CA2423022A1 - System and method for low signature launch of projectile - Google Patents
System and method for low signature launch of projectile Download PDFInfo
- Publication number
- CA2423022A1 CA2423022A1 CA002423022A CA2423022A CA2423022A1 CA 2423022 A1 CA2423022 A1 CA 2423022A1 CA 002423022 A CA002423022 A CA 002423022A CA 2423022 A CA2423022 A CA 2423022A CA 2423022 A1 CA2423022 A1 CA 2423022A1
- Authority
- CA
- Canada
- Prior art keywords
- projectile
- plates
- launch
- launching
- tube
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Abandoned
Links
- 238000000034 method Methods 0.000 title claims abstract description 4
- 230000008878 coupling Effects 0.000 abstract 1
- 238000010168 coupling process Methods 0.000 abstract 1
- 238000005859 coupling reaction Methods 0.000 abstract 1
- 238000010304 firing Methods 0.000 description 8
- 239000003380 propellant Substances 0.000 description 8
- 239000007789 gas Substances 0.000 description 5
- NIOPZPCMRQGZCE-WEVVVXLNSA-N 2,4-dinitro-6-(octan-2-yl)phenyl (E)-but-2-enoate Chemical compound CCCCCCC(C)C1=CC([N+]([O-])=O)=CC([N+]([O-])=O)=C1OC(=O)\C=C\C NIOPZPCMRQGZCE-WEVVVXLNSA-N 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 230000009969 flowable effect Effects 0.000 description 3
- 230000003287 optical effect Effects 0.000 description 3
- 229920000271 Kevlar® Polymers 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 2
- 239000004020 conductor Substances 0.000 description 2
- 239000006185 dispersion Substances 0.000 description 2
- 239000000835 fiber Substances 0.000 description 2
- 239000011810 insulating material Substances 0.000 description 2
- 239000004761 kevlar Substances 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 239000010959 steel Substances 0.000 description 2
- 230000002411 adverse Effects 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F3/00—Rocket or torpedo launchers
- F41F3/04—Rocket or torpedo launchers for rockets
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41A—FUNCTIONAL FEATURES OR DETAILS COMMON TO BOTH SMALLARMS AND ORDNANCE, e.g. CANNONS; MOUNTINGS FOR SMALLARMS OR ORDNANCE
- F41A1/00—Missile propulsion characterised by the use of explosive or combustible propellant charges
- F41A1/08—Recoilless guns, i.e. guns having propulsion means producing no recoil
- F41A1/10—Recoilless guns, i.e. guns having propulsion means producing no recoil a counter projectile being used to balance recoil
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
- Waveguides (AREA)
- Actuator (AREA)
- Fluid-Damping Devices (AREA)
- Toys (AREA)
Abstract
A method and a device for the launching of a projectile is disclosed. A front and aft plate are coupled to an expansion vessel having an axis so that when the volume of the expansion vessel increases the pistons move in opposing directions along the axis. A projectile is so disposed that it is launched in a desired direction by the motion of the front plate. The motion of the plates along the axis is limited in that the two plates are connected to each other by an extendible coupling structure.
Description
System and method for low si ature launch of rp---jectile Background of the invention:
In many tactical situations, and in particular in urban Warfare, there is great importance in reducing the signatures associated with launching a projectile.
When launching a projectile from a tube with a rocket motor, the exhaust gases create a high-pressure area and significant acoustical and optical signature is observable.
These effects preclude firing from enclosures and makes the gunner easily detectable.
In order to reduce such unwelcome effects, closed launched systems have been designed, which confine the gaseous products of propellant combustion between two pistons moving in opposite directions in the launch tube. Schnabele et al. in US Pat.
3.771,417 and Schnabele in US Patent 3,779,130 present a design of a launching system for firing projectiles which has since been known as the double "trapped piston" design. One of the piston pushes and accelerates the projectile in the launch direction, while the other piston pushes a counter-mass until it is ejected in the backward direction. The pistons move until they run into mechanical stops at the forward and backward end of the launch tube. Even if the weights on both sides of the propelling charge are carefully matched, there might be some mismatch in the timing of the two pistons running into the stops, resulting in possible recoil effects that might adversely affect accuracy and gunner safety.
In addition, since at the end of the stroke momentum is transferred from the pistons to the tube, the tube has to be stn~cturally designed to withstand the impulsive tensile forces, a requirement that undoubtedly contributes to the tube weight.
