EP0027418B1 - Vorrichtung zum Abfeuern eines Geschosses ohne rückwärtige Gasabfuhr und ohne Rückstoss mittels eines beidseitig offenen Abschussrohres - Google Patents

Vorrichtung zum Abfeuern eines Geschosses ohne rückwärtige Gasabfuhr und ohne Rückstoss mittels eines beidseitig offenen Abschussrohres Download PDF

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Publication number
EP0027418B1
EP0027418B1 EP19800401451 EP80401451A EP0027418B1 EP 0027418 B1 EP0027418 B1 EP 0027418B1 EP 19800401451 EP19800401451 EP 19800401451 EP 80401451 A EP80401451 A EP 80401451A EP 0027418 B1 EP0027418 B1 EP 0027418B1
Authority
EP
European Patent Office
Prior art keywords
projectile
piston
rod
inert mass
propelling charge
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
Application number
EP19800401451
Other languages
English (en)
French (fr)
Other versions
EP0027418A1 (de
Inventor
Christian Goulpeau
Jean Poisson
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Societe Europeenne de Propulsion SEP SA
Original Assignee
Societe Europeenne de Propulsion SEP SA
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Societe Europeenne de Propulsion SEP SA filed Critical Societe Europeenne de Propulsion SEP SA
Publication of EP0027418A1 publication Critical patent/EP0027418A1/de
Application granted granted Critical
Publication of EP0027418B1 publication Critical patent/EP0027418B1/de
Expired legal-status Critical Current

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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

