CA1142782A - Device for launching of a projectile from a launching tube opened at its two ends - Google Patents
Device for launching of a projectile from a launching tube opened at its two endsInfo
- Publication number
- CA1142782A CA1142782A CA000362148A CA362148A CA1142782A CA 1142782 A CA1142782 A CA 1142782A CA 000362148 A CA000362148 A CA 000362148A CA 362148 A CA362148 A CA 362148A CA 1142782 A CA1142782 A CA 1142782A
- Authority
- CA
- Canada
- Prior art keywords
- rod
- projectile
- piston
- propelling charge
- launching
- 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.)
- Expired
Links
Classifications
-
- 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)
- Toys (AREA)
Abstract
IN THE CANADIAN PATENT AND TRADEMARK OFFICE
PATENT APPLICATION
entitled : Device for launching of a projectile from a launching tube opened at its two ends.
ABSTRACT OF THE DISCLOSURE
A device for launching of a projectile from a launching tube, comprising : a projectile extended at its rear end by an axial rod, a propelling charge behind the projectile, an inert mass behind the propelling charge, a piston which separates said charge from said mass and which can slide rearwardly along said rod, means for holding back said piston at the rear end of said rod, and means for aerodynamically stabilizing the projectile in flight with said rod and piston.
PATENT APPLICATION
entitled : Device for launching of a projectile from a launching tube opened at its two ends.
ABSTRACT OF THE DISCLOSURE
A device for launching of a projectile from a launching tube, comprising : a projectile extended at its rear end by an axial rod, a propelling charge behind the projectile, an inert mass behind the propelling charge, a piston which separates said charge from said mass and which can slide rearwardly along said rod, means for holding back said piston at the rear end of said rod, and means for aerodynamically stabilizing the projectile in flight with said rod and piston.
Description
The present invention relates to a firing device without backward gas ejection or recoil.
The invention relates more precisely to a device for launching of a projectile from a launching tube opened at its two ends without gas ejection towards the back and without substantial recoil, which device i~ of the type comprising a projectile, a propelling charge placed behind the said projectile, an inert mass situated behind the propelling charge and designed to be ejected at the rear end of the launching tube during firing, and a piston separating in tight manner the propelling charge from the inert mas3.
The invention finds a special and non-restrictive field of application in missile firing devices, for example anti-tank missile~.
~ ith a device of the type defined herein-above, the absence of recoil is due to the fact that the amount of movement of the projectile is balanced by that of the inert mass ejected at the rear end of the launching tube, the piston preventing any gas ejection towards the rear.
In known devices of this type, suoh as those described in French patent No~ 2 166 394 and French patent application No. 2 194 940, two pushing pistons are provided, one acting on the pro~ectile and the other acting on the inert mass, and are actuated by the same propelling charge or by two different charges. Means are then provided on the launching tube and, if necessary, on a container housing the whole assembly of projectile, propelling charge, inert mass and pistons, to hold the pistonq back inside the launching tube at firing time.
If the pistons holding back means are constituted by contractions (narrowings) of the launching tube, said latter can only be used once. When firing with an aiming member fitted on the launching tube, it is 'l ~
neces~ary to set the aiming member back into place after every firing. If the holding bacX means are formed inside a container in~erted into the launching tube, said container, which is relatively cumbersome, should be removed from the tube after each firing operation.
In an another known device described in the patent of the United States of America No. 4,012,987, two propelling charges as well as two pistons are prov-ided for the projectile and inert mass respectively. Thepropelling charge associated with the inert mass are placed in a separate housing which is ejected after the piston associated with the propellant charge for the projectile has ruptured a rearend stop in response to the continued ignition of said last propellant charge.
It is an object of the present invention to provide a devlce which is as simple as pos~ible and permits to fire a projectile with a minimum of operation and trouble for the firing crew, and in particular with the possibility of immediate re-utilization of the launching tube.
It i9 also an object of the invention to pro~ide a device which permits to fire a projectile without any recoil and without backward ejection other than that of the inert mass.