Alternatively, it might be necessary to incorporate into the design a deforming braking device such as taught in US Patent 4,148,244 by Schnabele at al. Such a device adds to the complexity of the design and to its weight.
The current invention presents solutions for containing the high-pressure gaseous products of propellant combustion without axially loading the launch tube and without generating recoil forces.
Summary of the invention According to the current invention, a projectile is launched from the tube after being pushed by a plate, which might serve as a piston, while another plate, which might serve as a piston, pushes a counter-mass until it is ejected in the backward direction. The counter-mass consists of a flowable medium of relatively high density.
The two plates are interconnected and the structure connecting the two end-plates arrests them as soon as the distance between them reaches a pre-designed value. In one embodiment, the interconnecting structure is a sealed bellow that contains the gases between the two end-plates, without at all exposing the launch tube to the high pressure. In another embodiment, the interconnecting structure is a multitude of ropes, the gases being contained between the launch tube, serving as a pressure-vessel and the end-plates, serving as pistons.
Description of the Fi ures Fig. I a shows a launching system according to a first embodiment of the invention prior to launching the projectile.
Fig. 1b shows a launching system according to a first embodiment of the invention after launching the projectile.
Fig. 2a shows a Launching system according to a second embodiment of the invention prior to launching the projectile.
Fig. 2b shows a launching system according to a second embodiment of the invention after launching the projectile.
Detailed description of preferred embodiments of the inyention.
Figure 1 shows a first embodiment of the invention. The launching system consists of a, preferably, throw-away launch tube 1 with removable covers 2,3 on both ends. An optical sight 4 and a firing mechanism 5 are attached to launch tube 1. The output of the firing mechanism (electric or pyrotechnic) is transferred through an electric conductor or a pyrotechnic cable (such as a Nonel-type pyrotechnic cord) 6 to the propellant ignition system 7. A propelling charge 8 is enclosed between two end-plates, 9,10, serving as pistons.
The projectile 11 is located ahead of the front end-plate 9 and the counter-mass 12 which may, for example, be a flowable medium of relatively high density, is located behind the aft end-plate 10. The two end-plate 9,10 are interconnected by an open connecting structure 13 consisting of several ropes or cables made of high-tensile strength material such as high-stxength steel or high-strength fibers such as Kevlar or a combination thereof. If non-metallic, the ropes or cables might be coated with an insulating material such as rubber.
When the gunner activates the firing mechanism 5, a signal is transferred through to the propellant ignition system 7. The propellant charge 8 is ignited and burns, generating high temperature, high pressure gases. The pressure generated within the launch tube 1 and between the end-plates, serving as pistons 9, 10, impinges on the pistons. The projectile I 1 is pushed forward by end-plate 9 and subsequently ejected from tube 1.
The counter-mass 12 is pushed backwards by end-plate 10 and is dispersed when leaving tube 1.
The structure 13 connecting the two end-plates arrests them as soon as the distance between them reaches a pre-designed value as determined by the extended length of the ropes. The ropes or cables might be of equal length or slightly different lengths and might vary in thickness as well. Accordingly, the arresting of the pistons can be spread over a certain time interval and not conducted abruptly.
In order to facilitate the dispersion of the counter-mass and in order to gradually release the pressure between the end-plates once the projectile has been launched, several openings 14 such as holes or blow-out ports might be provided in the pistons.
Figure 2 shows a second embodiment of the invention. The elements which are in common with the embodiment of Figure 1 are not shown, or numbered.
Reference is made herein to Figure 1 where appropriate. The launching system consists of a, throw-away Launch tube 1 with removable covers 2,3 on both ends. An optical sight 4 and a firing mechanism 5 axe attached to the launch tube 1.
The output of the firing mechanism (electric or pyrotechnic) is transferred through an electric conductor or a pyrotechnic cable (such as a Nonel-type pyrotechnic cord) 6 to the propellant ignition system 7.
A propelling charge 8 is enclosed between two end-plates 9,10 which are connected by bellows 23. The two end-plates 9,10 together with the bellows 23 connecting them form a closed structure which serves as a pressure vessel. The bellows are made, for example, of high-tensile strength material such as high-strength steel or fabric reinforced with high-strength fibers such as Kevlar or a combination thereof. If non-metallic, the bellows might be coated with an insulating material such as rubber. It should be noted that according to this second embodiment, the launch tube I is- not pressurized, a feature that enables a reduced-weight design.
The end-plates 9,I0 do not serve in this case as pistons and no sealing is required between them and the launch tube I .
