EP0884553A1 - Antriebsgerät für eine die Rückstossenergie begrenzendes Geschoss - Google Patents

Antriebsgerät für eine die Rückstossenergie begrenzendes Geschoss Download PDF

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Publication number
EP0884553A1
EP0884553A1 EP98401424A EP98401424A EP0884553A1 EP 0884553 A1 EP0884553 A1 EP 0884553A1 EP 98401424 A EP98401424 A EP 98401424A EP 98401424 A EP98401424 A EP 98401424A EP 0884553 A1 EP0884553 A1 EP 0884553A1
Authority
EP
European Patent Office
Prior art keywords
projectile
chamber
assembly according
rod
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.)
Granted
Application number
EP98401424A
Other languages
English (en)
French (fr)
Other versions
EP0884553B1 (de
Inventor
Pascal Gendre
Grégory Soulier
Régis Riffet
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.)
Etienne LaCroix Tous Artifices SA
Original Assignee
Etienne LaCroix Tous Artifices 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 Etienne LaCroix Tous Artifices SA filed Critical Etienne LaCroix Tous Artifices SA
Publication of EP0884553A1 publication Critical patent/EP0884553A1/de
Application granted granted Critical
Publication of EP0884553B1 publication Critical patent/EP0884553B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B5/00—Cartridge ammunition, e.g. separately-loaded propellant charges
    • F42B5/02—Cartridges, i.e. cases with charge and missile
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C19/00—Details of fuzes
    • F42C19/08—Primers; Detonators
    • F42C19/0823—Primers or igniters for the initiation or the propellant charge in a cartridged ammunition
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C19/00—Details of fuzes
    • F42C19/08—Primers; Detonators
    • F42C19/0823—Primers or igniters for the initiation or the propellant charge in a cartridged ammunition
    • F42C19/0826—Primers or igniters for the initiation or the propellant charge in a cartridged ammunition comprising an elongated perforated tube, i.e. flame tube, for the transmission of the initial energy to the propellant charge, e.g. used for artillery shells and kinetic energy penetrators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C19/00—Details of fuzes
    • F42C19/08—Primers; Detonators
    • F42C19/0823—Primers or igniters for the initiation or the propellant charge in a cartridged ammunition
    • F42C19/083—Primers or igniters for the initiation or the propellant charge in a cartridged ammunition characterised by the shape and configuration of the base element embedded in the cartridge bottom, e.g. the housing for the squib or percussion cap

