CN115507700A

CN115507700A - Rocket range-extending launching device without backseat

Info

Publication number: CN115507700A
Application number: CN202211158499.XA
Authority: CN
Inventors: 赵小亮; 夏勤
Original assignee: Nanjing Vocational University of Industry Technology NUIT
Current assignee: Nanjing Vocational University of Industry Technology NUIT
Priority date: 2022-09-22
Filing date: 2022-09-22
Publication date: 2022-12-23

Abstract

The invention discloses a rocket range-extending launching device without a backseat, and belongs to the field of shell launching. According to the rocket range-extending launching device without the backseat, one side of the rear end cover is provided with the water storage bin, strong brine is arranged inside the water storage bin, the middle inside the fire transmission outer protection cover is provided with the fire transmission pipe, the inside of the propellant powder chamber section is provided with propellant powder, the inside of the fire transmission pipe is provided with black powder, and the outer surface of the fire transmission pipe is provided with the plurality of fire transmission holes which are arranged in a staggered mode. The invention solves the problems of high temperature and serious recoil at the tail part of the propellant tube caused by the projectile firing in the prior art, and after the propellant powder is ignited, the generated high-pressure gas can enable the propellant powder chamber section to have a backward movement force and a forward force, so that the front and back work is kept consistent, thereby realizing balanced propellant, reducing dust, realizing dim light, micro sound and low temperature, simultaneously lightening the recoil and being difficult to cause personal injury.

Description

Rocket range-extending launching device without backseat

Technical Field

The invention relates to the technical field of shell launching, in particular to a recoil-free rocket range-extending launching device.

Background

In the process of an inner trajectory, gunpowder burns to generate high-temperature and high-pressure gas continuously, the gas quantity inevitably leads to the rise of pressure in a certain space, the projectile is pushed to move at an accelerated speed under the action of the pressure, the space behind the projectile is increased continuously, and the high-temperature gas expands to do work, so the defects of high temperature at the tail part of the launching barrel, serious recoil and the like can be caused.

And the tail part of the gun has huge fire light, dust, noise and overhigh temperature during launching, partial unexhausted gunpowder gas also exists, and the dangerous area behind the gun is very easy to cause the injury and fatigue of personnel and the difficulty in service support behind the gun.

In view of these drawbacks, it is necessary to design a rocket extended-range launching device without a rear seat.

Disclosure of Invention

The invention aims to provide a recoilless rocket range-extending launching device, which can solve the problems of high temperature at the tail part of a launching barrel and serious recoil caused by the launching of a cannonball in the prior art.

In order to achieve the purpose, the invention provides the following technical scheme: the utility model provides a rocket of no back seat increases journey emitter, includes transmission barrel and the body, the body is located the inside front end of transmission barrel, flange fixedly connected with rear end cap is passed through to the rear end of transmission barrel, one side of rear end cap is provided with the aqua storage storehouse, and the inside of aqua storage storehouse is provided with the strong brine, the inside rear end of transmission barrel is provided with passes outer safety cover of fire, pass the inside centre of the outer safety cover of fire and install the biography firetube, the outside of biography firetube is provided with the propellant powder chamber section, and the inside of propellant powder chamber section is provided with the propellant powder, just the inside of biography firetube is provided with black powder, just the surface of biography firetube is provided with the biography fire hole that a plurality of staggered arrangement.

Preferably, the rear end cover is fixedly connected with the launching barrel through a bolt, a plurality of integrally formed drain holes are formed in the outer portion of one side of the rear end cover in a surrounding mode, two exhaust grooves are formed in the outer portion of the middle of the rear end cover, exhaust groove sealing covers are connected to the inner portions of the exhaust grooves in a sealing mode through sealing cushion layers, clamp springs are arranged on the inner side of the rear end cover, and the clamp springs are connected with one end of the rear end cover.

Preferably, install the back piston that is used for sealed reservoir between rear end cap and the transmission barrel, the back piston respectively with rear end cap and transmission barrel sliding connection, just be provided with the biography gas pocket that is used for adjusting atmospheric pressure between back piston and the outer safety cover of passing a fire, pass and install the preceding piston that is used for promoting the projectile body between outer safety cover of passing a fire and the transmission barrel, preceding piston respectively with pass outer safety cover of fire and transmission barrel sliding connection, the both ends outside of passing the outer safety cover of fire all is provided with shear bolt, shear bolt is used for carrying out spacing work to back piston and preceding piston.

