WO2004015361A1 - Programmierbarer artilleriezünder - Google Patents
Programmierbarer artilleriezünder Download PDFInfo
- Publication number
- WO2004015361A1 WO2004015361A1 PCT/EP2003/008583 EP0308583W WO2004015361A1 WO 2004015361 A1 WO2004015361 A1 WO 2004015361A1 EP 0308583 W EP0308583 W EP 0308583W WO 2004015361 A1 WO2004015361 A1 WO 2004015361A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- data
- detonator
- fuse
- ammunition
- information
- Prior art date
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
- F42C17/00—Fuze-setting apparatus
- F42C17/04—Fuze-setting apparatus for electric fuzes
Definitions
- the invention relates to a programmable artillery detonator according to the preamble of claim 1.
- Such a detonator with a coupling coil arranged coaxially in the area of its tip for transferring temperature data during the charging process on the howitzer is NATO standard and is described in DE-Z SOLDAT & TECHNIK, Issue 3, 1997, for the detonator series ANNZ DM74 and ZDZ DM52 described in more detail,
- This standardized inductive interface works with a frequency of 100 kHz in programming cycles of 775 ms, whereby a maximum of 30 bits can be transmitted and acknowledged within one cycle.
- Such a data rate is completely sufficient for the input of customary temp information, such as, in particular, flight distance-dependent target distance and triggering distance or delay in impact or blasting height and, if necessary, overflight safety and self-dismantling criteria.
- a transmitter coil arrangement is accommodated in the howitzer, which extends essentially over a third arc of a circle, along which the projectile is closed Gun supplied and inductively tempered, i.e. equipped with the ignition information.
- temperature information of a smaller amount of information is stored in a capacitor per bit in that the capacitor capacitor in the detonator tip is charged via a photo cell which is exposed to light from the end face of the detonator via a light guide parallel to the detonator axis.
- a hood is temporarily placed on the igniter face, in which a light source is contained, which shines through individually releasable channels into the locally assigned light guides to their photocells.
- the amount of information that can be transmitted in this way is therefore still considerably less than in the case of inductive temperature control via a programming coil contained in the detonator, and cannot be integrated into the howitzer as easily as the inductive information transmission in the course of the charging process.
- artillery ammunition can then be used with canard oars to increase the range by transitioning to a flat gliding flight after the
- Such a satellite-based orbit determination is, however, extremely time-consuming in view of the short computing time available during the possibilities of intervening in the course of a flight, for example in order to slow down the projectile in good time, since several navigation satellites over the horizon have to be detected and their current orbit data must be evaluated.
- this computational navigation task for the current determination of successive positions on the flown lane can be significantly shortened, if the navigation computer on board the projectile can be given as much prediction data as possible about the location by means of the navigation satellites that are likely to be recorded.
- the present invention is based on the technical problem immediately before the ammunition is fired from the
- Detonator tip e.g. Before the programming coil for the inductive tempi standard, which is also arranged coaxially therein, (optionally behind a protective cap made of infrared-transparent plastic material) an infrared data interface in the form of at least one IR receiver is arranged, which is connected to the navigation electronics with its satellite navigation receiver and a satellite antenna, as described in more detail in DE 10037886 A.
- At least one infrared data interface 13a or 13b is located within the cap 11 of the igniter 12, which is essentially frustoconical in shape and has the shape of a truncated cone. At least this is a commercially available infrared receiving diode known as such, which is installed coaxially behind the flattened detonator tip 14 and via which a data stream of up to 10,000 bits can be easily realized, which is quite sufficient to to transfer all available initialization information for satellite navigation to the ammunition in parallel with the inductive temperature control process in the course of the loading process, thereby reducing the computing effort on board to a minimum.
- the infrared data interface 13a for example in the form of an infrared radiation-sensitive receiving diode as shown, is arranged coaxially behind the center of the small truncated cone base of the detonator tip 14, then this necessitates a relative introduction of the detonator for the optronic transmission of the initialization information in the course of the charging process.
- the counter bearing with its infrared coupling element should be axially displaceable in order to be sufficiently close to the data interface for the optronic data transmission even in the event of shorter ammunition during the loading process 13a to be able to be brought up, which, however, would also require considerable interventions in the construction of the weapon.
- a ring 15 is provided as a counter bearing for receiving the coupling element of the infrared transmission path, the inside diameter of which is between the smallest and the largest diameter of the truncated cone-shaped igniter 12 lies, so that it can easily be pushed onto the igniter 12 from the flattened tip 14 without self-centering.
- the infrared data interface 13b is then, as shown in the drawing, not accessible in the flattened tip 14 but in the truncated cone surface of the cap 11 for feeding in modulated IR radiation, for which the ring 15 is equipped with at least one radiating coupling element 16.
- Control of the entire transmission scope is suitable, if necessary for feedback of a checksum.
- the fast infrared transmission enables complete feedback of the data records fed in for the functionally important initialization information for satellite navigation, for which both the interface 13b and the coupling elements 16 are each designed as transceiver units.