Definitions

  • the present invention relates to the field of sets of propulsion for projectiles, in particular the field of tube systems projectile launchers.
  • the present invention finds in particular, but not exclusively, application in the field of weapons. It is indeed not limited to this preferred application, but can be used in any launcher projectile, such as, for example, rocket launching tubes for fireworks, alarm signals, anti-hail rockets, or even in launch tubes on test benches in which projectiles can be formed by example of carriages or equivalent, in particular for impact tests, etc ...
  • launcher projectile such as, for example, rocket launching tubes for fireworks, alarm signals, anti-hail rockets, or even in launch tubes on test benches in which projectiles can be formed by example of carriages or equivalent, in particular for impact tests, etc ...
  • projectile tube launching systems include, as shown in Figure 1 attached, a barrel tube 10, a cylinder head or bottom 12 closing the tube 10 at one end and a pressure source 14, generally formed by a cartridge pyrotechnic.
  • a projectile propulsion unit of the type comprising a room that houses a pressure source and communicates with a space trigger through a passage controlled by a valve control system to control the driving pressure of the projectile and preferably adapted to define a constant pressure in the relaxation room.
  • WO-A-9107636 describes a projectile comprising timed ejection means of a load. More specifically, this document describes a launcher comprising a pressure source not shown, suitable for launching a projectile.
  • the projectile includes a payload, a first pressure chamber and a second pressure chamber.
  • a valve ensures the supply of the first pressure chamber to from the source.
  • the first pressure chamber communicates by elsewhere with the second pressure chamber through an orifice calibrated. More precisely the second chamber is defined between a piston likely to push the payload and a housing defining the first chamber, the piston and the casing being connected by a shear pin.
  • the first chamber is filled, according to the essential characteristic of this document, by a fibrous material. How this projectile works is basically the following. When launching the first room is charged at constant pressure via the valve. Pressure in the second room rises gradually until the pin. The piston then deposits the payload with a sudden rise in the pressure in the second chamber thanks to the passage thus freed from the connection between the two pressure
  • the NAVY TECHN document. DISCLOS. BULL., Vol. III, n ° 3, March 1978, DAHLGREN VIRGINIA describes a thruster provided on a system launcher or on a projectile. This document mainly relates to means for adjusting a surface ratio between an orifice leading to the relaxation room and vents.
  • GB-A-484346 describes a cartridge comprising a projectile guide means in the form of a central internal tube. A part of the propellant charge is placed inside this tube forming projectile guidance means and another part of the propellant charge is disposed outside of this guide tube. So, to allow on the one hand to guarantee a simultaneous initiation of the two parts of the propellant charge and on the other hand an equi-pressure between the interior and outside the guide tube, the latter is perforated. However, the provision described in this document in no way controls the propulsion pressure, and in particular keep it at least substantially constant.
  • the present invention now aims to improve the known projectile propulsion systems, in order to improve the performance of these.
  • a main object of the present invention is to modify the internal ballistic of the launcher tube so that the internal pressure in the tube when firing is as constant as possible.
  • a projectile propulsion unit of the type comprising a chamber which houses a pressure source, characterized in that said chamber that houses the pressure source communicates with at least one rod placed in the starter tube and comprising bores distributed over the length to be released successively during the ejection of the projectile.
  • the arrangement (including distribution, number and size) of the bores provided in the rod is suitable for ensuring propulsion pressure at least substantially constant in the launcher tube.
  • the rod with bores distributed over its length is interposed between the chamber which houses the pressure source and the expansion chamber which ensures the propulsion of the projectile.
  • the present invention also relates to suitable projectiles to be fired from such a power package.
  • the propulsion assembly according to the present invention includes a launcher tube 100.
  • a launcher tube 100 with closed barrel that is to say the bottom is closed by a cylinder head 110 or equivalent.
  • the launcher tube receives a pressure source 120.
  • a pressure source 120 are preferably a pyrotechnic cartridge.
  • the source of pressure 120 can be formed by any equivalent means.
  • the tube 100 is adapted to receive a projectile 200. This is adapted to the internal gauge of the tube 100 as seen in the figures attached.
  • the chamber which houses the pressure source 120 communicates with a rod 130 placed in the launcher tube 100.
  • the rod 130 comprises bores 132 distributed over its length to be released successively when projectile 200 is ejected.
  • the projectile 200 is provided with a chamber 210 opening on its rear end, which chamber 210 is adapted to the diameter outside of the rod 130.
