EP0145132A1 - Abschussvorrichtung - Google Patents

Abschussvorrichtung Download PDF

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Publication number
EP0145132A1
EP0145132A1 EP84306141A EP84306141A EP0145132A1 EP 0145132 A1 EP0145132 A1 EP 0145132A1 EP 84306141 A EP84306141 A EP 84306141A EP 84306141 A EP84306141 A EP 84306141A EP 0145132 A1 EP0145132 A1 EP 0145132A1
Authority
EP
European Patent Office
Prior art keywords
barrel
sleeve
under pressure
end portion
fluid under
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.)
Withdrawn
Application number
EP84306141A
Other languages
English (en)
French (fr)
Inventor
Roger Frederick Allen
Colin Ian Campbell
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.)
GQ Defence Equipment Ltd
Original Assignee
GQ Defence Equipment Ltd
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 GQ Defence Equipment Ltd filed Critical GQ Defence Equipment Ltd
Publication of EP0145132A1 publication Critical patent/EP0145132A1/de
Withdrawn legal-status Critical Current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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41B—WEAPONS FOR PROJECTING MISSILES WITHOUT USE OF EXPLOSIVE OR COMBUSTIBLE PROPELLANT CHARGE; WEAPONS NOT OTHERWISE PROVIDED FOR
    • F41B11/00—Compressed-gas guns, e.g. air guns; Steam guns