Preferably, one side in the middle of the outside of the rear piston is provided with a primer for outputting flame to ignite propellant powder, the primer is an electric firing primer device, and the primer is in tenon connection with the rear end of the inside of the fire transmission tube.

Preferably, the inside in biography fire hole is provided with a plurality of and is used for the slip sheet of sealed work, the slip sheet is used for igniting the propellant powder, the surface of passing fire outer safety cover passes through the rear end inner wall fixed connection of draw-in groove and transmission barrel.

Preferably, the externally mounted of preceding piston has the rubber circle, preceding piston pass through the rubber circle respectively with the launching barrel with pass fire outer protection cover sealing connection, the rubber circle is used for bearing the elastomer.

Preferably, the projectile body comprises a rocket engine cabin section, a control cabin section and a fighting cabin section, the control cabin section is located on one side of the rocket engine cabin section, the fighting cabin section is located on one side of the control cabin section, two folding tail wings are arranged at the rear end of the outer portion of the rocket engine cabin section, the two folding tail wings are movably connected with the rocket engine cabin section through hinges, two folding front wings are arranged on the outer portion of the control cabin section, and the two folding front wings are movably connected with the control cabin section through hinges.

Preferably, a centering part is arranged outside the cabin section of the warhead, the centering part is used for limiting the launching barrel and the outside of the cabin section of the warhead, a guide head is arranged at the front end of the cabin section of the warhead, a protective cover is welded to the front end of the launching barrel, and a muzzle outlet is arranged inside the protective cover.

Preferably, a water storage bin bottom plate is arranged on one side of the outer portion of the rear end cover, a plurality of integrally formed liquid discharge holes are communicated in the water storage bin bottom plate, a shearing copper sheet is fixedly connected to the inner wall of each liquid discharge hole, and the liquid discharge holes are used for extruding strong brine to impact the air discharge groove.

Preferably, a portable strap is arranged below the launching barrel, two ends of the portable strap are fixedly connected with the front end and the rear end of the lower portion of the launching barrel through buckles respectively, and the portable strap is used for bearing the whole launching barrel.

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

1. the rocket range-extending launching device without the backseat has the advantages that after the propellant is ignited, the generated high-pressure gas can enable the interior of a propellant chamber section to have backward movement force and forward force, the piston is pushed to move towards the rear end of a launching barrel at a high speed through the gas generated by gunpowder, the high-temperature high-pressure gas extrudes strong brine in a water storage bin in a rear end cover, the strong brine flushes a sealing cover on a drain hole and is discharged from the drain hole of the water storage bin at a high speed, so that an exhaust groove sealing cover can be pushed, the exhaust groove is opened, the residual strong brine and the gas generated by the gunpowder are discharged, the rocket range-extending launching device has a cooling function, the forward-impacting gas impacts the front piston at a high speed, the front piston pushes the rear end of a projectile body, the projectile body moves forwards at a high speed, the front and back acting work are kept consistent, balance launching is realized, dust raising is reduced, glimmer, microsound and low temperature are realized, meanwhile, recoil force is relieved, and personnel injury is not easy to cause.

2. This rocket of no back seat increases journey emitter, when using, sends out the primer device through the electric shock, lights the inside black powder of biography fire pipe, and black powder burning lights the slip sheet of the inside of biography fire hole, and the outside propellant powder of biography fire pipe is lighted again through passing fire hole the same time to the flame that the slip sheet produced, can form high temperature, high-pressure gas in the twinkling of an eye after propellant powder lights simultaneously, has improved the initial velocity of muzzle greatly.

3. This no rocket of back seat increases journey emitter sets up the strong brine in the inside reservoir of rear end cap, can improve the density of moisture in the reservoir, further improves emitter's stability, has kept the fore-and-aft balancing power, can improve the shot quality that is used for balanced transmission, realizes remote transmission.