These objects are reached according to the invention by a device of the above-mentioned type and including a projectile which is ex-tended at its rear end by at least an axially directed rod, integral with the projectile and having an external diameter smaller than that of the projectile, a piston which separates said propelling charge from said inert mass and is in direct engagement therewith and which can slide rearwardly along said rod after firing of said propeilin~ charge; holding means provided at the rear free end of said rod for holding back said pi~ton on '7~32 said rod; and means for aerodynamically stabilizing said projectile in flight with said rod and piston.
The device according to the invention comprises a minimum of parts. In addition, the rod on which the piston is held back being fired with the projectile, the inert mass ejected at the rear is the only part of the device remaining on the spot~ After firing, the launching tube is therefore ready to be loaded once again. In particular, any aiming device provided can stay on the launching tube.
Preferably, the rod exends towards the rear as far as the end of the inert mass~
Advantageously, the means provided for holding back the piston on the rod are simply constituted by a swelling of the free end of the rod.
According to a first embodiment of the devi-ce according to the invention, the propelling charge, the piston and the inert maYs are arranged around the rod, the piston separating in tight manner the propelling charge from the inert mass inside the annular space situated between the outer surface of the rod and the inner surface of the launching tube when the device is loaded in the latter. The rod can then be solid or hollow, and the aerodynamically-stabilizing means may be Rimply constituted by said piston having a front face turned toward said projectile in the form of a calotte of a surface of revolution.
According to another embodiment of the device according to the invention, the rod is tubular, and the propelling charge, the inert mass and the piston separating the propelling charge from the inert mass are housed inside the said rod. The aerodynamically stabilizing means may be then constituted by a tail unit provided at the external surface of said free end of the rod.
~l~Z'71~2 The invention will be more readily under-stood onreading the following description with reference to the accompanying drawings, in which:
- Figures 1 and 2 show two embodiments of the device according to the invention, loaded in its launching tube.
~ igure 1 illustrates diagrammatically a launching tube 10 opened at both ends and inside which is loaded an assembly composed of, from back to front, a missile or projectile 11, a propelling charge 12, a piston 13 and an inert mas~ 14. The charge 12 and mass 14 are in direct engagement with the opposite faces of the piston 13.
The piston 13 separateq in tight manner the charge 12 from the mass 14 inside an annular space defined by the inner face of the tube 10 and the outer face of a hollow rod 15 co-axial with the tube 10 and extend-ing from the rear part of the projectile 11.
The projectile 11 proper is placed directly inside the tube 10 and is guided at its periphery by the inner face of the said tube 10. Likewise, the block of propelling charge 12, the piston 13 and the inert mass 14 are each inscribed inside the same cylindrical surface with circular cross-section of a diameter equal to the inner diameter of the launching tube.
The propelling charge 12 i9 placed immedia-tely behind the projectile 11 proper. It can be constituted for e~ample, in manner known per se, by a lump of gun powder provided with a firing systam (not shown).
The inert mass 14 is very divided and of low density so that, once it has been ejected from the rear of the tube, it can be stopped over a qhort distanceO Very thin strips of discs of paper or of plastic material can, for example, be used as 'Z~1~2 constituents of the charge 14.
The rod 15 extends as far as the rear end of the inert mass 1~. An external swelling is provided at the free end of the rod 15. Other mean~ can of cour~e be provided at that end of the rod to hold back the piston 13~
When the charge 12 is set on fire, the resulting ga~es speed the projectile 11 forward with the rod 15 which is integral therewith and towards the piston 13 which pushes the inert mass 14. The piston than slides on the rod 15 from ît~ initial position cloqe to the end of the rod adjacent the rear part of the projectile 11 proper a~ far a~ the rear end of the said rod 15 where the swelling 16 prevents it from e-~caping.
The amount of movement of the mass 14 balances that of the projectile 11 with its rod 15, hence the absence of recoil.
