EP0151676B1 - Projectile with payload section and propulsion section - Google Patents

Projectile with payload section and propulsion section Download PDF

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Publication number
EP0151676B1
EP0151676B1 EP84107615A EP84107615A EP0151676B1 EP 0151676 B1 EP0151676 B1 EP 0151676B1 EP 84107615 A EP84107615 A EP 84107615A EP 84107615 A EP84107615 A EP 84107615A EP 0151676 B1 EP0151676 B1 EP 0151676B1
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EP
European Patent Office
Prior art keywords
projectile
propulsion
payload part
payload
barrel
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
EP84107615A
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German (de)
French (fr)
Other versions
EP0151676A3 (en
EP0151676A2 (en
Inventor
Werner Grosswendt
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.)
Rheinmetall Industrie AG
Original Assignee
Rheinmetall GmbH
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Filing date
Publication date
Application filed by Rheinmetall GmbH filed Critical Rheinmetall GmbH
Publication of EP0151676A2 publication Critical patent/EP0151676A2/en
Publication of EP0151676A3 publication Critical patent/EP0151676A3/en
Application granted granted Critical
Publication of EP0151676B1 publication Critical patent/EP0151676B1/en
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
    • F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles

Definitions

  • the invention relates to a projectile as defined in the preamble of claim 1.
  • shot projectiles From barrel weapons e.g. an artillery gun, shot projectiles have a limited range with an optimal pipe elevation, which is essentially limited by the initial speed and therefore ultimately by the energy content of the propellant charge.
  • the invention has for its object to provide a projectile of the type mentioned, which can be fired from imported weapons due to its short design, and especially in confined combat areas, such as. B. howitzer, can be used.
  • Fig. 1 shows a schematic representation of a projectile 10 consisting of a payload part 12 and a drive part 11 in the idle state or in the firing position.
  • the drive part 11 which is expediently a ramjet engine, coaxially surrounds the payload part 12 of the projectile 10. This results in a greatly shortened construction of the projectile 10, which enables the use of the projectile 10 in conventional weapon systems and in particular also in space-restricted combat areas, such as howitzer tanks.
  • the additional drive part 11 gives the projectile an additional drive after firing from a weapon barrel and thereby enables an increased range of the projectile. While conventional artillery shells can cover distances of up to 30 km, the range of a projectile can be increased by up to 50 km with an additional drive.
  • the projectile 10 is closed by means of a traction sheave 13, which transmits the pressure which develops on the projectile 10 in the weapon barrel during the propellant charge gases that are fired.
  • a bore 13 ' is arranged centrally axially in the traction sheave 13, through which propellant gases can penetrate into the rear region 11' of the drive part 11, which is sealed gas-tight to the front part of the projectile by a washer 20.
  • a lock prevents the payload part 12 of the projectile from moving under the pressure of the propellant gases which have penetrated through the opening 13 'in the traction sheave 13.
  • the inertial force of the payload part 12 can be used for this locking during the acceleration phase.
  • the bore 13 'in the traction sheave 13 and the volume of the chamber 11' of the drive part 11 are to be dimensioned such that the force exerted by the pressure of the inflowing propellant gases is less than the inertial force of the payload part 12 during the acceleration phase in the weapon barrel. Since no inertial forces act on the projectile after leaving the weapon barrel, the gases enclosed in the chamber 11 'can now push the payload part 12 forward and expel the traction sheave 13 unlocked by the displacement of the payload part 12 with a time delay to the left.
  • Fig. 2 shows the projectile 10 in flight position, which the projectile occupies after leaving the gun barrel.
  • the propellant gases have moved the payload part 12 of the projectile, which is telescopically displaceable in the drive part 11, so that the payload part 12 and the drive part 11 are now arranged one behind the other in the axial direction.
  • the drive part 11, which is designed as a ramjet engine, can now also function, which has an air inlet, which is designed as a ring diffuser 17, 19, and a nozzle 21 arranged at the rear.
  • the solid fuel 15 (FIG. 3) is applied in the form of a ring jacket on the inner wall of the tubular drive part 11.
  • the jacket of the solid fuel 15 is interrupted only by catwalks 14 arranged parallel to the axis, which are firmly connected to the drive part 11 and allow easy sliding of the payload part 12, which can be displaced telescopically into the flight position.
  • Fig. 3 which is a cross section shows by the drive part 11 of the projectile 10 along the line 3-3 of FIG. 2, four of these catwalks 14 are shown.
  • fewer can. e.g. B. three catwalks 14 or more catwalks may be provided.
  • the sealing disk 20 is ejected in the rear direction.
  • This sealing disk 20 (FIG. 1) is expediently removed by a pyrotechnic charge, not shown in the figure.
  • Fig. 4 shows a view of the floor 10 as viewed from 4-4 acc. Fig. 2 and shows the folding tail units 16, which were still in the firing position (Fig. 1) were placed on the jacket of the drive part 11 and only unfolded after the projectile 10 was fired.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)
  • Portable Nailing Machines And Staplers (AREA)
  • Plasma Technology (AREA)

