EP0151676A2 - Projectile with payload section and propulsion section - Google Patents

Projectile with payload section and propulsion section Download PDF

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Publication number
EP0151676A2
EP0151676A2 EP84107615A EP84107615A EP0151676A2 EP 0151676 A2 EP0151676 A2 EP 0151676A2 EP 84107615 A EP84107615 A EP 84107615A EP 84107615 A EP84107615 A EP 84107615A EP 0151676 A2 EP0151676 A2 EP 0151676A2
Authority
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.)
Granted
Application number
EP84107615A
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German (de)
French (fr)
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EP0151676A3 (en
EP0151676B1 (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
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Rheinmetall GmbH
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Filing date
Publication date
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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 with a payload part and a drive part.
  • missile projectiles have a limited range with 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 in particular 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-tight 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 Storey. While conventional artillery projectiles 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 launched.
  • a bore 13 ′ is arranged centrally axially in the traction sheave 13, through which propellant gases can penetrate into the rear area of the drive part 11, which is sealed off from 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 3 '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 eject the traction sheave 13 unlocked by the displacement of the payload part 12 with a time delay to the rear.
  • 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 14 which is designed as a ramjet engine, can also come into operation, which has an air inlet 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 14.
  • 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 enable the payload part 12, which can be telescopically displaced into the flight position, to slide easily.
  • less, e.g. B. three catwalks 14 or more catwalks may be provided.
  • the sealing disk 20 Before the payload part 12 slides forward, appropriately 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 shows a view of the projectile 10 as viewed from 4 to 4 according to FIG. 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.

Abstract

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.

Description

Die Erfindung betrifft ein Geschoß mit einem Nutzlastteil und einem Antriebsteil.The invention relates to a projectile with a payload part and a drive part.

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 guns, e.g. B. an artillery gun, missile projectiles have a limited range with 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 cannot readily be used 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.

Der Erfindung liegt die Aufgabe zugrunde, ein Geschoß der eingangs genannten Art bereitzustellen, das infolge seiner kurzen Bauweise aus eingeführten Waffen zu verschie- ßen 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 in particular 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 näher 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-tight 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 Storey. While conventional artillery projectiles 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 des Anteriebsteils 11 eindringen können, der zum Vorderteil des Geschosses hin durch eine Scheibe 20 abgedichtet ist. Eine Verriegelung verhindert dabei, daß unter dem Druck der Treibladungsgase, die durch die Öffnung 3' 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 hinten 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 launched. A bore 13 ′ is arranged centrally axially in the traction sheave 13, through which propellant gases can penetrate into the rear area of the drive part 11, which is sealed off from 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 3 '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 eject the traction sheave 13 unlocked by the displacement of the payload part 12 with a time delay to the rear.

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 14 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 14 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. Now the drive part 14, which is designed as a ramjet engine, can also come into operation, which has an air inlet 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 14. 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 enable the payload part 12, which can be telescopically displaced into the flight position, to slide easily. 3, which shows a cross section through the drive part 11 of the projectile 10 along the line 3 - 3 according to FIG. 2, four of these catwalks 14 are shown. Depending on the requirements, less, e.g. B. three catwalks 14 or more catwalks may be provided.

Noch vor 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.Before the payload part 12 slides forward, appropriately 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 projectile 10 as viewed from 4 to 4 according to FIG. 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 (6)

1. Geschoß mit Nutzlastteil und einem Antriebsteil, dadurch gekennzeichnet, daß das Antriebsteil (11) das Nutzlastteil (12) koaxial umgibt und daß das Nutzlastteil (12) teleskopartig verschiebbar im Antriebsteil (11) gelagert ist.1. projectile with payload part and a drive part, characterized in that the drive part (11) surrounds the payload part (12) coaxially and that the payload part (12) is telescopically mounted in the drive part (11). 2. Geschoß nach Anspruch 1, dadurch gekennzeichnet, daß das Antriebsteil (11) waffenseitig durch eine Treibscheibe (13) mit einer zentralaxialen Bohrung (13') abgeschlossen ist.2. Projectile according to claim 1, characterized in that the drive part (11) is completed on the weapon side by a traction sheave (13) with a central axial bore (13 '). 3. Geschoß nach einem der Ansprüche 1 und 2, dadurch gekennzeichnet, daß ein heckseitiger Bereich (11') des Antriebsteils (11) durch eine Dichtscheibe (20) gasdicht abgeschlossen ist.3. Projectile according to one of claims 1 and 2, characterized in that a rear region (11 ') of the drive part (11) is sealed gas-tight by a sealing washer (20). 4. Geschoß nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, daß das Antriebsteil (11) des Geschosses (10) als Staustrahltriebwerk mit einem Ringdiffusor (17, 19) , einer Düse (21) und einem zentral angeordneten Verbrennungsraum (11") ausgebildet ist.4. Projectile according to one of claims 1 to 3, characterized in that the drive part (11) of the projectile (10) as a ramjet with an annular diffuser (17, 19), a nozzle (21) and one centrally arranged combustion chamber (11 ") is formed. 5. Geschoß nach einem der Ansprüche 1 bis 4, gekennzeichnet, daß für den Betrieb des Antriebsteils (11) ein Festtreibstoff (15) vorgesehen ist, der ringmantelförmig auf der Innenwand der rohrförmig ausgebildeten zentralen Brennkammer (11") angeordnet ist.5. Projectile according to one of claims 1 to 4, characterized in that a solid fuel (15) is provided for the operation of the drive part (11), which is arranged in the form of an annular jacket on the inner wall of the tubular central combustion chamber (11 "). 6. Geschoß nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, daß innerhalb des Festtreibstoffs (15) achsparallel verlaufend eine Mehrzahl von Laufstegen 14 angeordnet ist.6. Projectile according to one of claims 1 to 5, characterized in that a plurality of catwalks 14 is arranged within the solid propellant (15) axially parallel.
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 true EP0151676A2 (en) 1985-08-21
EP0151676A3 EP0151676A3 (en) 1988-03-02
EP0151676B1 EP0151676B1 (en) 1990-06-13