Drawings

FIG. 1 is a side isometric view of the present invention;

FIG. 2 is a front isometric view of the present invention;

FIG. 3 is a cutaway isometric view of the present invention;

FIG. 4 is an internal structural view of the present invention;

FIG. 5 is an isometric front view of the bottom panel of the storage bin of the present invention;

FIG. 6 is a front isometric view of the fire transmitting outer shield of the present invention;

FIG. 7 is an internal structural view of the fire transmitting outer protective cover of the present invention;

fig. 8 is a side isometric view of the front piston of the present invention.

In the figure: 1. a rear end cap; 2. a drain hole; 3. strong brine; 4. an exhaust groove; 5. an exhaust groove sealing cover; 6. a rear piston; 7. a gas transfer hole; 8. primer fire; 9. a flame transmitting tube; 10. a fire transfer hole; 11. launching the medicine; 12. black powder; 13. a front piston; 14. a rubber ring; 15. folding the empennage; 16. a rocket motor compartment section; 17. a control section; 18. folding the front wing; 19. a centering part; 20. a payload bay section; 21. a seeker; 22. lining paper; 23. a drain hole; 24. shearing the copper sheet; 25. shearing the bolt; 26. a portable harness; 27. launching a barrel; 28. a protective cover; 29. discharging from a blast hole; 30. a body of elastomer; 31. a water storage bin bottom plate; 32. fire-transmitting outer protective cover.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be obtained by a person skilled in the art without making any creative effort based on the embodiments in the present invention, belong to the protection scope of the present invention.

In order to solve the technical problems that the tail of the launching device is high in temperature and serious in recoil caused by the launching of the cannonball in the prior art, please refer to fig. 1 to 4, and the following technical scheme is provided:

the utility model provides a rocket of no back seat increases journey emitter, including transmission barrel 27 and body 30, body 30 is located the inside front end of transmission barrel 27, the rear end of transmission barrel 27 passes through flange fixedly connected with rear end cap 1, one side of rear end cap 1 is provided with the reservoir, and the inside of reservoir is provided with strong brine 3, the inside rear end of transmission barrel 27 is provided with passes fire outer safety cover 32, pass fire pipe 9 is installed to the inside centre of passing fire outer safety cover 32, the outside of passing fire pipe 9 is provided with the propellant powder chamber section, and the inside of propellant powder chamber section is provided with propellant powder 11, and the inside of passing fire pipe 9 is provided with black powder 12, and the surface of passing fire pipe 9 is provided with a plurality of ignition hole 10 that the staggered arrangement was arranged.

The rear end cover 1 is fixedly connected with the launching barrel 27 through bolts, a plurality of integrally formed drain holes 2 are formed in the outer portion of one side of the rear end cover 1 in a surrounding mode, two exhaust grooves 4 are formed in the outer portion of the middle of the rear end cover 1, the inner portions of the exhaust grooves 4 are connected with an exhaust groove sealing cover 5 in a sealing mode through sealing cushion layers, clamp springs are arranged on the inner side of the rear end cover 1, and the clamp springs are connected with one end of the rear end cover 1.

The outside one side of rear end cover 1 is provided with water storage storehouse bottom plate 31, and the inside of water storage storehouse bottom plate 31 link up has a plurality of integrated into one piece's outage 23, and the inner wall fixedly connected with of outage 23 cuts copper sheet 24, and outage 23 is used for extrudeing strong brine 3 and strikes exhaust duct 4.

Specifically, after the propellant 11 is ignited, the generated high-pressure gas can enable the inside of a propellant chamber section to have a backward movement force and a forward force, the gas generated by gunpowder moves at a high speed to the rear end of the propellant barrel 27, the high-temperature high-pressure gas extrudes the strong brine 3 in the water storage bin in the rear end cover 1, the strong brine 3 flushes the sealing cover on the drain hole 2, the strong brine is discharged outwards at a high speed from the drain hole 2 of the water storage bin, so that the sealing cover 5 of the exhaust groove can be pushed, the exhaust groove 4 is opened, the residual strong brine 3 and the gas generated by the gunpowder are discharged, the cooling function is realized, the forward-impacting gas impacts the rear end of the projectile body 30 at a high speed, the projectile body 30 moves forwards at a high speed, the front and the back do work consistently before and after the realization, the balanced propellant is realized, the flying dust is reduced, the shimmer, the microsound and the low temperature are realized, the recoil is not easy to cause the injury of personnel, and the tail part of the existing projectile can be seriously damaged by the projectile firing technology because the strong brine 3 is arranged in the water storage bin in the rear end cover 1.

