EP0961096B1 - Mündungsbremse am Rohrlauf einer Rohrwaffe, insbesondere an einer Kanone von einem Luftfahrzeug - Google Patents

Mündungsbremse am Rohrlauf einer Rohrwaffe, insbesondere an einer Kanone von einem Luftfahrzeug Download PDF

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Publication number
EP0961096B1
EP0961096B1 EP99110205A EP99110205A EP0961096B1 EP 0961096 B1 EP0961096 B1 EP 0961096B1 EP 99110205 A EP99110205 A EP 99110205A EP 99110205 A EP99110205 A EP 99110205A EP 0961096 B1 EP0961096 B1 EP 0961096B1
Authority
EP
European Patent Office
Prior art keywords
bottle
space
opening
tube
muzzle
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 - Lifetime
Application number
EP99110205A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0961096A3 (de
EP0961096A2 (de
Inventor
Hartmut Gehse
Gerhard Wedekind
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.)
Airbus Defence and Space GmbH
Original Assignee
EADS Deutschland GmbH
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Filing date
Publication date
Application filed by EADS Deutschland GmbH filed Critical EADS Deutschland GmbH
Publication of EP0961096A2 publication Critical patent/EP0961096A2/de
Publication of EP0961096A3 publication Critical patent/EP0961096A3/de
Application granted granted Critical
Publication of EP0961096B1 publication Critical patent/EP0961096B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F41A21/00—Barrels; Gun tubes; Muzzle attachments; Barrel mounting means
    • F41A21/32—Muzzle attachments or glands
    • F41A21/36—Muzzle attachments or glands for recoil reduction ; Stabilisators; Compensators, e.g. for muzzle climb prevention