Definitions

  • the present invention relates to a device for allowing the firing of a projectile without ejection of gas towards the rear, nor recoil, by means of a launching tube open at its two ends.
  • the subject of the invention is a device of the type comprising a projectile, a propellant charge placed behind the projectile, an inert mass located behind the propellant charge and intended to be ejected from the rear of the launch tube during firing. , and a piston sealingly separating the propellant charge from the inert mass and capable of sliding backwards after firing of the propellant charge, along a rear axial extension of the projectile provided with means for stopping the piston at its rear end.
  • a particular non-limiting field of application of the invention is that of missile launching devices, for example anti-tank projectiles.
  • the absence of recoil results from balancing the momentum of the projectile with that of the inert mass ejected from the rear of the launch tube, the piston preventing the ejection of gas. rearward.
  • the means for retaining the pistons are formed by narrowing of the launch tube, this can only be used once. In the case of shots carried out with an aiming member mounted on the launching tube, it is then necessary to replace the aiming member each time. If the retaining means are formed in a container introduced into the launching tube, this relatively bulky container must be removed from the tube after each shot. Finally, in the case where the retaining means are provided on a rear extension of the projectile, they only provide temporary restraint. In the latter case, the envelope of the inert mass, the piston contained in this envelope and the piston associated with the propellant charge of the projectile are ejected at the rear under the effect of the combustion of this charge which continues after the Firing.
  • patent GB 241,240 describes a projectile in a launching tube with a charge, a separation disc, an inert mass and a closing disc housed in this order at the rear of the projectile between a rod secured to the projectile and the inner wall of the launch tube.
  • the assembly is assembled by a bolt screwed to the end of the rod.
  • the closing disc, the inert charge, the separating disc and the gases are ejected from the rear at the time of ignition.
  • the object of the present invention is to provide a device that is as simple as possible making it possible to fire a projectile with a minimum of operations and discomfort for the weapon's servants, and in particular with the possibility of immediate re-use of the launching tube. , and with no other rear ejection than that of the inert mass.
  • the device according to the invention comprises a minimum of parts.
  • the rod on which the piston is permanently retained being launched with the projectile, the inert mass ejected at the rear is the only part of the device remaining in place. After firing, the launch tube is therefore ready to be loaded again.
  • the rod extends rearward at least to the rear end of the inert mass.
  • the means for retaining the piston on the rod are simply formed by a bulge in the free end of the rod.
  • the propellant charge, the piston and the inert mass are arranged around the rod, the piston sealingly separating the propellant charge of the inert mass inside the annular space situated between the external surface of the rod and the internal surface of the launching tube when the device is loaded in the latter.
  • the rod can then be full or hollow.
  • the aerodynamic stabilization means are then constituted by the piston, the face of which faces towards the projectile has the shape of a cap with a surface of revolution.
  • the rod is tubular laire, and the propellant charge, the inert mass and the piston sealingly separating the propellant charge from the inert mass are housed inside the rod.
  • the aerodynamic stabilization means then consist of a tail unit carried by the rod.
  • FIGS. 1 and 2 illustrate, in FIGS. 1 and 2, two embodiments of a device according to the invention loaded into its launch tube.
  • FIG. 1 there is schematically shown a launch tube 10 open at its two ends and inside which is loaded an assembly comprising, from front to rear, a missile or projectile 11, a propellant charge 12 , a piston 13 and an inert mass 14.
  • the load 12 and the mass 14 are in direct contact with the opposite faces of the piston 13.
  • the piston 13 sealingly separates the charge 12 from the mass 14 inside an annular space delimited by the internal face of the tube 10 and the external face of a hollow rod 15 coaxial with the tube 10 and extending the projectile 11 at its rear part.
  • the projectile 11 proper is disposed directly inside the tube 10 and is guided at its periphery by the internal face of this tube 10.
  • the propellant charge block 12, the piston 13 and the inert mass 14 s' each write inside a same cylindrical surface with circular section of diameter equal to the inside diameter of the launching tube.
  • the propellant charge 12 is placed immediately behind the actual projectile 11. It consists, for example, as known per se, of a gunpowder block provided with an ignition system (not shown).
  • the inert charge 14 is very fragmented and of low specific mass so that its braking, after ejection at the rear of the launch tube, takes place over a short distance.
  • the constituent material of the filler 14 it is possible, for example, to use very thin strips or discs of paper or plastic materials.
  • the rod 15 extends to the rear end of the inert mass 14.
  • An external bulge 16 is formed at the free end of the rod 15.
  • Other means may of course be provided at this end of the rod to retain the piston 13.
  • the piston 13 slides without play on the external surface of the rod 15 and on the internal surface of the launching tube 10, it prevents ejection of the gases towards the rear.
  • the piston is braked then immobilized by the bulge 16 constituted by a progressive increase in the outside diameter of the rod 15.
  • the tube 10 After firing, the inert mass 14 being ejected at the rear and the hot gases being expelled at the front, the tube 10 is empty and ready to be reused.
  • the projectile 10 proper drives the piston 13 at the rear end of the rod 15 secured to the projectile 10.
  • the piston 13 is given a shape such that it aerodynamically stabilizes the projectile in flight.
  • the front face 13a of the piston 13 facing the projectile is a surface of revolution around the axis of the rod 15 in the form of a quadric cap such as a paraboloid or ellipsoid pierced for the passage of the rod 15 and of which the top is directed forward.
  • the projectile is extended axially towards the rear by a single hollow rod 15.
  • a single hollow rod 15 it is possible to provide several solid or hollow rods and directed axially.
  • small orifices may be formed in the wall of the launching tube, at the front thereof, in order to evacuate the gases under pressure to avoid detonation when firing.
  • FIG. 2 schematically shows a second embodiment of a device according to the invention loaded into the tube 10.
  • This device comprises, from the front to the rear, as in the previous case, a missile or projectile 21 guided directly by the tube 10, a propellant charge 22 disposed directly behind the projectile 21 proper, a piston 23 and a mass inert 24.
  • the load 22 and the mass 24 are in direct contact with the opposite faces of the piston 23.
  • the piston 23 sealingly separates the load 22 from the mass 24 inside a tubular rod 25 extending axially the rear part of the projectile 21 and integral therewith.
  • This projectile tube 25 has a circular cross section with an external diameter less than the internal diameter of the launch tube 10 and is therefore housed inside the latter without contact with its wall.
  • the projectile tube 25 can be provided at its rear part with fins 27 which, when fired, are guided by the interior surface of the launch tube and which, during flight, form a stabilizer stabilizing the projectile.
  • the inert mass 24 is housed entirely inside the projectile tube 25, for example up to the rear end thereof.
  • the projectile tube 25 has an internal bulge 26 formed by a progressive narrowing of its internal diameter.
  • the gases produced accelerate the actual projectile 21 forwards, and the piston 23, pushing the inert mass 24, towards the rear.
  • the piston 23 slides without play in the projectile tube 25 from its initial position close to the end of the projectile tube 25 near the rear part of the projectile 21, to the rear end of the projectile tube 25 where the bulge 26 brakes and immobilizes it.
  • the piston 23 keeps the gases trapped in the projectile tube 25, so that there is also no gas expelled in front of the launch tube.
  • the launch tube 10 After firing, the launch tube 10 is empty and ready to be immediately reused.
  • the projectile 21 in flight is aerodynamically stabilized by the tail 27 carried by the projectile rod 25 in which the gases are kept trapped by the piston 23.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)

Claims (7)