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

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DE (2) DE3327945A1 (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2000075600A1 (en) * 1999-06-04 2000-12-14 Nammo Raufoss As Translation and locking mechanism in missile
WO2000075599A1 (en) * 1999-06-04 2000-12-14 Nammo Raufoss As Propelling device for a projectile in a missile
WO2000075601A1 (en) * 1999-06-04 2000-12-14 Nammo Raufoss As Release mechanism in missile
US9823053B1 (en) * 2016-08-29 2017-11-21 The Boeing Company Solid-fuel ramjet ammunition
WO2023192694A1 (en) * 2022-03-28 2023-10-05 Raytheon Company Extended range projectile and method for propelling an extended range projectile

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3344402A1 (en) * 1983-12-08 1985-06-13 Diehl GmbH & Co, 8500 Nürnberg Missile
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
FR3080912B1 (en) * 2018-05-02 2020-04-03 Nexter Munitions PROJECTILE POWERED BY STATOREACTOR
WO2023137255A1 (en) * 2022-01-11 2023-07-20 Raytheon Company Effector having morphing airframe and method
US11796291B2 (en) * 2022-01-11 2023-10-24 Raytheon Company Effector having morphing airframe and method

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2989922A (en) * 1953-02-17 1961-06-27 Marvin H Greenwood Ramjet propulsion device
US3677179A (en) * 1966-09-29 1972-07-18 Lester A Potteiger Telescoping ordnance device
DE2234302B2 (en) * 1971-07-19 1977-03-03 Societe Nationale Des Poudres Et Explosifs, Paris ROCKET
CH610650A5 (en) * 1974-10-29 1979-04-30 Doetsch Hans Peter Self-propelled projectile
DE3148407A1 (en) * 1980-12-08 1982-08-26 United Technologies Corp., 06101 Hartford, Conn. BULLET

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2989922A (en) * 1953-02-17 1961-06-27 Marvin H Greenwood Ramjet propulsion device
US3677179A (en) * 1966-09-29 1972-07-18 Lester A Potteiger Telescoping ordnance device
DE2234302B2 (en) * 1971-07-19 1977-03-03 Societe Nationale Des Poudres Et Explosifs, Paris ROCKET
CH610650A5 (en) * 1974-10-29 1979-04-30 Doetsch Hans Peter Self-propelled projectile
DE3148407A1 (en) * 1980-12-08 1982-08-26 United Technologies Corp., 06101 Hartford, Conn. BULLET

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2000075600A1 (en) * 1999-06-04 2000-12-14 Nammo Raufoss As Translation and locking mechanism in missile
WO2000075599A1 (en) * 1999-06-04 2000-12-14 Nammo Raufoss As Propelling device for a projectile in a missile
WO2000075601A1 (en) * 1999-06-04 2000-12-14 Nammo Raufoss As Release mechanism in missile
US6640720B1 (en) 1999-06-04 2003-11-04 Nammo Raufoss As Translation and locking mechanism in missile
US6928931B1 (en) 1999-06-04 2005-08-16 Nammo Raufoss As Release mechanism in missile
US9823053B1 (en) * 2016-08-29 2017-11-21 The Boeing Company Solid-fuel ramjet ammunition
WO2023192694A1 (en) * 2022-03-28 2023-10-05 Raytheon Company Extended range projectile and method for propelling an extended range projectile
US11781842B1 (en) 2022-03-28 2023-10-10 Raytheon Company Extended range projectile and method for propelling an extended range projectile

Also Published As

Publication number Publication date
DE3482490D1 (en) 1990-07-19
EP0151676A3 (en) 1988-03-02
DE3327945A1 (en) 1985-02-21
EP0151676B1 (en) 1990-06-13

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