Moreover, the piston 13 ln sliding without play on the outer surface of the rod 15 and on the inner ~urface of the launching t~be 10 prevent~ a rearward ejection of ~a~es. At end o~ ~troke, the piston is ~lowed down and then ~topped by the swelling 16 re~ulting from a progressive increase of the external diameter of the rod 15.
Thetotality of the gase~ produced by the ignition of the charge and initially confined between the piston 13 and the projectile 11 are driven by the ~ald piston 13 towards the front of the tube 10 where-from they escape. In this way, all emanation of hot ga~es and detonating noises toward~ the rear are avoided, such effects being particularly annoyin~ for the gun crew e~pecially when the firing takes place from clo~ed quarters Df re~tricted volume.
After firing, the inert maRs 1~ being 11f~27~Z
ejected at the rear, and the hot gases being expelledat the front, the tube 10 is empty and ready to be used again.
On its course, the projectile 10 proper drives the piston 13 to the rear end of the rod 15 integral with the projectile 10. Advantageously, the piston is shaped so that it ~tabilizes aerodynamically the pn~ectile in flight. For example, the ~ront face 13a of the piston 13 turned towards the projectile 11 is a surface of revolution about the axis of the rod 15 which is ~haped as a calotte of a surface such as a paraboloid or ellipsoid, perforated for letting through the rod 15 and the top end of which faces forwardO
In the example described hereinabove, the pro~ectile 11 is extended axially towards the rear by only one hollow rod 15. Several hollow or solid rodY, axially oriented, can be provided as a variant.
Still as a variant, small orifices can be provided in the wall of the launching tube~ at the fore end thereof, in order to release the pressurized gases and avoid a detonation at firing time.
~igure 2 diagrammatically shows a 4econd embodiment of a device according to the invention loaded in the tube 10.
Said devices comprise, from the front towards the rear, as in the preceding case, a missile or projectile 21 guided directly by the`tube 10, a prop-ellins charge 22 placed directly behind the projectile 21 proper, a piston 23 and an inert mass 24. The charge 22 and the means 24 are in direct engagement with the opposite faces of the piston 23.
The pi~ton 23 separates in tight manner the charge 22 from the mass 24 inside a tubular rod 25 extending axially from the rear portion of the projectile 21 and integral therewith.
~.~4Z~8Z
Said tubular rod 25 haq a circular cros~-section with an outer diameter which is less than the inner diameter of the launching tube 10 and is thus housed inside the latter without being in contact with its wall. The projectile rod 25 is provided at its rear portions with fin~ or vanes 27 whichl at firing time, are guided by the inner surface of the launching tube and which, during the flight, form a tail unit stabilizing the projectileO
The inner mass 24 is entirely contained inside the projectile tube 25, for example as far as the rear end thereof. At that rear end, the projectile tube 25 i~ provided with an internal swelling 26 which results from a gradual narrowing of its inner diameter.
When the charge 22 i3 set on fire, the ga~es produced speed the projectile proper 21 forward, and the pi~ton 23 backward, ~aid piston pushing the inert mass 24. The piston 23 slides in~ide the projectile tube 25 without play from its initial po~ition close to the end of the projectile tube 25 which i9 adjacent the rear end of the projectile 21, as far as the rear end of the projectile tube 25 where the swelling a6 ~low~ it down and stops it.
As in the case of the embodiment described with reference to Figure 1, owing to the ejection of the inert mass there is no recoil effect and owing to the piston 23, there i~ no gas ejection toward~ the rear.
Moreover, the pi~ton 23 keeps the gases confined in the projectile tube 25, ~o that there are no gases ejected at the fore end of the launching tube either.
Due to the ab~ence of $ases, flames, smoke and dusts produced by the charge 22, the firing is extremely unconspicuous and is not awkward for the gun '- 'll~Z'~iZ
crew.
After firing, the launching tube 10 is empty and ready for immediate re-utilization. The projec-tile 21 in flight is aerodynamically stabilized by the tail unit 27 provided on the projectile rod 25 inside which the gases are confined by the piston 23.