Definitions

  • the invention relates to a device on the barrel of a barrel weapon, in particular on a cannon of an aircraft, containing one on the muzzle side End of the pipe run by means of holding means arranged cladding tube that the recording serves a shock wave at the mouth of the pipe run, the cladding tube has rear opening and subsequently has a front opening in the weft direction, through which a shot projectile leaves the cladding tube.
  • the cannon barrel is surrounded by a bottle in its end region, so that there is a space between the cannon barrel and the bottle.
  • the bottle At its front end, the bottle has a muzzle brake of known design with an opening for passing through the projectile that has been fired and means (blades) for deflecting the shot gases against the shot direction.
  • the rear end of the bottle At the rear end of the bottle there is another opening for discharging the shot gases.
  • only part of the shock wave is detected. The size of the detected part of the shock wave depends on the dimensioning of the muzzle brake. This proportion is extremely limited by the relatively narrow passage openings.
  • the detected part of the shock wave is deflected into the bottle by deflecting means, ie directed into the rear space of the bottle against the direction of the shot and escapes there after only one pass through the rear opening of the bottle.
  • a significant proportion of the shock wave leaves the gun barrel through the front muzzle and continues to cause undesirable dynamic loads on the structure of the aircraft.
  • the object of the invention is, preferably in aircraft, to significantly reduce the shock wave loading and the weapon recoil force of the tube weapon compared to the structure or the equipment of the aircraft.
  • the object is achieved in accordance with the characterizing features of claim 1.
  • the bottle space enclosed by the bottle is essentially arranged downstream of the mouth of the pipe run.
  • the bottle is placed on the mouth of the pipe run in the shot direction with its rear opening.
  • the rear opening and front opening of the bottle thus lie in the weft direction, ie on the weft axis.
  • a holding means which encompasses the pipe run, carries the bottle and positively positions the rear opening of the bottle at the mouth of the pipe run.
  • the loads that result from the shock reflection at the front end of the bottle are transmitted to the bottle holder via the wall of the bottle and not via internal webs, as in the case of the muzzle brake according to DE 39 40 807 A1. This enables maximum expansion of the main joint from the pipe mouth.
  • the bottle With its front opening, the bottle carries a butt splitter tube which is also positioned in the weft direction and which projects into the bottle space with its inner opening. Internal opening means that this opening of the butt splitter tube is arranged within the bottle space. With its inner opening, the butt splitter tube divides the bottle space into two rooms (chambers), an expansion space that is arranged between the inner opening of the butt splitter tube and the mouth of the pipe run, and a sack space that corresponds to a subsequent space corresponding to the length of the butt splitter tube in the bottle space.
  • the free passage into the expansion space has the advantage that the gas (shock wave) emerging from the pipe run can expand explosively into a relatively large space (the expansion space). There is no obstruction due to narrow inflow slots or immediate forced deflection by deflecting means.
  • the expansion space could also extend slightly beyond the mouth of the pipe run in the opposite direction of the shot in order to be able to influence the time of a second reflection.
  • the gas expands further into the sack space, separated from the smallest possible proportion of the gas which exits directly through the inner opening of the butt splitter tube.
  • the bag space has a relatively large entry opening.
  • the shape of the bag space can certainly be slimmer towards the front, whereby its effective length is shortened somewhat (the incoming impact is focused), but the effectiveness would hardly be impaired.
  • the opening of the butt splitter tube should be as small as possible, so that freedom of movement for the floor is guaranteed.
  • Freedom of movement means that the projectile can just pass the butt splitter tube without jamming between the projectile and butt splitter tube. This influences the strength of the first impact at the outer opening (opening located outside the bottle space) of the impact divider tube and thus reduces stress on the structure of the aircraft. If necessary, the diameter of the butt splitter tube could widen in the direction of the outer opening in order to allow freedom of movement for a swinging projectile.
  • both the weapon recoil and the Shock wave is significantly reduced compared to the prior art.
  • the impulse when the shock wave is reflected at the end of the bag space one causes the Recoil of the projectile opposing force, the greater the better parts of the main joint can be diverted from the pipe mouth into the sack space.
  • the recoil "smears" itself towards a more even load rather than a shock, which is the sound exposure significantly reduced to the structure of the aircraft.
  • the diameter and depth of the expansion space have an influence on the position of a focus area, which results after the reflected first impact on the wall of the expansion space.
  • the position of this focus area is optimal if it lies on or in the direction of the shot downstream of the inner opening of the butt splitter tube.
  • the diameter and in particular the length of the bag space determine the point in time at which the shock wave reflected in this space again reaches the inner opening of the bumper divider tube.
  • the diameter of the bottle is usually limited by the aircraft structure.
  • both the diameter and the depth of the expansion space are determined by the structure of the aircraft, in a further embodiment of the invention there is the possibility of making the length of the butt splitter tube protruding into the bottle so that the fixed focus is positioned on the wall of the butt splitter tube.
  • the diameter of the inner opening corresponds precisely to the freedom of movement of a projectile.
  • the included from the bottle 4 bottle space is arranged downstream of the mouth of H 2 of a tubular barrel 1 in the weft direction S R substantially.
  • This bottle space H enables the energy of the gas from the pipe run 1, which is produced when a projectile is fired, to be stored temporarily. By temporarily storing the energy of the gas, it cannot be released suddenly.
  • the bottle 4 has a rear opening 4.2 and a front opening 4.1.
  • the bottle 4 is positively placed with the rear opening 4.2 of the mouth 2 of the pipe run 1.
  • a holding means 3, which includes the pipe run 1 at the mouth, carries the bottle 4.
  • the front opening 4.1 of the bottle 4 has a butt splitter tube 5 positioned in the weft direction S R by means of the carrier 7.
  • the butt splitter tube 5 projects with its inner opening 5.1 into the bottle space H.
  • the outer opening 5.2 of the butt splitter tube also forms the mouth of the bottle 4.
  • the inner opening 5.1 of the butt splitter tube 5 divides the bottle space H into two spaces (2 chambers), the expansion space A. and the bag room B.
  • the expansion room A is characterized by the diameter d and the depth T.
  • the bag room is a so-called "dead" room that has no exit.
  • the bag space B extends from the expansion space to the front wall of the bottle 4.
  • the front wall of the bottle 4 can also be designed as a deflection means 6.
  • the gas emerging from the pipe run 1 can expand explosively.
  • the gas continues to expand, separated from the portion of the gas which emerges directly through the butt splitter tube 5.
  • the butt splitter tube 5 should have the smallest possible diameter, which just guarantees freedom of movement for the projectile. If necessary, the butt splitter tube can widen in the direction of the outer opening to allow freedom of movement for a swinging projectile. As can be seen in FIG. 2a , this impact can expand into the bag space B in its "natural" running direction (corresponds to the weft direction) with the largest possible "entry opening". Only a small part of the first impact is released to the environment through the impact divider tube 5.
  • the impact speed in the bottle space H can be in the range from 500 to 1000 m / s.
  • the time to build up the impact maximum in front of the outer opening 5.2 of the impact divider tube 5 in the area of the aircraft structure is approximately 0.5 ms.
  • An average surge pressure ratio ⁇ 50 at the mouth 2 of the pipe run 1 is assumed. Under these boundary conditions, for example, the impact caused by the gas emerging from the mouth 2 reaches the inner opening 5.1 of the impact divider tube 5 after 0.1 ms.
  • the impact has strong expansion areas on the side ("effective" angle of the outflow cone ⁇ 30 to 45 degrees), so that a noticeable impact reflection occurs first in the area A 'in FIG. 2 on the wall of the expansion space A.
  • This reflected impact first reaches the area of the shot axis in the focus area F, which is located at or downstream of the inner opening 5.1 of the impact splitter tube 5 and thus determines the depth (T) of the expansion space A.
  • the floor should be in the area of the inner opening 5.1 at this time.
  • the impact in bag space B reaches its front wall and is reflected. In the meantime the time reaches about 0.3 ms.
  • the gas between the front wall and the reflected impact is brought to a standstill and reaches very high pressures and temperatures.
  • the time for the back and forth movement of the impact in the bag space B should be such that the reflected impact reaches the inner opening 5.1 of the impact divider tube 5 long before the flow from the mouth 2 is fully developed, ie long before the otherwise usual maximum of the shock pulse.
  • This time should be, for example, 0.25 to 0.3 ms.
  • This time period determines the length of the bag room B. Accordingly, the length of the bag room B will be, for example, 0.1 to 0.2 m.
  • the projectile was still in the butt splitter tube 5.
  • the reflected impact in the bag space B reaches the inner opening 5.1 of the impact divider tube 5. The flow in the entire bag space B is brought to a standstill.
  • Impulse i 1 from FIG. 6 schematically shows the impact without a device at the mouth of the pipe run.
  • a relatively large maximum M of the impact is reached very quickly after a time t M , in order then to drop steeply in a rear flank R.
  • This process takes about 1 ms.
  • the pulse i 2 shock wave
  • the pulse i 2 shock wave to be registered at the outer opening 5.2 of the flow divider tube - as shown in FIG. 7 - is significantly reduced in its height and time-stretched, as the schematic representation further shows. This form of impulse does not converge again until a very great distance.
  • This strong reduction of the shock by means of the device according to the invention is essentially due to the fact that it was possible to use the reflected shock in order to influence the first shock that is still building up (rising edge of the pulse) in such a way that the maximum M cannot form , but is stalled and the pulse i 2 is delayed (smeared) in the direction of a longer but significantly lower pulse height.
  • the geometry of the bottle space helps to ensure that the flow is stalled before the end face of the joint can fully build up. This significantly reduces vibrations.
  • the invention can also be used with other known firearms.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)
  • Vibration Dampers (AREA)
  • Vending Machines For Individual Products (AREA)
EP99110205A 1998-05-29 1999-05-26 Mündungsbremse am Rohrlauf einer Rohrwaffe, insbesondere an einer Kanone von einem Luftfahrzeug Expired - Lifetime EP0961096B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19824010A DE19824010A1 (de) 1998-05-29 1998-05-29 Einrichtung am Rohrlauf einer Rohrwaffe, insbesondere an einer Kanone von einem Luftfahrzeug
DE19824010 1998-05-29