In order to solve the technical problem of unstable internal structure of the device in the process of launching the cannonball in the prior art, please refer to fig. 3, fig. 4 and fig. 8, the following technical solutions are provided:

install the back piston 6 that is used for sealed water storage storehouse between rear end cap 1 and the transmission barrel 27, back piston 6 respectively with rear end cap 1 and transmission barrel 27 sliding connection, and be provided with between back piston 6 and the outer safety cover 32 of passing a fire and be used for adjusting atmospheric pressure pass gas hole 7, install the preceding piston 13 that is used for promoting projectile 30 between the outer safety cover 32 of passing a fire and the transmission barrel 27, preceding piston 13 respectively with pass a fire outer safety cover 32 and transmission barrel 27 sliding connection, the both ends outside of the outer safety cover 32 of passing a fire all is provided with shear bolt 25, shear bolt 25 is used for carrying out spacing work to back piston 6 and preceding piston 13.

Specifically, the gas generated by gunpowder pushes the rear piston 6 to move at a high speed towards the rear end of the launching barrel 27, the high-temperature high-pressure gas extrudes the strong brine 3 in a water storage bin in the rear end cover 1, the forward-impacting gas impacts the front piston 13 at a high speed, the front piston 13 pushes the rear end of the projectile body 30, the projectile body 30 moves forward at a high speed, the positions of the rear piston 6 and the front piston 13 are kept stable through the shearing bolt 25, and the gas keeps stable transverse movement through the rear piston 6 and the front piston 13 in the moving process, so that the projectile launching quality is improved.

In order to solve the technical problems that the initial speed of the cannonball is slow and the shooting range is affected when the cannonball is shot in the prior art, please refer to fig. 3-7, and the following technical scheme is provided:

one side in the middle of the outside of the rear piston 6 is provided with a primer 8 for outputting flame to ignite propellant powder 11, the primer 8 is provided with a device for electrically striking the primer 8, and the primer 8 is in tenon joint with the rear end of the inside of the fire transfer tube 9.

The inside of biography fire hole 10 is provided with a plurality of slip sheets 22 that are used for sealing work, and slip sheet 22 is used for igniting propellant powder 11, passes the outer surface of fire outer protective cover 32 and passes through draw-in groove and the rear end inner wall fixed connection of transmission barrel 27.

The rubber ring 14 is arranged outside the front piston 13, the front piston 13 is respectively connected with the launching barrel 27 and the fire transmission outer protection cover 32 in a sealing way through the rubber ring 14, and the rubber ring 14 is used for supporting the projectile body 30.

Specifically, the device for igniting primer 8 by electric shock ignites the black powder 12 inside the fire transfer tube 9, the black powder 12 burns to ignite the lining paper 22 inside the fire transfer hole 10, the flame generated by the lining paper 22 passes through the fire transfer hole 10 at the same time to ignite the propellant 11 outside the fire transfer tube 9 at the same time, and the propellant 11 can form high-temperature and high-pressure gas instantly after being ignited, so that the initial speed of the muzzle is greatly improved.

In order to solve the technical problems of the prior art that the projectile has a general launching effect and is inconvenient to carry, please refer to fig. 1-4, the following technical solutions are provided:

the projectile body 30 comprises a rocket engine cabin section 16, a control part cabin section 17 and a fighting part cabin section 20, the control part cabin section 17 is located on one side of the rocket engine cabin section 16, the fighting part cabin section 20 is located on one side of the control part cabin section 17, two folding tail wings 15 are arranged at the rear end of the outer portion of the rocket engine cabin section 16, the two folding tail wings 15 are movably connected with the rocket engine cabin section 16 through hinges, two folding front wings 18 are arranged on the outer portion of the control part cabin section 17, and the two folding front wings 18 are movably connected with the control part cabin section 17 through hinges.