Description

Die Erfindung bertrifft ein Geschoß, wie es im Oberbegriff des Anspruchs 1 definiert ist.The invention relates to a projectile as defined in the preamble of claim 1.

Aus Rohrwaffen z.B. einem Artilleriegeschütz, verschossene Geschosse haben bei optimaler Rohrerhöhung eine begrenzte Reichweite, die im wesentlichen durch die Anfangsgeschwindigkeit und daher letztlich durch den Energieinhalt der Treibladung begrenzt ist.From barrel weapons e.g. an artillery gun, shot projectiles have a limited range with an optimal pipe elevation, which is essentially limited by the initial speed and therefore ultimately by the energy content of the propellant charge.

Es ist bereits bekannt (DE-OS 31 48 407), die Reichweite eines derartigen Geschosses durch einen zusätzlichen Antrieb, beispielsweise ein Staustrahltriebwerk, zu vergrößern, das nach dem Abfeuern gezündet wird und dem Geschoß einen zusätzlichen Impuls verleiht. Das sich an den Nutzlastteil des Geschosses anschließende Staustrahltriebwerk vergrößert dessen Baulänge in nachteiliger Weise, so daß es in herkömmlichen Geschützen mit einem vorgegebenen Ladungsraum nicht ohne weiteres verwendbar ist. Auch wenn durch Modifikationen des Ladungsraums eine Verwendung derartiger Geschosse denkbar wäre, ist eine Handhabung derartiger überlanger Geschosse in Panzerhaubitzen wegen des dort vorhandenen geringen Raumangebots nahezu völlig ausgeschlossen.It is already known (DE-OS 31 48 407) to increase the range of such a projectile by an additional drive, for example a ramjet, which is ignited after firing and gives the projectile an additional impulse. The ramjet engine adjoining the payload part of the projectile increases its overall length in a disadvantageous manner, so that it is not readily usable in conventional guns with a given cargo space. Even if the use of such projectiles would be conceivable through modifications to the cargo space, handling of such excessively long projectiles in self-propelled howitzers is almost completely ruled out because of the limited space available there.

Aus der US-PS 2,989,922 sind bereits sogenannte luftatmende Geschosse mit einlaboriertem Treibsatz und verschiebbarem Nutzlastteil offenbart. Dabei erfolgt eine Verschiebung des eigentlichen Projektiles gegenüber dem restlichen Geschoß nur um eine relativ kurze Strecke und dient nur dazu, nach Art eines Ventiles den Luftweg zu öffnen. Die Brennkammer im Inneren des Geschosses ist im wesentlichen bereits vorhanden, bevor das Geschoß verschoben wird. Dadurch entsteht ein großer, für Festtreibstoffe nicht ausgenutzter Raum.From US Pat. No. 2,989,922, so-called air-breathing projectiles with an incorporated propellant charge and displaceable payload part have already been disclosed. The actual projectile is only shifted by a relatively short distance from the rest of the storey and only serves to open the airway in the manner of a valve. The combustion chamber inside the projectile is essentially already present before the projectile is moved. This creates a large space that is not used for solid fuels.

