EP0802391B1 - Verfahren zur Bestimmung einer korrigierten Zerlegungszeit eines programmierbar zerlegbaren Geschosses - Google Patents

Verfahren zur Bestimmung einer korrigierten Zerlegungszeit eines programmierbar zerlegbaren Geschosses Download PDF

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Publication number
EP0802391B1
EP0802391B1 EP96118044A EP96118044A EP0802391B1 EP 0802391 B1 EP0802391 B1 EP 0802391B1 EP 96118044 A EP96118044 A EP 96118044A EP 96118044 A EP96118044 A EP 96118044A EP 0802391 B1 EP0802391 B1 EP 0802391B1
Authority
EP
European Patent Office
Prior art keywords
projectile
velocity
time
target
fragmentation
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.)
Expired - Lifetime
Application number
EP96118044A
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German (de)
English (en)
French (fr)
Other versions
EP0802391A1 (de
Inventor
André Boss
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 Air Defence AG
Original Assignee
Oerlikon Contraves AG
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Filing date
Publication date
Application filed by Oerlikon Contraves AG filed Critical Oerlikon Contraves AG
Publication of EP0802391A1 publication Critical patent/EP0802391A1/de
Application granted granted Critical
Publication of EP0802391B1 publication Critical patent/EP0802391B1/de
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
    • 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 method for determining a corrected disassembly time one of a programmable disassembled from a gun barrel Projectile according to the preamble of the only claim.
  • a device which has a measuring device for the projectile velocity arranged at the mouth of a gun barrel.
  • the measuring device consists of two ring coils arranged at a certain distance from one another.
  • a pulse is generated in short succession in each ring coil due to the change in magnetic flux that occurs.
  • the pulses are fed to evaluation electronics, in which the projectile speed is calculated from the time interval between the pulses and the distance between the ring coils.
  • a transmitting coil is arranged behind the measuring device for the speed, which co-operates with a receiving coil provided in the projectile.
  • the receiving coil is connected to a counter via a high-pass filter, which is connected on the output side to a timer.
  • a disassembly time is formed from the calculated bullet speed and a target distance to a target object, which is transmitted inductively to the bullet immediately after the measuring device has flown through. With this disassembly time, the time fuse is set so that the projectile can be disassembled in the area of the target object.
  • an attacking target can be destroyed by multiple hits, as is known, for example, from a publication OC 2052 d 94 from the company Oerlikon-Contraves, Zurich, if, after the sub-projectiles have been ejected, Time of disassembly the expected area of the target is occupied by a cloud formed by the subprojectiles.
  • the part carrying the subprojectiles is separated and torn open at predetermined breaking points.
  • the ejected sub-projectiles describe a swirl-stabilized trajectory caused by the rotation of the projectile and lie evenly distributed on approximately semicircular curves of circular areas of a cone, so that a good chance of hitting can be achieved.
  • the invention has for its object to propose a method according to the preamble, by means of which an optimal while avoiding the disadvantages mentioned above Hit or shot probability is achievable.
  • the advantages achieved with the invention can be seen in the fact that a given disassembly distance is independent of the current measured bullet speed, so that a permanent optimal hit or shot probability is achieved can.
  • the proposed correction factor for correcting the disassembly time is based only on the relative velocity of the bullet-target and a derivation of the ballistics at the meeting point.
  • 1 denotes a fire control and 2 a gun.
  • the fire control system 1 consists of a search sensor 3 for the detection of a target 4 , a follow-up sensor 5 connected to the search sensor 3 for target detection, 3-D target tracking and 3-D target measurement, and a fire control computer 6 .
  • the fire control computer 6 has at least one main filter 7 , a lead computing unit 9 and a correction computing unit 12 .
  • the main filter 7 is connected on the input side to the follow sensor 5 and on the output side to the lead computing unit 9 , the main filter 7 receiving the 3-D target data received from the follow sensor 5 in the form of estimated target data 2 such as position, speed, acceleration, etc. forward the lead computing unit 9 , which is connected on the output side to the correction computing unit.
  • Meteorological data can be supplied to the lead computing unit 9 via a further input Me. The meaning of the designations on the individual connections or connections is explained in more detail below on the basis of the functional description.
  • a computer of the gun 2 has an evaluation circuit 10 and an update computing unit 11 .