- the detonator 12 is, for example, satellite navigation on board the ammunition during its ballistic flight behind its flattened radome tip 14 with an infrared data interface 13a in the form of e.g. an infrared radiation sensitive
- a transmit / receive interface 13b is installed in the cone area of the detonator cap 11, which interacts with at least one of a plurality of bidirectionally parallel transceiver coupling elements 16 on a ring 15 through which the detonator tip 14 projects for data transmission.
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
- Radar Systems Or Details Thereof (AREA)
Abstract
Description
Claims
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10/522,053 US20050211085A1 (en) | 2002-08-07 | 2003-08-02 | Programmable artillery fuse |
EP03784157A EP1527314A1 (de) | 2002-08-07 | 2003-08-02 | Programmierbarer artilleriezünder |
AU2003255358A AU2003255358A1 (en) | 2002-08-07 | 2003-08-02 | Programmable artillery fuse |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE10236157A DE10236157A1 (de) | 2002-08-07 | 2002-08-07 | Programmierbarer Artilleriezünder |
DE10236157.6 | 2002-08-07 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2004015361A1 true WO2004015361A1 (de) | 2004-02-19 |
Family
ID=30775065
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/EP2003/008583 WO2004015361A1 (de) | 2002-08-07 | 2003-08-02 | Programmierbarer artilleriezünder |
Country Status (6)
Country | Link |
---|---|
US (1) | US20050211085A1 (de) |
EP (1) | EP1527314A1 (de) |
KR (1) | KR20050026693A (de) |
AU (1) | AU2003255358A1 (de) |
DE (1) | DE10236157A1 (de) |
WO (1) | WO2004015361A1 (de) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102004036003B4 (de) * | 2004-07-23 | 2006-11-16 | Diehl Bgt Defence Gmbh & Co. Kg | Panzerhaubitze mit Programmiereinrichtung für Artilleriemunition mit Korrekturzünder |
DE102009016147A1 (de) | 2009-04-03 | 2010-10-07 | Rheinmetall Soldier Electronics Gmbh | Zerlegendes Geschoss |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102005024179A1 (de) * | 2005-05-23 | 2006-11-30 | Oerlikon Contraves Ag | Verfahren und Vorrichtung zur Tempierung und/oder Korrektur des Zündzeitpunktes eines Geschosses |
Citations (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4091734A (en) | 1977-02-22 | 1978-05-30 | The United States Of America As Represented By The Secretary Of The Navy | Aircraft to weapon fuze communication link |
US4788899A (en) | 1981-08-19 | 1988-12-06 | Aai Corporation | Ammunition with internal light-settable pickup arrangement for digital memory storage |
EP0451522A1 (de) | 1990-03-15 | 1991-10-16 | Honeywell Ag | Tempiervorrichtung für Geschosszeitzünder |
FR2687260A1 (fr) * | 1992-02-12 | 1993-08-13 | Telecommunications Sa | Procede de transmission de donnees par faisceau optique entre un vehicule porteur et sa charge et dispositif pour la mise en óoeuvre du procede. |
US5467940A (en) | 1993-07-28 | 1995-11-21 | Diehl Gmbh & Co. | Artillery rocket |
EP0797068A2 (de) * | 1996-03-21 | 1997-09-24 | Israel Aircraft Industries, Ltd. | Lenkungssystem für Luft-Luft-Flugkörper |
EP0806625A2 (de) | 1996-05-09 | 1997-11-12 | Bodenseewerk Gerätetechnik GmbH | Schnittstelle zur digitalen Datenübertragung zwischen einem Flugkörper und einem Startgerät |
DE19740888A1 (de) | 1997-09-17 | 1999-03-25 | Rheinmetall W & M Gmbh | Verfahren zum autonomen Lenken eines drallstabilisierten Artilleriegeschosses und autonom gelenktes Artilleriegeschoß zur Durchführung des Verfahrens |
US5943009A (en) * | 1997-02-27 | 1999-08-24 | Abbott; Anthony Steven | GPS guided munition |
DE19957363A1 (de) | 1999-11-29 | 2001-05-31 | Diehl Munitionssysteme Gmbh | Verfahren zur zielbezogenen Korrektur einer ballistischen Flugbahn |
DE10023345A1 (de) | 2000-05-12 | 2001-11-22 | Diehl Munitionssysteme Gmbh | Drallstabilisiertes Projektil mit Bremseinrichtung |
Family Cites Families (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3228337A (en) * | 1962-12-04 | 1966-01-11 | Rodney E Grantham | Radio frequency free communication system |
CH628732A5 (fr) * | 1979-03-05 | 1982-03-15 | Mefina Sa | Dispositif pour transmettre des signaux a une fusee de projectile. |
US4322998A (en) * | 1979-10-26 | 1982-04-06 | The United States Of America As Represented By The Secretary Of The Navy | Integral store suspension and communication device |