Der Erfindung liegt die Aufgabe zugrunde, ein Geschoß der eingangs genannten Art bereitzustellen, das infolge seiner kurzen Bauweise aus eingeführten Waffen zu verschießen ist, und das insbesondere auch in beengten Kampfräumen, wie z. B. Panzerhaubitzen, verwendbar ist.The invention has for its object to provide a projectile of the type mentioned, which can be fired from imported weapons due to its short design, and especially in confined combat areas, such as. B. howitzer, can be used.

Diese Aufgabe wird durch die im Patentanspruch 1 angegebene Erfindung gelöst.This object is achieved by the invention specified in claim 1.

Vorteilhafte Ausgestaltungen der Erfindung gehen aus den Unteransprüchen hervor.Advantageous embodiments of the invention emerge from the subclaims.

Die Erfindung wird nachfolgend unter Bezug auf die Zeichnung näber erläutert. Dabei zeigt.

  • Fig. 1: das Geschoß in Ruhelage bzw. Abschußposition;
  • Fig. 2: das Geschoß in Flugposition;
  • Fig. 3: einen Querschnitt durch den Antriebsteil des Geschosses entlang Linie 3-3 der Fig. 2;
  • Fig. 4: eine Vorderansicht des Geschosses aus Blickrichtung 4-4 der Fig. 2.
The invention is explained in more detail below with reference to the drawing. It shows.
  • Fig. 1: the projectile in the rest position or firing position;
  • Fig. 2: the projectile in flight position;
  • 3 shows a cross section through the drive part of the projectile along line 3-3 of FIG. 2;
  • 4: a front view of the projectile from viewing direction 4-4 of FIG. 2.

Fig. 1 zeigt in schematischer Darstellung ein aus einem Nutzlastteil 12 und einem Antriebsteil 11 bestehendes Geschoß 10 im Ruhezustand bzw. in Abschußposition. Dabei umgibt der Antriebsteil 11, bei dem es sich zweckmäßig um ein Staustrahltriebwerk handelt, den Nutzlastteil 12 des Geschosses 10 koaxial. Auf diese Weise ergibt sich eine stark verkürzte Bauweise des Geschosses 10, die die Verwendung des Geschosses 10 bei herkömmlichen Waffenanlagen und insbesondere auch in räumlich beengten Kampfräumen, wie in Panzerhaubitzen, ermöglicht. Das zusätzliche Antriebsteil 11 verleiht dem Geschoß nach dem Abfeuern aus einem Waffenrohr einen Zusatzantrieb und ermöglicht dadurch eine vergrößerte Reichweite des Geschosses. Während herkömmliche Artilleriegeschosse Entfernungen bis zu etwa 30 km überbrücken können, läßt sich die Reichweite eines Geschosses mit einem Zusatzantrieb etwa bis auf 50 km steigern.Fig. 1 shows a schematic representation of a projectile 10 consisting of a payload part 12 and a drive part 11 in the idle state or in the firing position. The drive part 11, which is expediently a ramjet engine, coaxially surrounds the payload part 12 of the projectile 10. This results in a greatly shortened construction of the projectile 10, which enables the use of the projectile 10 in conventional weapon systems and in particular also in space-restricted combat areas, such as howitzer tanks. The additional drive part 11 gives the projectile an additional drive after firing from a weapon barrel and thereby enables an increased range of the projectile. While conventional artillery shells can cover distances of up to 30 km, the range of a projectile can be increased by up to 50 km with an additional drive.