Definitions

  • the present invention relates to projectile propulsive devices and is particularly although not exclusively concerned with a projectile launching device for launching a projectile containing equipment which needs to be deployed at a location remote from the launching site.
  • projectile launching devices which utilise air or gas under pressure for propulsion of the projectile from the launcher.
  • the projectile is mounted in a launcher barrel having a forward open end and a rearward closed end and is launched by supplying air under pressure to the barrel at a position rearward of the projectile and allowing the pressurised air to act on the base of the projectile to propel the projectile along the barrel and discharge it from the forward open end.
  • the forward thrust of the pressurised air on the base of the projectile is balanced by an equal and opposite force on the rearward closed end of the launcher tube with the result that a considerable recoil force is transmitted to the launcher.
  • the launcher can be sited on hard ground or on a rigid structure the recoil forces are adequately absorbed and the accuracy of firing of the launcher not impaired.
  • the launcher is required to be fired for example from a soft ground surface such as a sandy beach the recoil forces are not adequately absorbed and give rise to a displacement of the launcher which adversely affects the firing accuracy and is a hazard to operating personnel.
  • the launcher is mounted on say a light road vehicle or light marine craft the recoil forces are found to be absorbed by displacement of the vehicle or craft, which gives rise to inaccurate firing.
  • the launcher cannot be used if no stable position is available for mounting it.
  • a projectile propulsive device for propelling a projectile under the action of fluid under pressure
  • a barrel having an axial bore with a forward open end from which the projectile is in use propelled by the fluid under pressure, pressurised fluid supply means, and valve means for controlling the supply of fluid under pressure from the supply means to the bore of the barrel through one or more supply apertures in the barrel, characterised by the fact that the bore of the barrel has a rearward open end, whereby at least part of the forward thrust of the fluid under pressure in the axial bore of the barrel is balanced by a rearward thrust of fluid under pressure discharged from the rearward open end of the barrel.
  • the rearward open end of the axial bore of the barrel is formed with a throat end portion providing a constricted opening having a cross-sectional area smaller than that of the bore of the barrel and the throat end portion is removably mounted in the rearward open end of the axial bore of the barrel.
  • a closure end plate may be provided with the device which can be substituted for the throat end portion and which closes the rearward open end of the axial bore of the barrel so that the device can be operated by balancing the forward thrust of the fluid under pressure in the barrel by a rearward thrust on the closure end plate.
  • the throat end portion is formed with an axial bore and the constricted opening is formed therein by a gradual reduction in the cross sectional area of the bore in the direction of flow of fluid therein followed by a gradual increase in cross sectional area of the bore.
  • the gradual reduction in cross sectional area of the bore of the throat end portion is preferably such as to form an annular shoulder within the bore and wherein the gradual increase in cross section is preferably such as to produce a conical enlargement of the bore.
  • the pressurised fluid supply means comprises a chamber for containing fluid under pressure and communicating with the bore of the barrel through the one or more supply apertures and the valve means comprises a closure element movable between a closed position in which it closes the supply aperture or apertures and an open position in which it no longer closes the aperture or apertures.
  • the closure element comprises a sleeve coaxially mounted with respect to the bore of the barrel and axially displaceable along the barrel between the closed and open positions.
  • sleeve displacement means are provided for supplying to an end portion of the sleeve fluid under pressure to produce an axial displacement load on the sleeve to move it from the closed position in the direction of the open position.
  • the sleeve is furthermore so constructed and arranged that when it is in the closed position it is subjected to an axial displacement load from the fluid under pressure in the chamber sufficient to hold it in the closed position in the absence of an application of fluid under pressure from the sleeve displacement means.
  • the area of the end portion of the sleeve to which fluid under pressure is applied by the sleeve displacement means is such that the sleeve is moved from the closed position in the direction of the open position under a pressure no greater than that of the fluid in the chamber and the sleeve is held in the closed position solely by fluid under pressure in the chamber and is movable between the closed and open positions by external impressed forces produced solely by fluid under pressure.
  • the end portion of the sleeve is arranged to engage an end portion of the barrel
  • the end portion of the barrel is formed with two concentric resilient ring seals which engage the end portion of the sleeve
  • the sleeve displacement means is such as to discharge fluid under pressure from the end portion of the barrel in the area between the two seals.
  • the chamber and the sleeve displacement means are arranged to be supplied with fluid under pressure from a single pressure fluid source.