US4318342A (en) * | 1980-01-25 | 1982-03-09 | Aai Corporation | Ammunition with surface-mounted light-settable pickup arrangement for digital memory storage |
CA1233896A (en) * | 1983-04-11 | 1988-03-08 | Kenneth N. Jarrott | Programmable electronic delay fuse |
US4597345A (en) * | 1984-10-29 | 1986-07-01 | The United States Of America As Represented By The Secretary Of The Navy | Torpedo cableless umbilical |
US4711152A (en) * | 1986-10-30 | 1987-12-08 | Aerojet-General Corporation | Apparatus for transmititng data to a projectile positioned within a gun tube |
DE58901599D1 (de) * | 1988-10-21 | 1992-07-09 | Rheinmetall Gmbh | Vorrichtung zur zuendereinstellung. |
DE3912287A1 (de) * | 1989-04-14 | 1990-10-18 | Diehl Gmbh & Co | Ladeschuetzenausruestung |
US4936187A (en) * | 1989-04-20 | 1990-06-26 | The United States Of America As Represented By The Secretary Of The Navy | Wire-free arming system for an aircraft-delivered bomb |
US5247866A (en) * | 1992-09-16 | 1993-09-28 | The United States Of America As Represented By The Secretary Of The Army | Optically set fuze system |
US5657947A (en) * | 1994-08-24 | 1997-08-19 | Loral Corp. | Precision guidance system for aircraft launched bombs |
DE19824288C2 (de) * | 1998-05-29 | 2002-11-14 | Rheinmetall W & M Gmbh | Artilleriegeschoß |
KR100616806B1 (ko) * | 2001-06-06 | 2006-08-29 | 세넥스 익스플로시브즈, 인코포레이티드 | 개별 지연된 뇌관들로 된 발파 회로의 기폭 시스템 |
-
2002
- 2002-08-07 DE DE10236157A patent/DE10236157A1/de not_active Withdrawn
-
2003
- 2003-08-02 US US10/522,053 patent/US20050211085A1/en not_active Abandoned
- 2003-08-02 KR KR1020047006717A patent/KR20050026693A/ko not_active Application Discontinuation
- 2003-08-02 WO PCT/EP2003/008583 patent/WO2004015361A1/de not_active Application Discontinuation
- 2003-08-02 EP EP03784157A patent/EP1527314A1/de not_active Withdrawn
- 2003-08-02 AU AU2003255358A patent/AU2003255358A1/en not_active Abandoned
Patent Citations (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4091734A (en) | 1977-02-22 | 1978-05-30 | The United States Of America As Represented By The Secretary Of The Navy | Aircraft to weapon fuze communication link |
US4788899A (en) | 1981-08-19 | 1988-12-06 | Aai Corporation | Ammunition with internal light-settable pickup arrangement for digital memory storage |
EP0451522A1 (de) | 1990-03-15 | 1991-10-16 | Honeywell Ag | Tempiervorrichtung für Geschosszeitzünder |
FR2687260A1 (fr) * | 1992-02-12 | 1993-08-13 | Telecommunications Sa | Procede de transmission de donnees par faisceau optique entre un vehicule porteur et sa charge et dispositif pour la mise en óoeuvre du procede. |
US5467940A (en) | 1993-07-28 | 1995-11-21 | Diehl Gmbh & Co. | Artillery rocket |
EP0797068A2 (de) * | 1996-03-21 | 1997-09-24 | Israel Aircraft Industries, Ltd. | Lenkungssystem für Luft-Luft-Flugkörper |
EP0806625A2 (de) | 1996-05-09 | 1997-11-12 | Bodenseewerk Gerätetechnik GmbH | Schnittstelle zur digitalen Datenübertragung zwischen einem Flugkörper und einem Startgerät |
US5943009A (en) * | 1997-02-27 | 1999-08-24 | Abbott; Anthony Steven | GPS guided munition |
DE19740888A1 (de) | 1997-09-17 | 1999-03-25 | Rheinmetall W & M Gmbh | Verfahren zum autonomen Lenken eines drallstabilisierten Artilleriegeschosses und autonom gelenktes Artilleriegeschoß zur Durchführung des Verfahrens |
DE19957363A1 (de) | 1999-11-29 | 2001-05-31 | Diehl Munitionssysteme Gmbh | Verfahren zur zielbezogenen Korrektur einer ballistischen Flugbahn |
DE10023345A1 (de) | 2000-05-12 | 2001-11-22 | Diehl Munitionssysteme Gmbh | Drallstabilisiertes Projektil mit Bremseinrichtung |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102004036003B4 (de) * | 2004-07-23 | 2006-11-16 | Diehl Bgt Defence Gmbh & Co. Kg | Panzerhaubitze mit Programmiereinrichtung für Artilleriemunition mit Korrekturzünder |
DE102009016147A1 (de) | 2009-04-03 | 2010-10-07 | Rheinmetall Soldier Electronics Gmbh | Zerlegendes Geschoss |
Also Published As
Publication number | Publication date |
---|---|
AU2003255358A8 (en) | 2004-02-25 |
EP1527314A1 (de) | 2005-05-04 |
US20050211085A1 (en) | 2005-09-29 |
KR20050026693A (ko) | 2005-03-15 |
DE10236157A1 (de) | 2004-02-26 |
AU2003255358A1 (en) | 2004-02-25 |
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