The projectile I1 is located ahead of the front end-plate 9 and the counter-mass 12 which consists of a flowable medium of relatively high density is located behind the aft end-plate 10. When the gunner activates the firing mechanism 5, a signal is transferred through to the propellant ignition system 7. The propellant charge 8 is ignited and burns generating high temperature, high pressure gases. The pressure generated within the bellows 23. and between the end-plates 9, 10 impinges on the end-plates. The projectile II. is pushed forward by end-plate 9 and subsequently ejected from the tube. The counter-mass 12 is pushed backwards by end-plate 10 and is dispersed when leaving the tube.
The bellows 23 connecting the two end-plates arrests them as soon as the distance between them reaches a pre-designed value as determined by the extended length of the bellows 23. It would be possible to connect the endplates with some high-strength ropes in addition to the bellows connection. Accordingly, the arresting of the end-plates can be spread over a certain time interval and not conducted abruptly.
In order to facilitate the dispersion of the counter-mass and in order to gradually release the pressure between the end-plates once the projectile has been launched, several openings 14 such as holes or blow-out ports might be provided in the pistons.
In many tactical situations, and in particular in urban Warfare, there is great importance in reducing the signatures associated with launching a projectile.
When launching a projectile from a tube with a rocket motor, the exhaust gases create a high-pressure area and significant acoustical and optical signature is observable.
These effects preclude firing from enclosures and makes the gunner easily detectable.
In order to reduce such unwelcome effects, closed launched systems have been designed, which confine the gaseous products of propellant combustion between two pistons moving in opposite directions in the launch tube. Schnabele et al. in US Pat.
3.771,417 and Schnabele in US Patent 3,779,130 present a design of a launching system for firing projectiles which has since been known as the double "trapped piston" design. One of the piston pushes and accelerates the projectile in the launch direction, while the other piston pushes a counter-mass until it is ejected in the backward direction. The pistons move until they run into mechanical stops at the forward and backward end of the launch tube. Even if the weights on both sides of the propelling charge are carefully matched, there might be some mismatch in the timing of the two pistons running into the stops, resulting in possible recoil effects that might adversely affect accuracy and gunner safety.
In addition, since at the end of the stroke momentum is transferred from the pistons to the tube, the tube has to be stn~cturally designed to withstand the impulsive tensile forces, a requirement that undoubtedly contributes to the tube weight.
Alternatively, it might be necessary to incorporate into the design a deforming braking device such as taught in US Patent 4,148,244 by Schnabele at al. Such a device adds to the complexity of the design and to its weight.
The current invention presents solutions for containing the high-pressure gaseous products of propellant combustion without axially loading the launch tube and without generating recoil forces.
Summary of the invention According to the current invention, a projectile is launched from the tube after being pushed by a plate, which might serve as a piston, while another plate, which might serve as a piston, pushes a counter-mass until it is ejected in the backward direction. The counter-mass consists of a flowable medium of relatively high density.
The two plates are interconnected and the structure connecting the two end-plates arrests them as soon as the distance between them reaches a pre-designed value. In one embodiment, the interconnecting structure is a sealed bellow that contains the gases between the two end-plates, without at all exposing the launch tube to the high pressure. In another embodiment, the interconnecting structure is a multitude of ropes, the gases being contained between the launch tube, serving as a pressure-vessel and the end-plates, serving as pistons.
Description of the Fi ures Fig. I a shows a launching system according to a first embodiment of the invention prior to launching the projectile.
Fig. 1b shows a launching system according to a first embodiment of the invention after launching the projectile.
Fig. 2a shows a Launching system according to a second embodiment of the invention prior to launching the projectile.
Fig. 2b shows a launching system according to a second embodiment of the invention after launching the projectile.
Detailed description of preferred embodiments of the inyention.
Figure 1 shows a first embodiment of the invention. The launching system consists of a, preferably, throw-away launch tube 1 with removable covers 2,3 on both ends. An optical sight 4 and a firing mechanism 5 are attached to launch tube 1. The output of the firing mechanism (electric or pyrotechnic) is transferred through an electric conductor or a pyrotechnic cable (such as a Nonel-type pyrotechnic cord) 6 to the propellant ignition system 7. A propelling charge 8 is enclosed between two end-plates, 9,10, serving as pistons.
The projectile 11 is located ahead of the front end-plate 9 and the counter-mass 12 which may, for example, be a flowable medium of relatively high density, is located behind the aft end-plate 10. The two end-plate 9,10 are interconnected by an open connecting structure 13 consisting of several ropes or cables made of high-tensile strength material such as high-stxength steel or high-strength fibers such as Kevlar or a combination thereof. If non-metallic, the ropes or cables might be coated with an insulating material such as rubber.