The invention is not limited to the description given hereinabove, and various modifications may of course be made thereto witho~t departing from the scope and the spirit thereof.
The invention relates more precisely to a device for launching of a projectile from a launching tube opened at its two ends without gas ejection towards the back and without substantial recoil, which device i~ of the type comprising a projectile, a propelling charge placed behind the said projectile, an inert mass situated behind the propelling charge and designed to be ejected at the rear end of the launching tube during firing, and a piston separating in tight manner the propelling charge from the inert mas3.
The invention finds a special and non-restrictive field of application in missile firing devices, for example anti-tank missile~.
~ ith a device of the type defined herein-above, the absence of recoil is due to the fact that the amount of movement of the projectile is balanced by that of the inert mass ejected at the rear end of the launching tube, the piston preventing any gas ejection towards the rear.
In known devices of this type, suoh as those described in French patent No~ 2 166 394 and French patent application No. 2 194 940, two pushing pistons are provided, one acting on the pro~ectile and the other acting on the inert mass, and are actuated by the same propelling charge or by two different charges. Means are then provided on the launching tube and, if necessary, on a container housing the whole assembly of projectile, propelling charge, inert mass and pistons, to hold the pistonq back inside the launching tube at firing time.
If the pistons holding back means are constituted by contractions (narrowings) of the launching tube, said latter can only be used once. When firing with an aiming member fitted on the launching tube, it is 'l ~
neces~ary to set the aiming member back into place after every firing. If the holding bacX means are formed inside a container in~erted into the launching tube, said container, which is relatively cumbersome, should be removed from the tube after each firing operation.
In an another known device described in the patent of the United States of America No. 4,012,987, two propelling charges as well as two pistons are prov-ided for the projectile and inert mass respectively. Thepropelling charge associated with the inert mass are placed in a separate housing which is ejected after the piston associated with the propellant charge for the projectile has ruptured a rearend stop in response to the continued ignition of said last propellant charge.
It is an object of the present invention to provide a devlce which is as simple as pos~ible and permits to fire a projectile with a minimum of operation and trouble for the firing crew, and in particular with the possibility of immediate re-utilization of the launching tube.
It i9 also an object of the invention to pro~ide a device which permits to fire a projectile without any recoil and without backward ejection other than that of the inert mass.
These objects are reached according to the invention by a device of the above-mentioned type and including a projectile which is ex-tended at its rear end by at least an axially directed rod, integral with the projectile and having an external diameter smaller than that of the projectile, a piston which separates said propelling charge from said inert mass and is in direct engagement therewith and which can slide rearwardly along said rod after firing of said propeilin~ charge; holding means provided at the rear free end of said rod for holding back said pi~ton on '7~32 said rod; and means for aerodynamically stabilizing said projectile in flight with said rod and piston.
The device according to the invention comprises a minimum of parts. In addition, the rod on which the piston is held back being fired with the projectile, the inert mass ejected at the rear is the only part of the device remaining on the spot~ After firing, the launching tube is therefore ready to be loaded once again. In particular, any aiming device provided can stay on the launching tube.
Preferably, the rod exends towards the rear as far as the end of the inert mass~
Advantageously, the means provided for holding back the piston on the rod are simply constituted by a swelling of the free end of the rod.
According to a first embodiment of the devi-ce according to the invention, the propelling charge, the piston and the inert maYs are arranged around the rod, the piston separating in tight manner the propelling charge from the inert mass inside the annular space situated between the outer surface of the rod and the inner surface of the launching tube when the device is loaded in the latter. The rod can then be solid or hollow, and the aerodynamically-stabilizing means may be Rimply constituted by said piston having a front face turned toward said projectile in the form of a calotte of a surface of revolution.
According to another embodiment of the device according to the invention, the rod is tubular, and the propelling charge, the inert mass and the piston separating the propelling charge from the inert mass are housed inside the said rod. The aerodynamically stabilizing means may be then constituted by a tail unit provided at the external surface of said free end of the rod.