  • Further sleeve displacement means are also provided for supplying to an opposite end portion of the sleeve fluid under pressure to move the sleeve from the open position to the closed position and the further sleeve displacement means is arranged to be supplied with fluid under pressure from the single pressure fluid source.
  • the chamber for containing fluid under pressure and communicating with the bore of the barrel through the supply aperture or apertures needs to be of a robust construction which will support the high pressures to which it is subjected by the fluid in the chamber and in an embodiment of the invention hereinafter to be described
  • the barrel is formed by an inner barrel tube having a rear end portion and a forward end portion, and an outer barrel tube which is coaxial with the inner barrel tube and which is held in compression between the rear and forward barrel end portions of the inner barrel tube by axial adjustment of one of the forward and rear end portions of the inner barrel tube, and the chamber comprises the annular space between the inner and outer barrel tubes.
  • the annular space between the inner and outer barrel tubes communicates with a further annular space, which is formed in the rear end portion of the inner barrel tube and communicates with the axial bore of the inner barrel tube through the supply aperture or apertures.
  • the launcher shown comprises an inner barrel tube 11 of circular cross section, an outer barrel tube 12 also of circular cross section and supported in concentric relationship with the inner barrel tube 11 by engagement in a forwardly facing end groove 13 of a support block 14 mounted on the rear end of the inner barrel tube 11 and in an rearwardly facing end groove 15 formed in a clamping ring 16, which is screwed on to the forward end of the inner barrel tube 11 and tightened down to bring the outer barrel tube 12 under compression.
  • the support block 14 has a rear open end in which is mounted a throat end piece 17 held in place by clamping bolts one of which is shown in Fig. 1 and indicated by the reference numeral 18.
  • the throat end piece 17 is formed with an axial bore which together with the axial bore of the rear end of the support block 14 and the axial bore of the inner barrel tube 11 form the axial bore of the launcher barrel.
  • the axial bore of the throat end piece 17 is constricted at 19 by a gradual reduction in cross section followed by a gradual increase in cross section.
  • the support block 14 is formed with a forwardly extending arm 10 fitted with hand grips 20 and 21 and a mounting support 22.
  • the annular space between the inner and outer barrel tubes 11 and 12 forms a chamber 23 which communicates through axial passageways 24 in the support block 14 with an annular space 25 formed in the rear of the support block 14 and opening into the axial bore of the launcher barrel through a fully circumferentially extending lateral aperture 26.
  • a sleeve 27 is provided for closing off the annular space 25 from the lateral aperture 26 and is mounted coaxially with respect to the bore of the inner barrel tube 11 and is axially slidable in a guide slot 28 between a closed position as shown in Figs.
  • An inlet 42 in the support block 14 is provided for supplying pressurised air to the guide slot 28 which is sealed by ring seals 31 and 32 which engage with the sleeve 27.
  • An inlet duct 40 is provided for supplying pressurised air to the annular space 25 and through the passages 24 to the chamber 23 and a further inlet 41 which communicates with a multiplicity of axially directed ducts 36 is provided for supplying air under pressure to the rear end portion of the sleeve 27.
  • the rear end portion of the sleeve 27 in the closed position of the sleeve firstly abuts against the forwardly facing end face of the support block 14, where it engages a concentric ring seal 37 mounted in the end face, and secondly engages over a forwardly projecting boss portion of the block 14, where it engages a ring seal 38 mounted in the boss portion.
  • the air ducts 36 are positioned to direct air under pressure to the annular area between the seals 37 and 38 and the end of the sleeve 27 is radially extended by flange 39.
  • the construction of the rear end of the sleeve 27 and its manner of cooperation with the ring seals 37 and 38 are made such that when the sleeve 27 takes up the position shown in Figs. 1 and 2 it is held in that position by air under pressure in the annular space 25 acting on the flange 39 which is arranged to present an effective area to the pressurised air in the annular space 25 greater than that presented by the rear end face of the sleeve 27.
  • the effective area of the rear end face of the sleeve 27 can be taken to extend to the inner periphery of the ring seal 37, the diameter of which is greater than the outer diameter of the main body portion of the sleeve. As a consequence of this, there is set up a net axial displacement load produced by pressurised air in the annular space 25 holding the sleeve 27 in the closed position shown in the drawings.
  • the construction of the rear end of the sleeve 27 and the disposition of the ring seal 37 is made such that the effective area of the rear end face of the sleeve 27 to which pressurised air from the ducts 36 is applied is greater than the net effective area presented by the sleeve to the pressurised air in the annular space 25.
  • there is set up a net axial displacement load causing the sleeve 27 to move away from the forwardly facing end face of the support block 14 when pressurised air at a pressure equal to that in the annular space 25 is applied through inlet duct 41 and ducts 36 to the area of the support block 14 between the two ring seals 37 and 38.