  • the projectile 200 originally covers the majority of bores 132 but gradually releases these during its displacement.
  • the tube 100 and the projectile 200 can be the subject of numerous embodiments. They will therefore not be described in detail by the after.
  • the pressure source or pyrotechnic cartridge 120 is placed directly into the rod 130 so that the chamber 122 which houses the pressure source 120 communicates directly with chamber 140 which receives the projectile 200 via the bores 132.
  • an intermediate chamber 150 is interposed between the chamber very high pressure 122 which houses the source 120 and the chamber 140 receiving the projectile 200.
  • This high pressure intermediate chamber 150 communicates with the internal volume of the rod 130.
  • the rod 130 is closed at its front end by a transverse partition 134 so that the only possible communication between the internal volume of the rod 130 and the chamber 140 receiving the projectile 200 corresponds to bores 132.
  • At least one of the orifices 132 formed in the rod 130 communicates with said chamber 140 receiving the projectile 200, to allow high pressure gas circulation at from the internal volume of the rod 130 towards this chamber 140.
  • This orifice is illustrated under reference 132a in the appended figures. According to the figure 3, it is the orifice (s) closest to the cylinder head 110.
  • the orifice (orifices) 132 which opens (s) initially in room 140 is the one (s) located (s) the most forward, that is to say the closest to the wall 134 (according to FIGS. 4a at 4c, this orifice 132a is then temporarily closed by the projectile 200 after the start of the shot and before the projectile 200 leaves the tube 100).
  • the projectile 200 can be held in the tube 100 before firing by any suitable conventional means, for example by pins shearable.
  • the projectile 200 is provided with a tail unit 220 at its rear end.
  • This empennage 220 is adapted to initially seal all of the ports 132 of the cane with the sole exception of the above-mentioned port 132a.
  • the arrangement of the orifices 132 in particular their distribution, size and number, is suitable for ensuring propulsion pressure at least substantially constant in the propulsion chamber 140.
  • the wall of the rod 130 perforated by the openings 132 is inserted directly or indirectly (via the high pressure chamber 150) between the chamber which houses the pressure source 120 and the propulsion chamber 140.
  • the operation of the propellant assembly in accordance with this invention essentially comprises three successive phases.
  • the pressure prevailing in the launcher tube 100 during these three successive faces is illustrated by way of nonlimiting example in FIG. 5.
  • the pyrotechnic cartridge 120 When ignited, the pyrotechnic cartridge 120 (or the source equivalent pressure formed for example from a gas source compressed) generates very high pressure gases which fill the rod 130 (directly according to FIG. 3 and after transit via the chamber 150 according to FIG. 4) and flow into chamber 140 via the bore (or bores) 132a. Following this flow through of bore 132a, the driving pressure will increase in chamber 140 during a phase referenced phase 1 in Figure 5 to reach a regulating pressure at the end of this phase 1. Projectile 200 is moved in the tube 100 with the increase in this driving pressure.
  • the initial passage section 132a is completely closed at the end of this phase 1, but on the other hand the rear bores 132 are discovered.
  • the displacement of the projectile 200 unmask as the bores 132 formed in the rod 130 to maintain in the form of a plate substantially constant driving pressure in room 140.
  • Progressive release bores 132 increase the fluid flow rate between the source of pressure 120 and the launching chamber 140 to maintain the pressure drive at an at least substantially constant value.
  • a third phase begins when the 200 projectile has exposed all orifices 132.
  • the driving pressure can no longer be maintained at a constant regulation threshold. Then begins a low relaxation phase pressure as illustrated in figure 5.
  • FIGS. 4a, 4b and 4c the projectile 200 is illustrated respectively in the positions occupied in phase 1, phase 2 and phase 3 of Figure 5.
  • the number, size and position of the bores 132 must be adapted according to the power of the pressure source 120, the caliber and mass of the 200 projectile.
  • the rod 130 has a length of 120 mm and a diameter 26 mm and it has 24 bores 132 formed of circular orifice with a diameter of around 2 mm distributed with a variable pitch from 21 to 12 mm along the length of the rod 130 and also provided with 3 holes 132a with a diameter of 1.5mm.
  • propulsion device in accordance with this invention can be combined with any other known structure capable of reduce the force of retraction of the tube 100, for example all means shock absorbers compatible with this propulsion system.
  • the present invention finds particular application in shoulder shooting systems.
  • the present invention offers many advantages over known prior systems.
  • the rod 130 can be integrated into the cylinder head not consumable from a cannon or in a consumable socket secured to a projectile.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)
  • Excavating Of Shafts Or Tunnels (AREA)
EP98401424A 1997-06-11 1998-06-11 Antriebsgerät für eine die Rückstossenergie begrenzendes Geschoss Expired - Lifetime EP0884553B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9707226A FR2764682B1 (fr) 1997-06-11 1997-06-11 Ensemble de propulsion pour projectile limitant l'effort de recul
FR9707226 1997-06-11