The outside of the battle section cabin section 20 is provided with a centering part 19, the centering part 19 is used for limiting the launching barrel 27 and the outside of the battle section cabin section 20, the front end of the battle section cabin section 20 is provided with a guide head 21, the front end of the launching barrel 27 is connected with a protective cover 28 in a welding mode, and the protective cover 28 is internally provided with a blast outlet 29.

A portable strap 26 is arranged below the launching barrel 27, two ends of the portable strap 26 are fixedly connected with the front end and the rear end of the lower part of the launching barrel 27 through buckles respectively, and the portable strap 26 is used for bearing the whole launching barrel 27.

Specifically, when the portable missile is used, the projectile body 30 is kept limited integrally through the centering portion 19 outside the combat cabin section 20, the projectile body 30 can be launched through the projectile outlet 29 and then can be unfolded in the air to form the folding front wing 18 and the folding tail wing 15, the range is increased, the structure is simple, the portable carrying belt 26 is carried by a user to enable the portable missile to be portable, the portable missile is convenient to use, and the application range is wide.

To sum up, in the usage of the rocket range-extending launcher without backseat, an operator can carry the whole device by carrying the portable braces 26, when the projectile body 30 needs to be launched, the primer 8 device is triggered by electric shock, the black powder 12 in the fire transfer tube 9 is ignited, the black powder 12 is combusted, the lining paper 22 in the fire transfer hole 10 is ignited, the flame generated by the lining paper 22 passes through the fire transfer hole 10 at the same time and then ignites the propellant 11 outside the fire transfer tube 9 at the same time, the propellant 11 can instantly form high-temperature and high-pressure gas after being ignited, the initial speed of the muzzle is greatly improved, after the propellant 11 is ignited, the generated high-pressure gas can enable the inside of the propellant chamber section to have a backward movement force and a forward force, the gas generated by the propellant pushes the rear piston 6 to move to the rear end of the propellant body 27 at high speed, the high-temperature and high-pressure gas extrudes the strong brine 3 in the water storage bin in the rear end cover 1, the strong brine 3 washes away the sealing cover on the drain hole 2, and is discharged outwards at a high speed from the drain hole 2 of the water storage bin, so that the sealing cover 5 of the exhaust slot can be pushed, the exhaust slot 4 is opened, the gas generated by the residual strong brine 3 and gunpowder is discharged, and the cooling function is realized, the strong brine 3 is arranged in the water storage bin inside the rear end cover 1, the density of water in the water storage bin can be improved, the stability of the launching device is further improved, the front and rear balance force is maintained, the quality of shot used for balanced launching can be improved, the long-distance launching is realized, the forward-impacting gas impacts the front piston 13 at a high speed, the front piston 13 pushes the rear end of the projectile body 30, the projectile body 30 moves forwards at a high speed, the working is kept consistent before and after the launching is realized, the balanced launching is realized, the raised dust is reduced, the glimmer, the micro-sound and the low temperature are realized, meanwhile, the recoil force is lightened, and the injury of personnel is not easy to cause, the projectile body 30 is kept limited by the centering part 19 outside the warhead cabin section 20, and after being launched through the muzzle 29, the projectile body 30 can be unfolded in the air to form the folding front wing 18 and the folding tail wing 15, so that the range is increased.

It should be noted that, in this document, relational terms such as first and second, and the like are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.

Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.

Claims

1. A recoil-free rocket range-extending launching device comprising a launching barrel (27) and a projectile body (30), characterized in that: the projectile body (30) is located the inside front end of transmission barrel (27), flange fixedly connected with rear end cap (1) is passed through to the rear end of transmission barrel (27), one side of rear end cap (1) is provided with the water storage storehouse, and the inside in water storage storehouse is provided with strong brine (3), the inside rear end of transmission barrel (27) is provided with outer safety cover (32) of biography fire, pass fire pipe (9) are installed to the inside centre of outer safety cover (32) of biography fire, the outside of biography fire pipe (9) is provided with the transmission powder chamber section, and the inside of transmission powder chamber section is provided with propellant powder (11), just the inside of biography fire pipe (9) is provided with black powder (12), just the surface of biography fire pipe (9) is provided with biography fire hole (10) that a plurality of staggered arrangement arranged.