  • a pneumatic control system for controlling the application of air under pressure to the inlets 40,41 and 42 is illustrated in Figure 3 and comprises two-position spring biased control valves 43 and 44 each provided with a relief port to atmosphere, a two-position on-off valve 45 provided with a relief port to atmosphere, a metering valve 46 with an associated non-return valve, a pressure regulator 47 with a relief port to atmosphere, and a pressure gauge 48.
  • Air under high pressure from a supply cylinder (not shown) is applied to an input 49 of the control system and fed through line 50 to the two-position valve 45 which in the position shown provides a communication between the line 50 and an output line 51.
  • Air under pressure in line 51 is applied to the two-position valve 43 which is spring biased to the cut-off position shown in Fig. 3, preventing air under pressure from being supplied to output line 52.
  • air under pressure is fed on line 54 to valve 44 likewise spring biased to its cut-off position as shown in Fig. 3 and preventing air under pressure from being supplied to output line 55.
  • Finally air under pressure on the line 51 is applied through line 56 and the manually operable metering valve 46 to output line 57.
  • the valve 44 is operated to move it from the position shown in Figure 3 to its other position in which pressurised air on line 54 is fed through it to inlet 41 and through ducts 36 to the forwardly facing end face of the support block 14 in the area between the two seals 37 and 38.
  • the inlet 42 is connected by the valve 43 to atmosphere in the position of the valve 43 shown in Fig. 3 and as the effective area of the end face of the sleeve 27 to which the pressurised air from ducts 36 is applied is arranged to be greater than that acted upon by the pressurised air in the annular space 25 the sleeve 27 moves forwardly in the guide slot 28.
  • constricted opening 19 By forming the constricted opening 19 a smaller rearwardly moving mass of pressurised air at a higher velocity is used with advantage to balance a greater forwardly moving mass of air at a lower velocity. It will of course be appreciated that a small but insignificant recoil force is applied to the launching device by reason of the constricted opening. For most purposes this small recoil force can be ignored.
  • Re-setting of the launching device shown in Figs. 1 and 2 is effected by first operating the control valve 43 so that it transmits air under pressure from the line 51 to the line 52 and inlet 42. Pressurised air at the inlet 42 is transmitted to the guide slot 28, causing the slide 27 to move back to the position shown in Fig. 1. With the valve 43 held operated, the metering valve 46 is then opened to supply pressurised air through line 57 to inlet 40 for re-charging the chamber 23 and the annular space 25.
  • valve 46 is then closed and the valve 43 released leaving the launching device ready for firing a further projectile front loaded into the inner barrel tube 11.
  • the two-position on-off valve 45 which is normally in the position shown in Fig. 3, can be operated in an emergency to switch it into its other position in which it vents the line 51 to atmosphere and clears the launching device of pressurised air.
  • the projectile launching device illustrated in the drawings is of a very compact construction and is adapted to be fired by an operator from his shoulder. In use, he rests the device on his shoulder with the mounting 22 against it and supports the launcher by gripping the two hand grips 20 and 21.
  • a trigger 9 is provided for firing the device and serves to operate the valve 44 of the pneumatic control system. The operator is subjected to little or no recoil from the device by virtue of the provision of the rearward open end formed by the throat end portion 1-7.
  • the support arm 10 can readily be replaced by any other form of mounting to support the launcher for firing from a ground surface or from a motor vehicle or other craft, with the same advantage that only a relatively insignificant recoil force is developed when the device is fired.
  • the sleeve 27 functions solely under the application of pressurised air and for this reason is less likely to be subject to mechanical failure.
  • the compact construction of the launching device described with reference to the drawings has furthermore the added advantage that the inner and outer barrel tubes 11 and 12 are prestressed and better able to withstand the high pressures applied to them by the pressurised air fed to the chamber 23.
  • the closure element for closing off the lateral aperture 26 from the annular space 25 takes the form of the sleeve 27 which is movable between an open position in which it is retracted in its guide slot 28 and a closed position in which it engages an end portion of the support block 14.
  • the flange 39 formed on the end of the sleeve 27 serves to ensure that the sleeve 27 is held in its closed position in abutment with the end face of the support block 14 by fluid under pressure in the annular space 25. It will however be appreciated that the feature of providing the barrel of the device with a rearward open end may be used with alternative means for closing off the aperture 26.
  • the sleeve 27 and the pneumatic control circuit which controls its displacement may, if desired, be replaced by the sleeve construction and pneumatic control circuit employed in the projectile propulsive device described in our copending European Patent Application No. 83302997.8, with appropriate changes being made to the support block 14 and the inner barrel tube 11 to provide for reception of the alternative sleeve and its movement between its open and closed positions.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Actuator (AREA)
  • Transition And Organic Metals Composition Catalysts For Addition Polymerization (AREA)
EP84306141A 1983-09-09 1984-09-07 Abschussvorrichtung Withdrawn EP0145132A1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB8324142 1983-09-09
GB8324142 1983-09-09