Publications (3)

Publication Number Publication Date
EP0961096A2 EP0961096A2 (de) 1999-12-01
EP0961096A3 EP0961096A3 (de) 2001-02-21
EP0961096B1 true EP0961096B1 (de) 2003-09-24

Family

ID=7869267

Family Applications (1)

Application Number Title Priority Date Filing Date
EP99110205A Expired - Lifetime EP0961096B1 (de) 1998-05-29 1999-05-26 Mündungsbremse am Rohrlauf einer Rohrwaffe, insbesondere an einer Kanone von einem Luftfahrzeug

Country Status (3)

Country Link
EP (1) EP0961096B1 (es)
DE (2) DE19824010A1 (es)
ES (1) ES2202963T3 (es)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ES1065590Y (es) * 2007-01-12 2008-01-01 Gamo Ind Sa Arma de fuego o deportiva con silenciador
ES2435495B1 (es) 2012-01-13 2014-10-23 Gamo Outdoor, S.L. Procedimiento para la fabricación de un cañón para carabinas de aire comprimido o CO2 y cañón para carabinas de aire comprimido o CO2 obtenido.

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NL31599B (es) * 1925-10-21 1900-01-01
US2150161A (en) * 1936-10-16 1939-03-14 Samuel G Green Muzzle attachment for guns
US2402632A (en) * 1942-02-07 1946-06-25 Ivanovic Nicholas Blast deflector and gun installation
GB683923A (en) * 1950-08-01 1952-12-10 Alexander John Ingram Improvements in recoil-reducing devices for firearms
US2859663A (en) * 1955-02-28 1958-11-11 Canadair Ltd Gun blast deflector
DE1922117A1 (de) * 1969-04-30 1970-11-05 Eta Corp Rohrfeuerwaffe,insbesondere Hochleistungskanone
DE3940807A1 (de) * 1989-12-09 1991-06-13 Dornier Luftfahrt Schutzvorrichtung gegen muendungsfeuereffekte bei rohrwaffen

Also Published As

Publication number Publication date
EP0961096A3 (de) 2001-02-21
DE19824010A1 (de) 1999-12-02
EP0961096A2 (de) 1999-12-01
DE59907083D1 (de) 2003-10-30
ES2202963T3 (es) 2004-04-01

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