~l~Z'71~2 The invention will be more readily under-stood onreading the following description with reference to the accompanying drawings, in which:
- Figures 1 and 2 show two embodiments of the device according to the invention, loaded in its launching tube.
~ igure 1 illustrates diagrammatically a launching tube 10 opened at both ends and inside which is loaded an assembly composed of, from back to front, a missile or projectile 11, a propelling charge 12, a piston 13 and an inert mas~ 14. The charge 12 and mass 14 are in direct engagement with the opposite faces of the piston 13.
The piston 13 separateq in tight manner the charge 12 from the mass 14 inside an annular space defined by the inner face of the tube 10 and the outer face of a hollow rod 15 co-axial with the tube 10 and extend-ing from the rear part of the projectile 11.
The projectile 11 proper is placed directly inside the tube 10 and is guided at its periphery by the inner face of the said tube 10. Likewise, the block of propelling charge 12, the piston 13 and the inert mass 14 are each inscribed inside the same cylindrical surface with circular cross-section of a diameter equal to the inner diameter of the launching tube.
The propelling charge 12 i9 placed immedia-tely behind the projectile 11 proper. It can be constituted for e~ample, in manner known per se, by a lump of gun powder provided with a firing systam (not shown).
The inert mass 14 is very divided and of low density so that, once it has been ejected from the rear of the tube, it can be stopped over a qhort distanceO Very thin strips of discs of paper or of plastic material can, for example, be used as 'Z~1~2 constituents of the charge 14.
The rod 15 extends as far as the rear end of the inert mass 1~. An external swelling is provided at the free end of the rod 15. Other mean~ can of cour~e be provided at that end of the rod to hold back the piston 13~
When the charge 12 is set on fire, the resulting ga~es speed the projectile 11 forward with the rod 15 which is integral therewith and towards the piston 13 which pushes the inert mass 14. The piston than slides on the rod 15 from ît~ initial position cloqe to the end of the rod adjacent the rear part of the projectile 11 proper a~ far a~ the rear end of the said rod 15 where the swelling 16 prevents it from e-~caping.
The amount of movement of the mass 14 balances that of the projectile 11 with its rod 15, hence the absence of recoil.
Moreover, the piston 13 ln sliding without play on the outer surface of the rod 15 and on the inner ~urface of the launching t~be 10 prevent~ a rearward ejection of ~a~es. At end o~ ~troke, the piston is ~lowed down and then ~topped by the swelling 16 re~ulting from a progressive increase of the external diameter of the rod 15.
Thetotality of the gase~ produced by the ignition of the charge and initially confined between the piston 13 and the projectile 11 are driven by the ~ald piston 13 towards the front of the tube 10 where-from they escape. In this way, all emanation of hot ga~es and detonating noises toward~ the rear are avoided, such effects being particularly annoyin~ for the gun crew e~pecially when the firing takes place from clo~ed quarters Df re~tricted volume.
After firing, the inert maRs 1~ being 11f~27~Z
ejected at the rear, and the hot gases being expelledat the front, the tube 10 is empty and ready to be used again.
On its course, the projectile 10 proper drives the piston 13 to the rear end of the rod 15 integral with the projectile 10. Advantageously, the piston is shaped so that it ~tabilizes aerodynamically the pn~ectile in flight. For example, the ~ront face 13a of the piston 13 turned towards the projectile 11 is a surface of revolution about the axis of the rod 15 which is ~haped as a calotte of a surface such as a paraboloid or ellipsoid, perforated for letting through the rod 15 and the top end of which faces forwardO
In the example described hereinabove, the pro~ectile 11 is extended axially towards the rear by only one hollow rod 15. Several hollow or solid rodY, axially oriented, can be provided as a variant.
Still as a variant, small orifices can be provided in the wall of the launching tube~ at the fore end thereof, in order to release the pressurized gases and avoid a detonation at firing time.
~igure 2 diagrammatically shows a 4econd embodiment of a device according to the invention loaded in the tube 10.