Publications (1)

Publication Number Publication Date
EP0145132A1 true EP0145132A1 (de) 1985-06-19

Family

ID=10548519

Family Applications (1)

Application Number Title Priority Date Filing Date
EP84306141A Withdrawn EP0145132A1 (de) 1983-09-09 1984-09-07 Abschussvorrichtung

Country Status (3)

Country Link
EP (1) EP0145132A1 (de)
JP (1) JPS6078299A (de)
GB (1) GB2146416A (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2013174821A1 (de) * 2012-05-24 2013-11-28 Rheinmetall Waffe Munition Gmbh WAFFENSYSTEM MIT EINER RÜCKSTOßFREIEN ODER RÜCKSTOßARMEN WAFFE UND EINER MIT DER WAFFE VERSCHIEßBAREN GRANATE

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB8417826D0 (en) * 1984-07-12 1984-08-15 Daystate Ltd Capsule gun
US5967133A (en) * 1996-01-16 1999-10-19 Smart Parts, Inc. Pneumatically operated projectile launching device
US6035843A (en) 1996-01-16 2000-03-14 Smart Parts, Inc. Pneumatically operated projectile launching device
US6349711B1 (en) 2000-03-20 2002-02-26 Smart Parts, Inc. Low pressure electrically operated pneumatic paintball gun
US6889681B1 (en) 2000-08-01 2005-05-10 Akalmp, Inc. Electronic pneumatic paintball gun
US6675791B1 (en) 2002-01-17 2004-01-13 Akalmp, Inc. Pressure regulator for pneumatic guns
US7185646B2 (en) 2003-10-27 2007-03-06 Smart Parts, Inc. Pneumatic assembly for a paintball gun
US7617820B2 (en) 2004-06-15 2009-11-17 Smart Parts, Inc. Pneumatic paintball gun
US7556032B2 (en) 2004-06-15 2009-07-07 Smart Parts, Inc. Pneumatic paintball gun
US7640925B2 (en) 2003-10-27 2010-01-05 Smart Parts, Inc. Pneumatic assembly for a paintball gun
CA2542888A1 (en) 2003-10-27 2005-05-19 Smart Parts, Inc. Pneumatic assembly for a paintball gun
US7237544B2 (en) 2003-12-22 2007-07-03 Smart Parts, Inc. Pneumatic paintball gun and components
US7624723B2 (en) 2004-06-15 2009-12-01 Smart Parts, Inc. Paintball gun kit
US7461646B2 (en) 2006-03-08 2008-12-09 Smart Parts, Inc. Bolt for pneumatic paintball gun

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1248961A (fr) * 1959-02-25 1960-12-23 Bofors Ab Dispositif pour armes à feu sans recul
FR1576322A (de) * 1967-08-19 1969-07-25
DE2040863A1 (de) * 1970-08-18 1972-03-02 Eta Corp Rohrfeuerwaffe,insbesondere rueckstossfreie Kanone fuer huelsenlose Ladungen
US3893479A (en) * 1971-06-01 1975-07-08 Gen Electric High rate of flow port for spool valves
FR2352270A1 (fr) * 1976-05-17 1977-12-16 Bofors Ab Dispositif de tir sans recul d'un missile
US4349200A (en) * 1980-07-28 1982-09-14 The Secretary Of State For Defence In Her Britannic Majesty's Government Of The United Kingdom Of Great Britain And Northern Ireland Gas gun for ballistic testing

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1095310A (de) * 1900-01-01
NL137772C (de) * 1965-06-22
DE1954683A1 (de) * 1969-10-30 1971-05-06 Diehl Fa Rueckstossfreie Maschinenwaffe
SE413696B (sv) * 1976-06-15 1980-06-16 Foerenade Fabriksverken Anordning vid rekylfritt vapen
SE442441B (sv) * 1981-02-09 1985-12-23 Ffv Affersverket Fordemningsbricka for rekylfritt vapen
GB2105826A (en) * 1981-08-20 1983-03-30 Colin Ian Campbell Projectile launching device
GB2105447A (en) * 1981-08-20 1983-03-23 Colin Ian Campbell Projectile launching device
SE428604B (sv) * 1981-10-21 1983-07-11 Foerenade Fabriksverken Tryckdempare for rekylfria vapen

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1248961A (fr) * 1959-02-25 1960-12-23 Bofors Ab Dispositif pour armes à feu sans recul
FR1576322A (de) * 1967-08-19 1969-07-25
DE2040863A1 (de) * 1970-08-18 1972-03-02 Eta Corp Rohrfeuerwaffe,insbesondere rueckstossfreie Kanone fuer huelsenlose Ladungen
US3893479A (en) * 1971-06-01 1975-07-08 Gen Electric High rate of flow port for spool valves
FR2352270A1 (fr) * 1976-05-17 1977-12-16 Bofors Ab Dispositif de tir sans recul d'un missile
US4349200A (en) * 1980-07-28 1982-09-14 The Secretary Of State For Defence In Her Britannic Majesty's Government Of The United Kingdom Of Great Britain And Northern Ireland Gas gun for ballistic testing

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
WAFFENTECHNISCHES TASCHENBUCH, 3rd edition, 1977, pages 108-109, Rheinmetall GmbH, D}sseldorf, DE; *

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2013174821A1 (de) * 2012-05-24 2013-11-28 Rheinmetall Waffe Munition Gmbh WAFFENSYSTEM MIT EINER RÜCKSTOßFREIEN ODER RÜCKSTOßARMEN WAFFE UND EINER MIT DER WAFFE VERSCHIEßBAREN GRANATE

Also Published As

Publication number Publication date
GB2146416A (en) 1985-04-17
JPS6078299A (ja) 1985-05-02
GB8422596D0 (en) 1984-10-10

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PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

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Effective date: 19860220

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Inventor name: CAMPBELL, COLIN IAN

Inventor name: ALLEN, ROGER FREDERICK