EP0027418A1 - 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

Info

Publication number: EP0027418A1
Authority: EP; European Patent Office
Prior art keywords: projectile; piston; rod; inert mass; propellant charge
Prior art date: 1979-10-10
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.): Granted

Application number

EP19800401451

Other languages

English (en)

French (fr)

Other versions

EP0027418B1 (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.)

1979-10-10

Filing date

1980-10-09

Publication date

1981-04-22

1980-10-09 Application filed by Societe Europeenne de Propulsion SEP SA filed Critical Societe Europeenne de Propulsion SEP SA

1981-04-22 Publication of EP0027418A1 publication Critical patent/EP0027418A1/de

1985-03-20 Application granted granted Critical

1985-03-20 Publication of EP0027418B1 publication Critical patent/EP0027418B1/de

Status Expired legal-status Critical Current

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Images

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 missiles.
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.
two push pistons are provided, one acting on the projectile and the other on the inert mass and are activated by the same propellant charge or two different charges.
Means are then provided on the launching tube, on a container containing the projectile, propellant charge, inert mass and pistons assembly, or on a rear extension of the projectile to retain the pistons when fired.
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.
the present invention aims to provide a device as simple as possible for carrying out projectile fire with a minimum of operations and discomfort for the weapon staff, and in particular with the possibility of immediate reuse of the tube launch, and with no other rear ejection than that of the inert mass.
a device of the type defined at the head of the description in which, in accordance with the invention, the projectile is extended at its rear part by at least one rod secured to the projectile and of external diameter less than that of the projectile; the piston is in direct contact with both the propellant charge and the inert mass 1 the means for stopping the piston are means for permanently retaining the piston on the rod, and means are provided to aerodynamically stabilize in flight the projectile with the rod and the piston.
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 from the inert mass inside the annular space located between the external surface of the rod and the internal surface of the launch 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, 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 are then constituted by 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 in 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. Similarly, the propellant charge block 12, the piston 13 and the inert mass 14 s' each enter within the 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 material constituting the load 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 11 is a surface of revolution around the axis of the rod 15 in the form of a quadric cap such as paraboloid or ellipsoid pierced for the passage of the rod 15 and whose apex is directed forward.
the projectile 11 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 front to 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 gradual 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 him.
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.

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

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 true EP0027418A1 (de)	1981-04-22
EP0027418B1 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)	ES8105859A1 (de)
FR (1)	FR2467380B1 (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
FR2558946A1 (fr) *	1984-01-27	1985-08-02	Brandt Armements	Tube de lancement pour arme de tir sans recul
FR2602040A1 (fr) *	1986-07-23	1988-01-29	Serat	Perfectionnements apportes aux armes, ou systemes lanceurs, sans recul, de projectiles

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
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

Citations (5)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
GB241240A (en) *	1924-04-29	1926-02-18	Bohdan Pantoflicek	Improvements in ammunition for non recoil guns
DE1012849B (de) *	1955-05-20	1957-07-25	Ludger Volpert	Geschoss mit Selbstvortrieb
FR1326176A (fr) *	1961-07-20	1963-05-03	Energa	Projectile
FR2003374A1 (de) *	1968-03-07	1969-11-07	Oerlikon Buehrle Ag
DE2553201A1 (de) *	1975-11-27	1979-10-31	Rheinmetall Gmbh	Rueckstoss- und knallfrei abschiessbares geschoss

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
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

1979
- 1979-10-10 FR FR7925232A patent/FR2467380B1/fr not_active Expired
1980
- 1980-10-08 ES ES495746A patent/ES8105859A1/es not_active Expired
- 1980-10-09 EP EP19800401451 patent/EP0027418B1/de not_active Expired
- 1980-10-09 DE DE8080401451T patent/DE3070323D1/de not_active Expired
- 1980-10-10 CA CA000362148A patent/CA1142782A/en not_active Expired