Publications (2)

Publication Number Publication Date
EP0884553A1 true EP0884553A1 (de) 1998-12-16
EP0884553B1 EP0884553B1 (de) 2003-02-12

Family

ID=9507847

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98401424A Expired - Lifetime EP0884553B1 (de) 1997-06-11 1998-06-11 Antriebsgerät für eine die Rückstossenergie begrenzendes Geschoss

Country Status (5)

Country Link
US (1) US6044746A (de)
EP (1) EP0884553B1 (de)
CA (1) CA2239154C (de)
DE (1) DE69811291T2 (de)
FR (1) FR2764682B1 (de)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2739930B1 (de) * 2011-08-04 2016-10-12 Polywad, Inc. Rückstossabgeschwächtes nutzlastträgersystem
US8967046B2 (en) * 2012-11-30 2015-03-03 Alliant Techsystems Inc. Gas generators, launch tubes including gas generators and related systems and methods
US9448033B2 (en) * 2013-07-11 2016-09-20 The United States Of America As Represented By The Secretary Of The Army Projectile launcher with a permanent high-low pressure system
US10281248B2 (en) 2015-11-11 2019-05-07 Northrop Grumman Innovation Systems, Inc. Gas generators, launch tube assemblies including gas generators, and related systems and methods

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB484346A (en) 1936-04-03 1938-05-04 Sageb Sa Improvements in or relating to cartridges for firearms
US3628415A (en) 1970-01-27 1971-12-21 Stuart H Mcelroy Mortar
EP0090155A2 (de) * 1982-03-30 1983-10-05 Affärsverket FFV Treibladungskartusche für eine Mörsergeschoss
DE3336295A1 (de) * 1983-10-06 1985-04-25 Norbert 2000 Hamburg Bork Revolverpatrone mit gasdichtungshuelse
WO1991007636A1 (en) 1989-11-21 1991-05-30 Saab Missiles Aktiebolag Projectile for the dispersal of a load with time delay
FR2713324A1 (fr) 1993-11-30 1995-06-09 Lacroix E Tous Artifices Ensemble de propulsion pour projectile.

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB592092A (en) * 1944-12-16 1947-09-08 Charles Dennistoun Burney Improvements in or relating to ordnance
US1347125A (en) * 1919-02-28 1920-07-20 Schneider & Cie Projectile for bomb-throwers
US2651972A (en) * 1949-10-31 1953-09-15 Edmund H Engelke Stop shoulder for recoilless rifle ammunition
NL65695C (de) * 1961-07-20 Energa
US3138991A (en) * 1962-01-10 1964-06-30 Richard L Malter Firearm muzzle attachment and projectile with expansible, detachable husk
NL137772C (de) * 1965-06-22
US3376784A (en) * 1965-07-05 1968-04-09 Forsvarets Fabriksverk Spacing member for a recoil-free weapon
US3505924A (en) * 1967-04-18 1970-04-14 Allied Res Ass Inc Silent mortar
DE2713324A1 (de) * 1976-03-30 1977-10-27 Submarine Eng As Vorrichtung zum auffangen von erdoel oder dergleichen am wasser
US4038902A (en) * 1976-08-17 1977-08-02 Welsh Robert B Artillery weapon
US4782758A (en) * 1986-02-03 1988-11-08 Aerojet-General Corporation Ammunition round
US4803927A (en) * 1986-02-03 1989-02-14 Aerojet-General Corporation Ammunition round and method of manufacture thereof
US4962689A (en) * 1989-08-01 1990-10-16 Hughes Aircraft Company Gas generator missile launch system
DE3939295A1 (de) * 1989-11-28 1991-05-29 Rheinmetall Gmbh Verfahren und vorrichtung zur herstellung von grosskalibriger munition
US5837919A (en) * 1996-12-05 1998-11-17 The United States Of America As Represented By The Secretary Of The Navy Portable launcher

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB484346A (en) 1936-04-03 1938-05-04 Sageb Sa Improvements in or relating to cartridges for firearms
US3628415A (en) 1970-01-27 1971-12-21 Stuart H Mcelroy Mortar
EP0090155A2 (de) * 1982-03-30 1983-10-05 Affärsverket FFV Treibladungskartusche für eine Mörsergeschoss
DE3336295A1 (de) * 1983-10-06 1985-04-25 Norbert 2000 Hamburg Bork Revolverpatrone mit gasdichtungshuelse
WO1991007636A1 (en) 1989-11-21 1991-05-30 Saab Missiles Aktiebolag Projectile for the dispersal of a load with time delay
FR2713324A1 (fr) 1993-11-30 1995-06-09 Lacroix E Tous Artifices Ensemble de propulsion pour projectile.

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
"navy techn. disclos. bull", vol. 3, part 3 March 1978, DAHLGREN VIRGINIA

Also Published As

Publication number Publication date
CA2239154C (fr) 2006-08-15
FR2764682B1 (fr) 1999-09-03
US6044746A (en) 2000-04-04
CA2239154A1 (fr) 1998-12-11
DE69811291D1 (de) 2003-03-20
EP0884553B1 (de) 2003-02-12
FR2764682A1 (fr) 1998-12-18
DE69811291T2 (de) 2003-11-06

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