US20050211085A1 - Programmable artillery fuse - Google Patents

Programmable artillery fuse Download PDF

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Publication number
US20050211085A1
US20050211085A1 US10/522,053 US52205305A US2005211085A1 US 20050211085 A1 US20050211085 A1 US 20050211085A1 US 52205305 A US52205305 A US 52205305A US 2005211085 A1 US2005211085 A1 US 2005211085A1
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US
United States
Prior art keywords
fuse
data
ammunition
cap
ring
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.)
Abandoned
Application number
US10/522,053
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English (en)
Inventor
Karl Kautzsch
Volker Koch
Johann Pannhorst
Rolf Kaden
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.)
Diehl BGT Defence GmbH and Co KG
Original Assignee
Diehl Munitionssysteme GmbH and Co KG
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 Diehl Munitionssysteme GmbH and Co KG filed Critical Diehl Munitionssysteme GmbH and Co KG
Assigned to DIEHL MUNITIONSSYSTEME GMBH & CO. reassignment DIEHL MUNITIONSSYSTEME GMBH & CO. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: KAUTZSCH, KARL, KOCH, VOLKER, KADEN, ROLF, PANNHORST, JOHANN
Publication of US20050211085A1 publication Critical patent/US20050211085A1/en
Abandoned legal-status Critical Current