Heckseitig ist das Geschoß 10 mittels einer Treibscheibe 13 verschlossen, die den Druck, der sich im Waffenrohr beim Abschuß entwickelnden Treibladungsgase auf das Geschoß 10 überträgt. Zentralaxial in der Treibscheibe 13 ist eine Bohrung 13' angeordnet, durch die Treibladungsgase in den heckseitigen Bereich 11' des Anteriebsteils 11 eindringen können, der zum Vorderteil des Geschosses hin durch eine Scheibe 20 gas dicht abgedichtet ist. Eine Verriegelung verhindert dabei, daß unter dem Druck der Treibladungsgase, die durch die Öffnung 13' in der Treibscheibe 13 eingedrungen sind, sich der Nutzlastteil 12 des Geschosses nach vorn bewegt. Auf sehr einfache und zweckmäßige Weise kann für diese Verriegelung die Trägheitskraft des Nutzlastteile 12 während der Beschleunigungsphase herangezogen werden. Dazu sind die Bohrung 13' in der Treibscheibe 13 sowie das Volumen der Kammer 11' des Antriebsteils 11 so zu dimensionieren, daß die durch den Druck der eingeströmten Treibladungsgase ausgeübte Kraftwirkung geringer ist, als die Trägheitskraft des Nutzlastteils 12 während der Beschleunigungsphase im Waffenrohr. Da nach dem Verlassen des Waffenrohrs keine Trägheitskräfte mehr auf das Geschoß wirken, können nun die in die Kammer 11' eingeschlossenen Gase den Nutzlastteil 12 nach vorne schieben und die durch die Verlagerung des Nutzlastteils 12 entriegelte Treibscheibe 13 mit zeitlicher Verzögerung nach binten ausstoßen.On the rear side, the projectile 10 is closed by means of a traction sheave 13, which transmits the pressure which develops on the projectile 10 in the weapon barrel during the propellant charge gases that are fired. A bore 13 'is arranged centrally axially in the traction sheave 13, through which propellant gases can penetrate into the rear region 11' of the drive part 11, which is sealed gas-tight to the front part of the projectile by a washer 20. A lock prevents the payload part 12 of the projectile from moving under the pressure of the propellant gases which have penetrated through the opening 13 'in the traction sheave 13. In a very simple and expedient manner, the inertial force of the payload part 12 can be used for this locking during the acceleration phase. For this purpose, the bore 13 'in the traction sheave 13 and the volume of the chamber 11' of the drive part 11 are to be dimensioned such that the force exerted by the pressure of the inflowing propellant gases is less than the inertial force of the payload part 12 during the acceleration phase in the weapon barrel. Since no inertial forces act on the projectile after leaving the weapon barrel, the gases enclosed in the chamber 11 'can now push the payload part 12 forward and expel the traction sheave 13 unlocked by the displacement of the payload part 12 with a time delay to the left.

Fig. 2 zeigt das Geschoß 10 in Flugposition, die das Geschoß nach dem Verlassen des Waffenrohrs einnimmt.Fig. 2 shows the projectile 10 in flight position, which the projectile occupies after leaving the gun barrel.