When the gunner activates the firing mechanism 5, a signal is transferred through to the propellant ignition system 7. The propellant charge 8 is ignited and burns, generating high temperature, high pressure gases. The pressure generated within the launch tube 1 and between the end-plates, serving as pistons 9, 10, impinges on the pistons. The projectile I 1 is pushed forward by end-plate 9 and subsequently ejected from tube 1.
The counter-mass 12 is pushed backwards by end-plate 10 and is dispersed when leaving tube 1.
The structure 13 connecting the two end-plates arrests them as soon as the distance between them reaches a pre-designed value as determined by the extended length of the ropes. The ropes or cables might be of equal length or slightly different lengths and might vary in thickness as well. Accordingly, the arresting of the pistons can be spread over a certain time interval and not conducted abruptly.
In order to facilitate the dispersion of the counter-mass and in order to gradually release the pressure between the end-plates once the projectile has been launched, several openings 14 such as holes or blow-out ports might be provided in the pistons.
Figure 2 shows a second embodiment of the invention. The elements which are in common with the embodiment of Figure 1 are not shown, or numbered.
Reference is made herein to Figure 1 where appropriate. The launching system consists of a, throw-away Launch tube 1 with removable covers 2,3 on both ends. An optical sight 4 and a firing mechanism 5 axe attached to the launch tube 1.
The output of the firing mechanism (electric or pyrotechnic) is transferred through an electric conductor or a pyrotechnic cable (such as a Nonel-type pyrotechnic cord) 6 to the propellant ignition system 7.
A propelling charge 8 is enclosed between two end-plates 9,10 which are connected by bellows 23. The two end-plates 9,10 together with the bellows 23 connecting them form a closed structure which serves as a pressure vessel. The bellows are made, for example, of high-tensile strength material such as high-strength steel or fabric reinforced with high-strength fibers such as Kevlar or a combination thereof. If non-metallic, the bellows might be coated with an insulating material such as rubber. It should be noted that according to this second embodiment, the launch tube I is- not pressurized, a feature that enables a reduced-weight design.
The end-plates 9,I0 do not serve in this case as pistons and no sealing is required between them and the launch tube I .
The projectile I1 is located ahead of the front end-plate 9 and the counter-mass 12 which consists of a flowable medium of relatively high density is located behind the aft end-plate 10. When the gunner activates the firing mechanism 5, a signal is transferred through to the propellant ignition system 7. The propellant charge 8 is ignited and burns generating high temperature, high pressure gases. The pressure generated within the bellows 23. and between the end-plates 9, 10 impinges on the end-plates. The projectile II. is pushed forward by end-plate 9 and subsequently ejected from the tube. The counter-mass 12 is pushed backwards by end-plate 10 and is dispersed when leaving the tube.
The bellows 23 connecting the two end-plates arrests them as soon as the distance between them reaches a pre-designed value as determined by the extended length of the bellows 23. It would be possible to connect the endplates with some high-strength ropes in addition to the bellows connection. Accordingly, the arresting of the end-plates can be spread over a certain time interval and not conducted abruptly.
In order to facilitate the dispersion of the counter-mass and in order to gradually release the pressure between the end-plates once the projectile has been launched, several openings 14 such as holes or blow-out ports might be provided in the pistons.
Claims
Claims:
One or more aspects of system and method for low signature launch of projectile substantially as described herein.