Said devices comprise, from the front towards the rear, as in the preceding case, a missile or projectile 21 guided directly by the`tube 10, a prop-ellins charge 22 placed directly behind the projectile 21 proper, a piston 23 and an inert mass 24. The charge 22 and the means 24 are in direct engagement with the opposite faces of the piston 23.
The pi~ton 23 separates in tight manner the charge 22 from the mass 24 inside a tubular rod 25 extending axially from the rear portion of the projectile 21 and integral therewith.
~.~4Z~8Z
Said tubular rod 25 haq a circular cros~-section with an outer diameter which is less than the inner diameter of the launching tube 10 and is thus housed inside the latter without being in contact with its wall. The projectile rod 25 is provided at its rear portions with fin~ or vanes 27 whichl at firing time, are guided by the inner surface of the launching tube and which, during the flight, form a tail unit stabilizing the projectileO
The inner mass 24 is entirely contained inside the projectile tube 25, for example as far as the rear end thereof. At that rear end, the projectile tube 25 i~ provided with an internal swelling 26 which results from a gradual narrowing of its inner diameter.
When the charge 22 i3 set on fire, the ga~es produced speed the projectile proper 21 forward, and the pi~ton 23 backward, ~aid piston pushing the inert mass 24. The piston 23 slides in~ide the projectile tube 25 without play from its initial po~ition close to the end of the projectile tube 25 which i9 adjacent the rear end of the projectile 21, as far as the rear end of the projectile tube 25 where the swelling a6 ~low~ it down and stops it.
As in the case of the embodiment described with reference to Figure 1, owing to the ejection of the inert mass there is no recoil effect and owing to the piston 23, there i~ no gas ejection toward~ the rear.
Moreover, the pi~ton 23 keeps the gases confined in the projectile tube 25, ~o that there are no gases ejected at the fore end of the launching tube either.
Due to the ab~ence of $ases, flames, smoke and dusts produced by the charge 22, the firing is extremely unconspicuous and is not awkward for the gun '- 'll~Z'~iZ
crew.
After firing, the launching tube 10 is empty and ready for immediate re-utilization. The projec-tile 21 in flight is aerodynamically stabilized by the tail unit 27 provided on the projectile rod 25 inside which the gases are confined by the piston 23.
The invention is not limited to the description given hereinabove, and various modifications may of course be made thereto witho~t departing from the scope and the spirit thereof.
Claims (8)
1. A device for launching of a projectile from a launching tube opened at its two ends, said device comprising:
- a projectile extended at its rear end by at least one axially directed rod, integral with the projectile and having an external diameter smaller than than of the projectile;
- a propelling charge placed behind said projectile;
- an inert mass situated behind said propelling charge and designed to be ejected at the rear end of said launching tube, after firing of said propelling charge, in order to control recoil of said launching tube;
- a piston which separates said propelling charge from said inert mass and is in direct engagement there-with and which can slide rearwardly along said rod after firing of said propelling charge;
- holding means provided at the rear free end of said rod for holding back said piston on said rod; and - means for aerodynamically stabilizing said projectile in flight with said rod and piston.
- a projectile extended at its rear end by at least one axially directed rod, integral with the projectile and having an external diameter smaller than than of the projectile;
- a propelling charge placed behind said projectile;
- an inert mass situated behind said propelling charge and designed to be ejected at the rear end of said launching tube, after firing of said propelling charge, in order to control recoil of said launching tube;
- a piston which separates said propelling charge from said inert mass and is in direct engagement there-with and which can slide rearwardly along said rod after firing of said propelling charge;
- holding means provided at the rear free end of said rod for holding back said piston on said rod; and - means for aerodynamically stabilizing said projectile in flight with said rod and piston.
2. A device as claimed in claim 1, wherein said rod extends rearwardly at least as far as the rear end of said inert mass.
3. A device as claimed in claim 1, wherein said piston holding back means are constituted by a swelling of said free end of the rod.