Die Treibladungsgase haben den teleskopartig im Antriebsteil 11 verschiebbar gelagerten Nutzlastteil 12 des Geschosses nach vorn bewegt, so daß nunmehr Nutzlastteil 12 und Antriebsteil 11 in Axialrichtung hintereinander angeordnet sind. Nun kann auch der als Staustrahltriebwerk ausgebildete Antriebsteil 11 in Funktion treten, der über einen als Ringdiffusor 17, 19 ausgebildeten Lufteinlauf und eine heckseitig angeordnete Düse 21 verfügt. Der Festtreibstoff 15 (Fig. 3) ist ringmantelförmig auf der Innenwandung des rohrförmig ausgebildeten Antriebsteils 11 aufgebracht. Der Mantel des Festtreibstoffs 15 ist lediglich durch achsaparallel angeordnete Laufstege 14 unterbrochen, die mit dem Antriebsteil 11 fest verbunden sind und ein leichtes Gleiten des teleskopartig in die Flugposition verschiebbaren Nutzlastteils 12 ermöglichen. In Fig. 3, die einen Querschnitt durch den Antriebsteil 11 des Geschosses 10 entlang der Linie 3-3 nach Fig. 2 zeigt, sind vier dieser Laufstege 14 dargestellt. Je nach den Erfordernissen können auch weniger. z. B. drei Laufstege 14 oder mehr Laufstege vorgesehen werden.The propellant gases have moved the payload part 12 of the projectile, which is telescopically displaceable in the drive part 11, so that the payload part 12 and the drive part 11 are now arranged one behind the other in the axial direction. The drive part 11, which is designed as a ramjet engine, can now also function, which has an air inlet, which is designed as a ring diffuser 17, 19, and a nozzle 21 arranged at the rear. The solid fuel 15 (FIG. 3) is applied in the form of a ring jacket on the inner wall of the tubular drive part 11. The jacket of the solid fuel 15 is interrupted only by catwalks 14 arranged parallel to the axis, which are firmly connected to the drive part 11 and allow easy sliding of the payload part 12, which can be displaced telescopically into the flight position. In Fig. 3, which is a cross section shows by the drive part 11 of the projectile 10 along the line 3-3 of FIG. 2, four of these catwalks 14 are shown. Depending on the requirements, fewer can. e.g. B. three catwalks 14 or more catwalks may be provided.

Nach dem Vorgleiten des Nutzlastteils 12, zweckmäßig mit dem Lösen der Verriegelungsmittel synchronisiert, wird die Dichtscheibe 20 in Heckrichtung ausgestoßen. Das Ablösen dieser Dichtscheibe 20 (Fig. 1) erfolgt zweckmäßig durch eine in der Figur nicht dargestellte pyrotechnische Ladung.After the payload part 12 slides forward, advantageously synchronized with the release of the locking means, the sealing disk 20 is ejected in the rear direction. This sealing disk 20 (FIG. 1) is expediently removed by a pyrotechnic charge, not shown in the figure.

Fig. 4 zeigt eine Ansicht des Geschosses 10 mit Blickrichtung aus 4-4 gem. Fig. 2 und läßt die Klappleitwerke 16 erkennen, die in Abschußposition (Fig. 1) noch an den Mantel des Antriebsteils 11 angelegt waren und sich erst nach dem Abschuß des Geschosses 10 entfaltet haben.Fig. 4 shows a view of the floor 10 as viewed from 4-4 acc. Fig. 2 and shows the folding tail units 16, which were still in the firing position (Fig. 1) were placed on the jacket of the drive part 11 and only unfolded after the projectile 10 was fired.

Claims (2)

1. Projectile with a propulsion part (11) which coaxially surrounds a payload part (12) and in which the payload part (12) is mounted in such a way as to be telescopically displaceable, the propulsion part (11) of the projectile (10) being constructed as a ram jet power unit with an annular diffuser (17, 19), solid fuel being present in the form of an annular casing on the inner wall of the central combustion chamber (11) which is of tubular construction, when the payload part (12) occupies the extended forward position the air duct through the propulsion part (11) is open, whereas the duct is closed when the payload part occupies the rearward position, that is when the projectile is located in the barrel of the weapon, and remains in the closed position until the projectile (10) has left the said barrel, characterised by the following features:
(a) the payload part (12), when in the rearward position, is retracted over almost the entire length thereof into the propulsion part (11), the solid fuel (15) surrounding the payload part (12) substantially without a gap;
(b) a pressure chamber (11') is formed in the rear zone of the propulsion part (11) and is closed by a propulsion disc (13) with a central axial boring (13'), the propulsion disc (13) being detachable after the payload part has been thrust forward into the forward position;
(c) the size of the aperture provided by the boring (13') in the propulsion disc (13) and also the volume of the pressure chamber (11') in the propulsion part (11) behind the payload part (12) in the rearward position being selected to ensure that the force exerted by the propulsion charge gases flowing through the boring (13') into the pressure chamber (11') - as long as the projectile (10) is still in the barrel - is less than the inertia force of the payload part (12) during the acceleration phase in the barrel.
2. Projectile in accordance with Claim 1, characterised by the fact that a number of runner rails (14) are provided paraxially inside the solid fuel (15).
EP84107615A 1983-08-03 1984-06-30 Projectile with payload section and propulsion section Expired - Lifetime EP0151676B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3327945 1983-08-03
DE19833327945 DE3327945A1 (en) 1983-08-03 1983-08-03 BULLET WITH A PAYLOAD PART AND A DRIVE PART