One or more aspects of system and method for low signature launch of projectile substantially as described herein.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| IL148919 | 2002-03-26 | ||
| IL14891902A IL148919A0 (en) | 2002-03-26 | 2002-03-26 | System and method for low signature launch of projectile |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA2423022A1 true CA2423022A1 (en) | 2003-09-26 |
Family
ID=27799859
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA002423022A Abandoned CA2423022A1 (en) | 2002-03-26 | 2003-03-21 | System and method for low signature launch of projectile |
Country Status (9)
| Country | Link |
|---|---|
| US (1) | US20040020350A1 (en) |
| EP (1) | EP1348925A1 (en) |
| KR (1) | KR20030077415A (en) |
| CN (1) | CN1447091A (en) |
| AU (1) | AU2003202429A1 (en) |
| BR (1) | BR0300750A (en) |
| CA (1) | CA2423022A1 (en) |
| IL (1) | IL148919A0 (en) |
| PL (1) | PL359325A1 (en) |
Families Citing this family (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7246613B1 (en) * | 2004-08-19 | 2007-07-24 | Mohar Robert C | Vehicle interdiction device and method |
| FR2887021B1 (en) * | 2005-06-14 | 2007-08-31 | Tda Armements Sas Soc Par Acti | PENETRATING AID KIT COMPRISING A BOMB, IN PARTICULAR ANTI-INFRASTRUCTURE, PENETRANT PROJECTILE EQUIPPED WITH SUCH A KIT, AND METHOD OF PENETRATION IN A TARGET |
| CN101240992B (en) * | 2008-02-15 | 2010-09-29 | 陈延文 | Fixed range pressure-dividing controllable fireworks burning device and its method |
| CN101240993B (en) * | 2008-02-15 | 2010-09-29 | 陈延文 | Fireworks burning launcher pressure-dividing device |
| CN101226044B (en) * | 2008-02-20 | 2011-05-18 | 陈延文 | Firing range control method and device thereof |
| KR101036941B1 (en) * | 2010-04-29 | 2011-05-25 | 주식회사 엠에스테크 | A flood-gate |
| CN102442526A (en) * | 2010-10-12 | 2012-05-09 | 杨礼诚 | Potential energy transporting system |
| RU201079U1 (en) * | 2020-04-28 | 2020-11-26 | Илья Григорьевич Вишняков | Disposable grenade launcher |
| CN114323729B (en) * | 2021-11-18 | 2024-05-28 | 北京卫星制造厂有限公司 | Sampling device |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2001758C3 (en) | 1970-01-16 | 1974-03-21 | Messerschmitt-Boelkow-Blohm Gmbh, 8000 Muenchen | Launching device for projectiles for anti-tank fighting |
| DE2055805C3 (en) * | 1970-11-13 | 1974-03-28 | Messerschmitt-Boelkow-Blohm Gmbh, 8000 Muenchen | Launching device for projectiles |
| DE2140875A1 (en) | 1971-08-14 | 1973-02-22 | Messerschmitt Boelkow Blohm | DEVICE FOR RECOIL-FREE AND SNAP-FREE SHOOTING OF BULLETS |
| DE2651167C3 (en) | 1976-11-10 | 1981-10-22 | Messerschmitt-Bölkow-Blohm GmbH, 8000 München | Arrangement for braking free pistons driven in a tube with great acceleration |
| FR2470358A1 (en) * | 1979-11-22 | 1981-05-29 | Serat | IMPROVEMENTS ON WEAPONS LAUNCHING PROJECTILES |
| DE3048598A1 (en) * | 1980-12-23 | 1982-07-29 | Dynamit Nobel Ag, 5210 Troisdorf | Recoil-less firearm with open barrel - has intermediate plungers halted by connecting rope before reaching barrel mouths |
| FR2534681B1 (en) * | 1982-10-19 | 1987-08-07 | Serat | IMPROVEMENTS IN PROJECTILE LAUNCHING WEAPON SYSTEMS, IN PARTICULAR FOR PROPELLANT LOADS AND INNER BALLISTICS |
-
2002
- 2002-03-26 IL IL14891902A patent/IL148919A0/en unknown
-
2003
- 2003-03-19 US US10/390,755 patent/US20040020350A1/en not_active Abandoned
- 2003-03-21 CA CA002423022A patent/CA2423022A1/en not_active Abandoned
- 2003-03-24 AU AU2003202429A patent/AU2003202429A1/en not_active Abandoned
- 2003-03-25 BR BR0300750-2A patent/BR0300750A/en not_active IP Right Cessation
- 2003-03-25 KR KR10-2003-0018371A patent/KR20030077415A/en not_active Application Discontinuation
- 2003-03-25 PL PL03359325A patent/PL359325A1/en not_active IP Right Cessation
- 2003-03-25 EP EP03251870A patent/EP1348925A1/en not_active Withdrawn
- 2003-03-26 CN CN03121372A patent/CN1447091A/en active Pending
Also Published As
| Publication number | Publication date |
|---|---|
| US20040020350A1 (en) | 2004-02-05 |
| AU2003202429A1 (en) | 2003-10-16 |
| IL148919A0 (en) | 2003-07-31 |
| CN1447091A (en) | 2003-10-08 |
| BR0300750A (en) | 2004-09-08 |
| KR20030077415A (en) | 2003-10-01 |
| EP1348925A1 (en) | 2003-10-01 |
| PL359325A1 (en) | 2003-10-06 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| FZDE | Discontinued |