1. Vorrichtung zum Abfeuern eines Geschosses ohne rückwärtige Gasabfuhr und ohne Rückstoß mittels eines beidseitig offenen Abschußrohres (10), die ein Geschoß (11, 21), einen hinter dem Geschoß angeordneten Treibsatz (12, 22), eine hinter dem Treibsatz angeordnete träge Masse (14, 24), die während des Abfeuerns am hinteren Ende des Abschußrohres ausgeworfen werden soll, und einen Kolben (13, 23), der den Treibsatz dicht von der trägen Masse abtrennt, und der nach Zündung des Treibsatzes längs einer hinteren axialen, an ihrem hinteren Ende mit Mitteln zum Stoppen des Kolbens versehenen Verlängerung des Geschosses nach hinten gleiten kann, aufweist, dadurch gekennzeichnet, daß das Geschoß (11, 21) an seinem hinteren Ende durch mindestens eine mit ihm fest verbundene Stange (15, 25) verlängert ist, die einen kleineren Außendurchmesser als das Geschoß aufweist, der Kolben (13, 23) sich in direktem Kontakt mit dem Treibsatz (12, 22) und der trägen Masse (14, 24) befindet, die Mittel zum Stoppen des Kolbens Mittel zum ständigen Zurückhalten des Kolbens auf der Stange sind, und Mittel (13, 27) zum aerodynamischen Stabilisieren des Flugs des Geschosses mit der Stange und dem Kolben vorgesehen sind.
2. Vorrichtung nach Anspruch 1, dadurch gekennzeichnet, daß sich die Stange (15, 24) mindestens bis zum hinteren Ende der trägen Masse (14, 24) nach hinten erstreckt.
3. Vorrichtung nach einem der Ansprüche 1 oder 2, dadurch gekennzeichnet, daß die Mittel zum Zurückhalten des Kolbens (13, 23) durch eine Ausbauchung (16, 26) des freien Endes der Stange (15, 25) gebildet werden.
4. Vorrichtung nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, daß der Treibsatz (12), der Kolben (13) und die träge Masse (14) um die Stange (15) herum angeordnet sind, wobei der Kolben (13) den Treibsatz (12) während die Vorrichtung in dem Abschußrohr (10) geladen ist, im Inneren des ringförmigen Raumes zwischen der Außenfläche der Stange (15) und der Innenfläche des Abschußrohrs (10) dicht von der trägen Masse (14) trennt.
5. Vorrichtung nach Anspruch 4, dadurch gekennzeichnet, daß der Kolben (13) die Mittel zum aerodynamischen Stabilisieren darstellt, dessen zum Geschoß (11) hinzeigende Fläche (13a) die Form einer Glocke mit rotationssymmetrischer Oberfläche hat.
6. Vorrichtung nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, daß die Stange (25) rohrförmig ist, der Treibsatz (22), die träge Masse (24) und der Kolben (23) im Inneren der Stange (25) untergebracht sind, wobei der Kolben (23) den Treibsatz (22) dicht von der trägen Masse (24) abtrennt.
7. Vorrichtung nach Anspruch 6, dadurch gekennzeichnet, daß die Mittel zum aerodynamischen Stabilisieren aus von der Stange (25) getragenen Flügeln (27) bestehen.
EP19800401451 1979-10-10 1980-10-09 Vorrichtung zum Abfeuern eines Geschosses ohne rückwärtige Gasabfuhr und ohne Rückstoss mittels eines beidseitig offenen Abschussrohres Expired EP0027418B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR7925232 1979-10-10
FR7925232A FR2467380B1 (fr) 1979-10-10 1979-10-10 Dispositif de tir sans ejection de gaz vers l'arriere, ni recul

Publications (2)

Publication Number Publication Date
EP0027418A1 EP0027418A1 (de) 1981-04-22
EP0027418B1 true EP0027418B1 (de) 1985-03-20

Family

ID=9230542

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19800401451 Expired EP0027418B1 (de) 1979-10-10 1980-10-09 Vorrichtung zum Abfeuern eines Geschosses ohne rückwärtige Gasabfuhr und ohne Rückstoss mittels eines beidseitig offenen Abschussrohres

Country Status (5)

Country Link
EP (1) EP0027418B1 (de)
CA (1) CA1142782A (de)
DE (1) DE3070323D1 (de)
ES (1) ES495746A0 (de)
FR (1) FR2467380B1 (de)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2558946B1 (fr) * 1984-01-27 1988-04-08 Brandt Armements Tube de lancement pour arme de tir sans recul
FR2602040B1 (fr) * 1986-07-23 1988-11-10 Serat Perfectionnements apportes aux armes, ou systemes lanceurs, sans recul, de projectiles
CN110160396A (zh) * 2019-05-15 2019-08-23 南京理工大学 一种基于分级药室的灭火弹发射装置及方法

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR597391A (fr) * 1924-04-29 1925-11-19 Dispositif et pièce pour un tir sans réaction
DE1012849B (de) * 1955-05-20 1957-07-25 Ludger Volpert Geschoss mit Selbstvortrieb
FR1326176A (fr) * 1961-07-20 1963-05-03 Energa Projectile
CH493818A (de) * 1968-03-07 1970-07-15 Oerlikon Buehrle Ag Geschoss mit Hohlsprengladung
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 (de) * 1975-11-27 1984-05-10 Rheinmetall GmbH, 4000 Düsseldorf Rückstoß- und knallfrei abschießbares Geschoß

Also Published As

Publication number Publication date
FR2467380A1 (fr) 1981-04-17
ES8105859A1 (es) 1981-06-16
FR2467380B1 (fr) 1986-04-18
DE3070323D1 (en) 1985-04-25
EP0027418A1 (de) 1981-04-22
CA1142782A (en) 1983-03-15
ES495746A0 (es) 1981-06-16

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