4. A device as claimed in claim 1, wherein said propelling charge, said piston and said inert mass are arranged around said rod said piston being arranged for separating in tight manner the propelling charge from the inner mass in the annular space between the outer surface of the rod and the inner surface of said launching tube when said device is loaded in said launching tube.
5. A device as claimed in claim 4, wherein said rod is hollow.
6. A device as claimed in claim 4, wherein said aerodynamically stabilizing means are constituted by said piston having a front face turned toward said projectile in the form of a calotte of a surface of revolution.
7. A device as claimed in claim 1, wherein said rod is tubular; and said propelling charge, said piston and said inert mass are housed inside said rod with said piston separating in tight manner the propell-ing charge from the inert mass.
8. A device as claimed in claim 7, wherein said aerodynamically stabilizing means are constituted by a tail unit provided at the external surface of said free end of the rod.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR7925232 | 1979-10-10 | ||
| FR7925232A FR2467380B1 (en) | 1979-10-10 | 1979-10-10 | DEVICE FOR SHOOTING WITHOUT EJECTING GAS TO THE REAR, OR BACK-UP |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA1142782A true CA1142782A (en) | 1983-03-15 |
Family
ID=9230542
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA000362148A Expired CA1142782A (en) | 1979-10-10 | 1980-10-10 | Device for launching of a projectile from a launching tube opened at its two ends |
Country Status (5)
| Country | Link |
|---|---|
| EP (1) | EP0027418B1 (en) |
| CA (1) | CA1142782A (en) |
| DE (1) | DE3070323D1 (en) |
| ES (1) | ES8105859A1 (en) |
| FR (1) | FR2467380B1 (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2558946B1 (en) * | 1984-01-27 | 1988-04-08 | Brandt Armements | LAUNCHING TUBE FOR RECOVERY SHOOTING WEAPON |
| FR2602040B1 (en) * | 1986-07-23 | 1988-11-10 | Serat | IMPROVEMENTS IN OR RELATING TO PROJECTILES WITHOUT RECOIL ARMS OR LAUNCHING SYSTEMS |
| CN110160396A (en) * | 2019-05-15 | 2019-08-23 | 南京理工大学 | A kind of fire extinguishing bullet launching device and method based on classification coyote hole |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR597391A (en) * | 1924-04-29 | 1925-11-19 | Device and part for non-reactive firing | |
| DE1012849B (en) * | 1955-05-20 | 1957-07-25 | Ludger Volpert | Self-propelled projectile |
| FR1326176A (en) * | 1961-07-20 | 1963-05-03 | Energa | Projectile |
| CH493818A (en) * | 1968-03-07 | 1970-07-15 | Oerlikon Buehrle Ag | Projectile with a hollow explosive charge |
| US4012987A (en) * | 1975-09-03 | 1977-03-22 | The United States Of America As Represented By The Secretary Of The Army | Dual combustion missile system |
| DE2553201C2 (en) * | 1975-11-27 | 1984-05-10 | Rheinmetall GmbH, 4000 Düsseldorf | Recoil-free and bang-free projectile |
-
1979
- 1979-10-10 FR FR7925232A patent/FR2467380B1/en not_active Expired
-
1980
- 1980-10-08 ES ES495746A patent/ES8105859A1/en not_active Expired
- 1980-10-09 DE DE8080401451T patent/DE3070323D1/en not_active Expired
- 1980-10-09 EP EP19800401451 patent/EP0027418B1/en not_active Expired
- 1980-10-10 CA CA000362148A patent/CA1142782A/en not_active Expired
Also Published As
| Publication number | Publication date |
|---|---|
| ES495746A0 (en) | 1981-06-16 |
| EP0027418B1 (en) | 1985-03-20 |
| DE3070323D1 (en) | 1985-04-25 |
| FR2467380B1 (en) | 1986-04-18 |
| EP0027418A1 (en) | 1981-04-22 |
| FR2467380A1 (en) | 1981-04-17 |
| ES8105859A1 (en) | 1981-06-16 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| MKEX | Expiry |