2. A recoilless rocket range extending launcher according to claim 1, wherein: the rear end cover (1) is fixedly connected with the launching barrel (27) through bolts, a plurality of integrally formed drain holes (2) are formed in the outer portion of one side of the rear end cover (1) in a surrounding mode, two exhaust grooves (4) are formed in the outer portion of the middle of the rear end cover (1), the inner portions of the exhaust grooves (4) are connected with exhaust groove sealing covers (5) in a sealing mode through sealing cushion layers, clamp springs are arranged on the inner side of the rear end cover (1), and the clamp springs are connected with one end of the rear end cover (1).

3. A recoilless rocket range extending launcher according to claim 2, wherein: install between rear end cap (1) and the transmission barrel (27) back piston (6) that are used for sealed water storage storehouse, back piston (6) respectively with rear end cap (1) and transmission barrel (27) sliding connection, just be provided with between back piston (6) and the outer safety cover of passing a fire (32) and be used for adjusting atmospheric pressure pass gas pocket (7), install between outer safety cover of passing a fire (32) and transmission barrel (27) preceding piston (13) that are used for promoting projectile (30), preceding piston (13) respectively with the outer safety cover of passing a fire (32) and transmission barrel (27) sliding connection, the both ends outside of the outer safety cover of passing a fire (32) all is provided with shear bolt (25), shear bolt (25) are used for carrying out spacing work to back piston (6) and preceding piston (13).

4. A recoilless rocket range extending launcher according to claim 3, wherein: one side in the middle of the outside of the rear piston (6) is provided with a primer (8) used for outputting flame to ignite propellant powder (11), the primer (8) is set as a device for sending the primer (8) by electric shock, and the primer (8) is connected with the rear end of the inside of the fire transmission tube (9) in a tenon mode.

5. A recoilless rocket range extending launcher according to claim 4, wherein: pass the inside of fire hole (10) and be provided with a plurality of slip sheet (22) that are used for sealing work, slip sheet (22) are used for igniting propellant powder (11), pass the outer surface of fire outer protective cover (32) and pass through the rear end inner wall fixed connection of draw-in groove and transmission barrel (27).

6. A recoilless rocket range extending launcher according to claim 5, wherein: the outside mounting of preceding piston (13) has rubber circle (14), preceding piston (13) respectively with launching barrel (27) and pass outer safety cover (32) sealing connection of fire through rubber circle (14), rubber circle (14) are used for bearing elastomer (30).

7. A recoilless rocket range extending launcher according to claim 6, wherein: the missile body (30) comprises a rocket engine cabin section (16), a control part cabin section (17) and a fighting part cabin section (20), the control part cabin section (17) is located on one side of the rocket engine cabin section (16), the fighting part cabin section (20) is located on one side of the control part cabin section (17), two folding tail wings (15) are arranged at the rear end of the outside of the rocket engine cabin section (16), the two folding tail wings (15) are movably connected with the rocket engine cabin section (16) through hinges, two folding front wings (18) are arranged on the outside of the control part cabin section (17), and the two folding front wings (18) are movably connected with the control part cabin section (17) through hinges.

8. A recoil-free rocket range-extending launching device according to claim 7, wherein: the outside of the battle section (20) is provided with a centering part (19), the centering part (19) is used for limiting the launching barrel (27) and the outside of the battle section (20), the front end of the battle section (20) is provided with a guide head (21), the front end of the launching barrel (27) is connected with a protective cover (28) in a welding mode, and a muzzle outlet (29) is formed in the protective cover (28).

9. A recoilless rocket range extending launcher according to claim 8, wherein: the novel exhaust hood is characterized in that a water storage bin bottom plate (31) is arranged on one side of the outer portion of the rear end cover (1), a plurality of integrally formed liquid discharge holes (23) are formed in the water storage bin bottom plate (31) in a penetrating mode, shear copper sheets (24) are fixedly connected to the inner wall of each liquid discharge hole (23), and the liquid discharge holes (23) are used for extruding strong brine (3) to impact the exhaust grooves (4).

10. A recoilless rocket range extending launcher according to claim 1, wherein: a portable strap (26) is arranged below the launching barrel (27), two ends of the portable strap (26) are fixedly connected with the front end and the rear end below the launching barrel (27) respectively through buckles, and the portable strap (26) is used for bearing the whole launching barrel (27).