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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 present invention relates to a programmable artillery fuse according to the preamble of claim 1 .
  • Such a fuse having a coupling coil, positioned coaxially in the region of its tip, for accepting fuse-setting data during the loading procedure at the howitzer is NATO standard and described in greater detail, for example, in DE-Z SOLDAT & TECHNIK [SOLDIER & TECHNOLOGY], Issue 3, 1997, for the fuse series ANNZ DM74 and ZDZ DM52.
  • This standardized conductive interface operates at a frequency of 100 kHz and programming cycles of 775 ms, a maximum of 30 bits able to be transmitted and acknowledged within a cycle.
  • Such a data rate is completely sufficient for the input of typical fuse-setting information, particularly target distance and triggering proximity, which are dependent on the flight time, or impact delay and/or detonation height and possibly overflight safety and self-destruct criteria.
  • a transmitting coil system is housed in the howitzer, for the inductive transmission of fuse-setting information into a fuse-setting coil of an artillery shell positioned coaxially in the fuse tip, which extends essentially over a third of a circle, along which the projectile is supplied to the breech of the weapon and its fuse is inductively set at the same time, i.e., equipped with the trigger information.
  • fuse-setting information of lesser informational extent is stored in a capacitor bit by bit in that the capacitor is charged in the fuse tip via a photocell, which has light applied to it from the fuse front face via an optical fiber parallel to the fuse axis.
  • a hood is temporarily placed on the fuse front face which contains a light source that irradiates these locally assigned optical fibers to their photocells via individually releasable channels.
  • the informational extent thus transmittable is therefore significantly less than in the case of inductive fuse setting via a programming coil contained in the fuse, and nay not be integrated into the howitzer as free of complications as inductive information transmission in the course of the loading procedure.
  • the artillery ammunition may be equipped, according to U.S. Pat. No. 5,467,940 A, with Canard rudders to increase the range by entering a flat glide flight after the apogee of the ballistic starting curve, or may be equipped, according to DE 197 40 888 A1, with a braking parachute to steepen the descent rate out of the ballistic start curve, for example.
  • the target position for a final phase control of the projectile be transmitted to the shell using an inductive data transmission system before the shell is fired, for example, and then this predetermined target data be compared after firing on board the artillery projectile with satellite navigation data obtained there, in order to obtain correction data for the projectile steering.
  • Such target coordinates which are merely to be preset, only have a data extent in the magnitude of the typical fuse-setting information, however, possible current projection data for accelerating the use of satellite navigation may not be reliably introduced into the ammunition via an inductive system of this type in the course of the loading procedure with the speed necessary in regard to the cadence of the howitzer and then possibly queried again to verify correct data transmission.
  • Foldable mantel segments for the braking function of the correction unit are positioned in the largest lower diameter region of the projectile fuse between the electronics and the fuse safety device.
  • Established artillery ammunition, which is first equipped with its fuse in case of use, is now fired using such a braking fuse instead of the typical time fuse if necessary.
  • the function-critical braking point on the ballistic flight path then actually flown is expediently established by comparing the current path data with predetermined path criteria, the information about the current flight path being obtained on board the projectile using satellite navigation.
  • Such a satellite-supported path determination is, however, extremely time-consuming in consideration of the short computing time available during the engagement possibilities in the course of a flight, such as braking the projectile at the right time, since multiple navigation satellites must be detected over the horizon and analyzed in regard to their instantaneous path data.
  • This computer navigation task for the current determination of sequential positions on the path flown may, however, be decisively shortened if as much projection data as possible about the location determination using the navigation satellites foreseeably to be detected may also be given to the navigation computer on board the projectile. In order to be current, this data may not be provided already in the magazine, but rather it must occur close in time to the firing of the ammunition in order to be able to actually noticeably shorten the necessary computing time for the path determination on board.
  • the data rate necessary for transmitting navigation information for multiple satellites in a short time is much too high to be executed via the inductive coupling coil of the loading system.
  • Integrating a second coil system into the fuse which is optimized for the higher data rate for additional information to be input inductively in addition to the typical fuse-setting presets, could be considered.
  • the installation space under the fuse ogive is insufficient for two inductive coupling systems to be operated separately; this does not even consider the problems of interference-free separate operation of two systems which are inductively coupled because of the installation conditions.
  • the suggestion of implementing the higher data rate of the additional information via a sensor in the ammunition tail known from EP 0 992 762 B1, also does not represent an achievable solution, at least for existing ammunition.
  • the present invention is based on the technical object of being able to implement data rates which significantly exceed the data extent of current fuse-setting systems directly before the firing of the ammunition from the howitzer, particularly to be able to transmit the greatest possible extent of initialization data for a rapid satellite-supported flight path determination on board the projectile, without interfering with the established inductive fuse setting in the course of the loading procedure in this way.
  • an infrared data interface in the form of at least one IR receiver, which is connected to the navigation electronics with its satellite navigation receiver and a satellite antenna, as is described in greater detail in DE 10037886 A, for example, is positioned under the radome of the fuse tip, e.g., in front of the programming coil for the inductive fuse-setting standard also positioned coaxially therein (possibly behind a protective cap made of infrared-transparent plastic material).
  • FIG. 1 has a simplified axial frontal view toward the fuse tip, shaped like a truncated cone, as its object.
  • At least one infrared data interface 13 a and/or 13 b is located inside the tip 11 of the fuse 12 , which essentially has the shape of a hollow truncated cone and may be blown open laterally to release braking means.
  • This interface is essentially a commercially available infrared receiving diode, known per se, which is installed coaxially behind the flattened fuse tip 14 and via which a data stream up to 10,000 bits may be implemented without anything further, which is completely sufficient to transmit all available initialization information for satellite navigation into the ammunition parallel in time to the inductive fuse-setting procedure in the course of the loading procedure and thus reduce the computing outlay on board to a minimum.
  • the infrared data interface 13 a is positioned coaxially behind the center of the small truncated cone base of the fuse tip 14 in the form of a receiving diode, which is sensitive to infrared radiation, as shown, for the optronic transmission of the initialization information in the course of the loading procedure, this requires a relative approach of the fuse tip 14 to a thrust bearing in the weapon, equipped with an infrared radiation transmitter as a coupling element, in order to be able to transmit the initialization information in the course of the loading procedure.
  • this thrust bearing having its infrared coupling element must be axially displaceable in order to be able to approach the data interface 13 a sufficiently closely for the optronic data transmission in the course of the loading procedure, even if there is shorter ammunition, which would nonetheless still require significant interventions in the construction of the weapon.
  • a ring 15 is provided as the thrust bearing for receiving the coupling element of the infrared transmission path, whose internal diameter is between the smallest and the largest diameters of the fuse 12 , which is shaped like a truncated cone, so that it may be pushed onto the fuse 12 from the flattened tip 14 in a self-centering way without problems.
  • the infrared data interface 13 b is then accessible not in the flattened tip 14 , but rather in the truncated cone lateral surface of the cap 11 for supplying modulated IR radiation, for which the ring 15 is equipped with at least one emitting coupling element 16 as shown in the drawing.
  • the typical inductive fuse setting is not suitable for acknowledgments to check the total extent of transmission, at least for acknowledgments of a check sum, because of its data processing capacity in regard to the transmission speed.
  • the rapid infrared transmission allows a complete acknowledgment of the data sets supplied for the functionally important initialization information for satellite navigation, for which both the interface 13 b and the coupling element 16 are each laid out as transceiver units.
  • the fuse 12 is equipped according to the present invention, behind its flattened radome tip 14 , for example, with an infrared data interface 13 in the form of a receiving diode sensitive to infrared radiation, for example, via which the initialization information for the satellite navigation receiver may be supplied optronically parallel in time to the inductive fuse-setting information, but without impairing it.
  • a transceiver interface 13 b is installed in the cone mantel region of the fuse cap 11 , which works together with at least one of multiple transceiver coupling elements 16 on a ring 15 , operated bidirectionally in parallel, through which the fuse tip 14 projects for the 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)
US10/522,053 2002-08-07 2003-08-02 Programmable artillery fuse Abandoned US20050211085A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE10236157A DE10236157A1 (de) 2002-08-07 2002-08-07 Programmierbarer Artilleriezünder
DE102361576 2002-08-07
PCT/EP2003/008583 WO2004015361A1 (de) 2002-08-07 2003-08-02 Programmierbarer artilleriezünder

Publications (1)

Publication Number Publication Date
US20050211085A1 true US20050211085A1 (en) 2005-09-29

Family

ID=30775065

Family Applications (1)

Application Number Title Priority Date Filing Date
US10/522,053 Abandoned US20050211085A1 (en) 2002-08-07 2003-08-02 Programmable artillery fuse