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
GB241240A (en) *	1924-04-29	1926-02-18	Bohdan Pantoflicek	Improvements in ammunition for non recoil guns
GB233347A (en) *	1924-04-29	1926-03-11	Bohdan Pantoflicek	Improvements in or relating to non-recoil-guns and ammunition therefor
DE1012849B (de) *	1955-05-20	1957-07-25	Ludger Volpert	Geschoss mit Selbstvortrieb
FR1326176A (fr) *	1961-07-20	1963-05-03	Energa	Projectile
FR2003374A1 (de) *	1968-03-07	1969-11-07	Oerlikon Buehrle Ag
US3580174A (en) *	1968-03-07	1971-05-25	Oerlikon Buehrle Ag	Projectile with hollow explosive charge
DE2553201A1 (de) *	1975-11-27	1979-10-31	Rheinmetall Gmbh	Rueckstoss- und knallfrei abschiessbares geschoss
FR2435015A1 (fr) *	1975-11-27	1980-03-28	Rheinmetall Gmbh	Projectile pouvant etre tire sans recul et sans detonation
GB1581538A (en) *	1975-11-27	1980-12-17	Rheinmetall Gmbh	Projectile

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
FR2558946A1 (fr) *	1984-01-27	1985-08-02	Brandt Armements	Tube de lancement pour arme de tir sans recul
FR2602040A1 (fr) *	1986-07-23	1988-01-29	Serat	Perfectionnements apportes aux armes, ou systemes lanceurs, sans recul, de projectiles
EP0256894A1 (de) *	1986-07-23	1988-02-24	Societe D'etudes De Realisations Et D'applications Techniques ( S.E.R.A.T.)	Rückstossfreie Geschütze oder Abschusssysteme

Also Published As

Publication number	Publication date
FR2467380B1 (fr)	1986-04-18
FR2467380A1 (fr)	1981-04-17
EP0027418B1 (de)	1985-03-20
ES495746A0 (es)	1981-06-16
DE3070323D1 (en)	1985-04-25
ES8105859A1 (es)	1981-06-16
CA1142782A (en)	1983-03-15

Legal Events

Date	Code	Title	Description
1981-02-23	PUAI	Public reference made under article 153(3) epc to a published international application that has entered the european phase	Free format text: ORIGINAL CODE: 0009012
1981-04-22	AK	Designated contracting states	Designated state(s): CH DE GB IT SE
1981-12-09	17P	Request for examination filed	Effective date: 19810929
1984-08-07	ITF	It: translation for a ep patent filed	Owner name: JACOBACCI & PERANI S.P.A.
1985-01-19	GRAA	(expected) grant	Free format text: ORIGINAL CODE: 0009210
1985-03-20	AK	Designated contracting states	Designated state(s): CH DE GB IT LI SE
1985-04-25	REF	Corresponds to:	Ref document number: 3070323 Country of ref document: DE Date of ref document: 19850425
1986-01-21	PLBE	No opposition filed within time limit	Free format text: ORIGINAL CODE: 0009261
1986-01-21	STAA	Information on the status of an ep patent application or granted ep patent	Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT
1986-03-12	26N	No opposition filed
1986-10-10	PG25	Lapsed in a contracting state [announced via postgrant information from national office to epo]	Ref country code: SE Effective date: 19861010
1986-10-31	PG25	Lapsed in a contracting state [announced via postgrant information from national office to epo]	Ref country code: LI Effective date: 19861031 Ref country code: CH Effective date: 19861031
1987-06-30	REG	Reference to a national code	Ref country code: CH Ref legal event code: PL
1987-07-01	GBPC	Gb: european patent ceased through non-payment of renewal fee
1987-07-01	PG25	Lapsed in a contracting state [announced via postgrant information from national office to epo]	Ref country code: DE Effective date: 19870701
1988-11-18	PG25	Lapsed in a contracting state [announced via postgrant information from national office to epo]	Ref country code: GB Effective date: 19881118
1995-01-31	EUG	Se: european patent has lapsed	Ref document number: 80401451.2 Effective date: 19870811

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