Publications (3)

Publication Number Publication Date
EP0151676A2 EP0151676A2 (en) 1985-08-21
EP0151676A3 EP0151676A3 (en) 1988-03-02
EP0151676B1 true EP0151676B1 (en) 1990-06-13

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Family Applications (1)

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EP84107615A Expired - Lifetime EP0151676B1 (en) 1983-08-03 1984-06-30 Projectile with payload section and propulsion section

Country Status (2)

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EP (1) EP0151676B1 (en)
DE (2) DE3327945A1 (en)

Cited By (1)

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Publication number Priority date Publication date Assignee Title
WO2023137255A1 (en) * 2022-01-11 2023-07-20 Raytheon Company Effector having morphing airframe and method

Families Citing this family (11)

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Publication number Priority date Publication date Assignee Title
DE3344402A1 (en) * 1983-12-08 1985-06-13 Diehl GmbH & Co, 8500 Nürnberg Missile
NO308717B1 (en) * 1999-06-04 2000-10-16 Nammo Raufoss As Propulsion device for a projectile in a missile
NO308715B1 (en) * 1999-06-04 2000-10-16 Nammo Raufoss As Missile release mechanism
NO995141A (en) 1999-06-04 2000-10-16 Nammo Raufoss As Missile feed and locking mechanism
US6598535B1 (en) * 2001-12-31 2003-07-29 The United States Of America As Represented By The Secretary Of The Army Collapsible support frame for kinetic energy penetrator
DE102006014729B3 (en) * 2006-03-30 2007-11-29 Diehl Bgt Defence Gmbh & Co. Kg Steerable projectile for average caliber ammunition comprises a drive based on a gel, an annular nozzle with a receiver for steering information and a cross-shift control unit with an energy supply from the stream of a diffuser
DE102007034546A1 (en) 2007-07-20 2009-01-22 Rheinmetall Waffe Munition Gmbh Target marking ammunition
US9823053B1 (en) * 2016-08-29 2017-11-21 The Boeing Company Solid-fuel ramjet ammunition
FR3080912B1 (en) 2018-05-02 2020-04-03 Nexter Munitions PROJECTILE POWERED BY STATOREACTOR
US11796291B2 (en) * 2022-01-11 2023-10-24 Raytheon Company Effector having morphing airframe and method
US11781842B1 (en) * 2022-03-28 2023-10-10 Raytheon Company Extended range projectile and method for propelling an extended range projectile

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US2989922A (en) * 1953-02-17 1961-06-27 Marvin H Greenwood Ramjet propulsion device

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US3677179A (en) * 1966-09-29 1972-07-18 Lester A Potteiger Telescoping ordnance device
FR2146552A5 (en) * 1971-07-19 1973-03-02 France Etat
CH610650A5 (en) * 1974-10-29 1979-04-30 Doetsch Hans Peter Self-propelled projectile
GB2089009A (en) * 1980-12-08 1982-06-16 United Technologies Corp Blast Equalizer for a Gun fired Ramjet Projectile

Patent Citations (1)

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Publication number Priority date Publication date Assignee Title
US2989922A (en) * 1953-02-17 1961-06-27 Marvin H Greenwood Ramjet propulsion device

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2023137255A1 (en) * 2022-01-11 2023-07-20 Raytheon Company Effector having morphing airframe and method

Also Published As

Publication number Publication date
DE3327945A1 (en) 1985-02-21
DE3482490D1 (en) 1990-07-19
EP0151676A3 (en) 1988-03-02
EP0151676A2 (en) 1985-08-21

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