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 (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20070074625A1 (en) * 2005-05-23 2007-04-05 Jens Seidensticker Method and device for setting the fuse and/or correcting the ignition time of a projectile

Families Citing this family (2)

* Cited by examiner, † Cited by third party
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

Citations (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3228337A (en) * 1962-12-04 1966-01-11 Rodney E Grantham Radio frequency free communication system
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
US4318342A (en) * 1980-01-25 1982-03-09 Aai Corporation Ammunition with surface-mounted light-settable pickup arrangement for digital memory storage
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
US4327625A (en) * 1979-03-05 1982-05-04 Mefina S.A. Device for transmitting signals to a 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
US4632031A (en) * 1983-04-11 1986-12-30 The Commonwealth Of Australia Programmable electronic delay fuse
US4711152A (en) * 1986-10-30 1987-12-08 Aerojet-General Corporation Apparatus for transmititng data to a projectile positioned within a gun tube
US4788899A (en) * 1981-08-19 1988-12-06 Aai Corporation Ammunition with internal light-settable pickup arrangement for digital memory storage
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
US4979424A (en) * 1988-10-21 1990-12-25 Rheinmetall Gmbh Device for setting a fuse
US5024136A (en) * 1989-04-14 1991-06-18 Diehl Gmbh & Co. Equipment for gun loader
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
US5983771A (en) * 1996-05-09 1999-11-16 Bodenseewerk Geratetechnik Gmbh Interface for digital data transfer between a missile and a launcher
US6618237B2 (en) * 2001-06-06 2003-09-09 Senex Explosives, Inc. System for the initiation of rounds of individually delayed detonators

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4008253A1 (de) * 1990-03-15 1991-09-19 Honeywell Regelsysteme Gmbh Tempiervorrichtung fuer geschosszeitzuender
FR2687260B1 (fr) * 1992-02-12 1995-02-24 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.
DE4325218C2 (de) 1993-07-28 1998-10-22 Diehl Stiftung & Co Artillerie-Rakete und Verfahren zur Leistungssteigerung einer Artillerie-Rakete
IL117589A (en) * 1996-03-21 2001-10-31 Israel Aircraft Ind Ltd Air-to-air missile guidance system
US5943009A (en) * 1997-02-27 1999-08-24 Abbott; Anthony Steven GPS guided munition
DE19740888C2 (de) * 1997-09-17 1999-09-02 Rheinmetall W & M Gmbh Verfahren zum autonomen Lenken eines drallstabilisierten Artilleriegeschosses und autonom gelenktes Artilleriegeschoß zur Durchführung des Verfahrens
DE19824288C2 (de) * 1998-05-29 2002-11-14 Rheinmetall W & M Gmbh Artilleriegeschoß
DE19957363A1 (de) 1999-11-29 2001-05-31 Diehl Munitionssysteme Gmbh Verfahren zur zielbezogenen Korrektur einer ballistischen Flugbahn
DE10023345C2 (de) 2000-05-12 2002-03-28 Diehl Munitionssysteme Gmbh Drallstabilisiertes Projektil mit Bremseinrichtung

Patent Citations (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3228337A (en) * 1962-12-04 1966-01-11 Rodney E Grantham Radio frequency free communication system
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
US4327625A (en) * 1979-03-05 1982-05-04 Mefina S.A. Device for transmitting signals to a fuse
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
US4788899A (en) * 1981-08-19 1988-12-06 Aai Corporation Ammunition with internal light-settable pickup arrangement for digital memory storage
US4632031A (en) * 1983-04-11 1986-12-30 The Commonwealth Of Australia 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
US4979424A (en) * 1988-10-21 1990-12-25 Rheinmetall Gmbh Device for setting a fuse
US5024136A (en) * 1989-04-14 1991-06-18 Diehl Gmbh & Co. Equipment for gun loader
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
US5983771A (en) * 1996-05-09 1999-11-16 Bodenseewerk Geratetechnik Gmbh Interface for digital data transfer between a missile and a launcher
US6618237B2 (en) * 2001-06-06 2003-09-09 Senex Explosives, Inc. System for the initiation of rounds of individually delayed detonators

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20070074625A1 (en) * 2005-05-23 2007-04-05 Jens Seidensticker Method and device for setting the fuse and/or correcting the ignition time of a projectile

Also Published As

Publication number Publication date
AU2003255358A8 (en) 2004-02-25
EP1527314A1 (de) 2005-05-04
WO2004015361A1 (de) 2004-02-19
KR20050026693A (ko) 2005-03-15
DE10236157A1 (de) 2004-02-26
AU2003255358A1 (en) 2004-02-25

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Date Code Title Description
AS Assignment

Owner name: DIEHL MUNITIONSSYSTEME GMBH & CO., GERMANY

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:KAUTZSCH, KARL;KOCH, VOLKER;PANNHORST, JOHANN;AND OTHERS;REEL/FRAME:016726/0714;SIGNING DATES FROM 20041011 TO 20041112

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION