part central shaft and advance.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310748531.4A CN103808212A (en) | 2013-12-31 | 2013-12-31 | Small missile launched by cannon |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310748531.4A CN103808212A (en) | 2013-12-31 | 2013-12-31 | Small missile launched by cannon |
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| Publication Number | Publication Date |
|---|---|
| CN103808212A true CN103808212A (en) | 2014-05-21 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310748531.4A Pending CN103808212A (en) | 2013-12-31 | 2013-12-31 | Small missile launched by cannon |
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| CN (1) | CN103808212A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111038699A (en) * | 2018-10-12 | 2020-04-21 | 北京理工大学 | Separable composite range extending system and method on aircraft |
-
2013
- 2013-12-31 CN CN201310748531.4A patent/CN103808212A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111038699A (en) * | 2018-10-12 | 2020-04-21 | 北京理工大学 | Separable composite range extending system and method on aircraft |
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Application publication date: 20140521 |