EP0151676A2 - Projectile comprenant une partie propulsion et une partie charge utile - Google Patents
Projectile comprenant une partie propulsion et une partie charge utile Download PDFInfo
- 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
Links
Images
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.
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)
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)
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)
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)
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 |
-
1983
- 1983-08-03 DE DE19833327945 patent/DE3327945A1/de not_active Withdrawn
-
1984
- 1984-06-30 DE DE8484107615T patent/DE3482490D1/de not_active Expired - Fee Related
- 1984-06-30 EP EP84107615A patent/EP0151676B1/fr not_active Expired - Lifetime
Patent Citations (5)
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)
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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Legal Events
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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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GBV | Gb: ep patent (uk) treated as always having been void in accordance with gb section 77(7)/1977 [no translation filed] | ||
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