EP0151676A2 - Projectile comprenant une partie propulsion et une partie charge utile - Google Patents

Projectile comprenant une partie propulsion et une partie charge utile 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
Other languages
German (de)
English (en)
Other versions
EP0151676A3 (en
EP0151676B1 (fr
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
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 Rheinmetall GmbH filed Critical Rheinmetall GmbH
Publication of EP0151676A2 publication Critical patent/EP0151676A2/fr
Publication of EP0151676A3 publication Critical patent/EP0151676A3/de
Application granted granted Critical
Publication of EP0151676B1 publication Critical patent/EP0151676B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42AMMUNITION; BLASTING
    • F42BEXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B15/00Self-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.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Plasma Technology (AREA)
  • Toys (AREA)
  • Portable Nailing Machines And Staplers (AREA)
EP84107615A 1983-08-03 1984-06-30 Projectile comprenant une partie propulsion et une partie charge utile Expired - Lifetime EP0151676B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19833327945 DE3327945A1 (de) 1983-08-03 1983-08-03 Geschoss mit einem nutzlastteil und einem antriebsteil
DE3327945 1983-08-03

Publications (3)

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

Family

ID=6205616

Family Applications (1)

Application Number Title Priority Date Filing Date
EP84107615A Expired - Lifetime EP0151676B1 (fr) 1983-08-03 1984-06-30 Projectile comprenant une partie propulsion et une partie charge utile

Country Status (2)

Country Link
EP (1) EP0151676B1 (fr)
DE (2) DE3327945A1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2000075600A1 (fr) * 1999-06-04 2000-12-14 Nammo Raufoss As Mecanisme de translation et de verrouillage pour missile
WO2000075599A1 (fr) * 1999-06-04 2000-12-14 Nammo Raufoss As Dispositif de propulsion d'un projectile dans un missile
WO2000075601A1 (fr) * 1999-06-04 2000-12-14 Nammo Raufoss As Mecanisme de liberation d'un missile
US9823053B1 (en) * 2016-08-29 2017-11-21 The Boeing Company Solid-fuel ramjet ammunition
WO2023192694A1 (fr) * 2022-03-28 2023-10-05 Raytheon Company Projectile à portée étendue et procédé de propulsion d'un projectile à portée étendue

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3344402A1 (de) * 1983-12-08 1985-06-13 Diehl GmbH & Co, 8500 Nürnberg Flugkoerper
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 (de) * 2006-03-30 2007-11-29 Diehl Bgt Defence Gmbh & Co. Kg Lenkbares Geschoss
DE102007034546A1 (de) 2007-07-20 2009-01-22 Rheinmetall Waffe Munition Gmbh Zielmarkierungsmunition
FR3080912B1 (fr) 2018-05-02 2020-04-03 Nexter Munitions Projectile propulse par statoreacteur
US11796291B2 (en) * 2022-01-11 2023-10-24 Raytheon Company Effector having morphing airframe and method
WO2023137255A1 (fr) * 2022-01-11 2023-07-20 Raytheon Company Effecteur ayant une cellule de transformation et procédé

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 (de) * 1971-07-19 1977-03-03 Societe Nationale Des Poudres Et Explosifs, Paris Rakete
CH610650A5 (en) * 1974-10-29 1979-04-30 Doetsch Hans Peter Self-propelled projectile
DE3148407A1 (de) * 1980-12-08 1982-08-26 United Technologies Corp., 06101 Hartford, Conn. Geschoss

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 (de) * 1971-07-19 1977-03-03 Societe Nationale Des Poudres Et Explosifs, Paris Rakete
CH610650A5 (en) * 1974-10-29 1979-04-30 Doetsch Hans Peter Self-propelled projectile
DE3148407A1 (de) * 1980-12-08 1982-08-26 United Technologies Corp., 06101 Hartford, Conn. Geschoss

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2000075600A1 (fr) * 1999-06-04 2000-12-14 Nammo Raufoss As Mecanisme de translation et de verrouillage pour missile
WO2000075599A1 (fr) * 1999-06-04 2000-12-14 Nammo Raufoss As Dispositif de propulsion d'un projectile dans un missile
WO2000075601A1 (fr) * 1999-06-04 2000-12-14 Nammo Raufoss As Mecanisme de liberation d'un 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 (fr) * 2022-03-28 2023-10-05 Raytheon Company Projectile à portée étendue et procédé de propulsion d'un projectile à portée étendue
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
EP0151676A3 (en) 1988-03-02
EP0151676B1 (fr) 1990-06-13
DE3482490D1 (de) 1990-07-19
DE3327945A1 (de) 1985-02-21

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