  • the evaluation circuit 10 is connected on the input side to a measuring device 14 for the projectile speed, which is arranged at the mouth of a gun barrel 13 and is described in greater detail below with reference to FIG . 2 , and is connected on the output side to the lead computing unit 9 and the update computing unit 11 .
  • the update computing unit 11 is connected on the input side to the reserve and correction computing unit 9, 12 and is connected on the output side to a programming part integrated in the measuring device 14 .
  • the correction arithmetic unit 12 is connected on the input side to the lead arithmetic unit 9 and on the output side to the update arithmetic unit 11 .
  • a gun servo 15 and a triggering device 16 responding to a fire command are also connected to the lead computing unit 9 .
  • the connections between the fire control 1 and the gun 2 are combined to form a data transmission, which is designated by 17 .
  • the meaning of the designations on the individual connections between the computing units 10, 11, 12 and between the fire control system 1 and the gun 2 is explained in more detail below on the basis of the functional description.
  • 18 and 18 ' designate a floor which is shown during a programming phase ( 18 ) and at the time of disassembly ( 18' ).
  • the projectile 18 is a programmable projectile with primary and secondary ballistics, which is equipped with an ejection charge and a time fuse and is filled with sub-projectiles 19 .
  • a support tube 20 attached to the muzzle of the gun barrel 13 consists of three parts 21, 22, 23 . Between the first part 21 and the second or third part 22, 23 , ring coils 24, 25 are arranged for measuring the projectile speed. On the third part 23 — also called the programming part — a transmission coil 27 held in a coil body 26 is fastened. The type of attachment of the support tube 20 and the three parts 21, 22, 23 to each other is not shown and described. Lines 28, 29 are provided for supplying the ring coils. Soft iron bars 30 are arranged on the circumference of the support tube 20 for the purpose of shielding against magnetic fields which interfere with the measurement.
  • the projectile 18 has a receiving coil 31 which is connected to a timer 34 via a filter 32 and a counter 33 .
  • a pulse is generated in short succession in each ring coil.
  • These pulses of the evaluation circuit 10 (Fig.1) are supplied, in which from the time interval of the pulses and a distance a between the toroid coils, the projectile velocity is calculated 24.25.
  • a disassembly time is calculated, as described in more detail below, which is transmitted inductively in digital form to the receiving coil 31 when the projectile 18 passes through the transmitting coil 27 for the purpose of setting the counter 32 .
  • Pz denotes a point of disassembly of the projectile 18 .
  • the ejected subprojectiles are, depending on the distance from the point of decomposition Pz, evenly distributed on approximately semicircular curves of (perspectively represented) circular areas F1, F2, F3, F4 of a cone C.
  • F1, F2, F3, F4 of a cone C.
  • On a first abscissa the distance from the point of decomposition Pz is plotted in meters m, while on a second abscissa II the area sizes of the areas F1, F2, F3, F4 are plotted in square meters m 2 and their diameter in meters m.
  • 4 and 4 ' denote the target to be defended, which is shown in a hit or shoot position ( 4 ) and in a position ( 4' ) preceding the hit or shoot position.
  • the lead computation unit 9 calculates a target distance RT, a disassembly time Tz and a sub-projectile flight time ts from a predetermined disassembly distance Dz, a retention speed VOv and the target data Z, taking meteorological data into account for projectiles with primary and secondary ballistics.
  • Tz is the flight time of the projectile to the point of disassembly Pz
  • ts is the flight time of a subprojectile flying in the projectile direction from the point of disassembly Pz to the meeting point Pf ( Fig . 3,4 ).
  • the lead speed VOv is formed, for example, from the mean value of a number of measured projectile speeds Vm supplied via the data transmission 17 , which immediately precede the current measured projectile speed Vm.
  • the lead computing unit 9 also determines a gun angle a of the azimuth and a gun angle ⁇ of the elevation.
  • the quantities ⁇ , ⁇ , Tz and VOv are fed to the correction computing unit 12 , which calculates a correction factor K as described in more detail below.
  • the current (running) time (t) is interpolated or extrapolated.
  • the ballistics of a projectile is determined by a system of differential equations of the form described, along with the initial conditions a clear ballistic solution is determined.
  • ⁇ o ( t o ) With becomes a component of ⁇ o ( t o ) in the pipe direction and with ⁇ (2) / o defines a perpendicular component, so that is where means the speed of the pipe mouth and is a reserve size which is actually maintained by the projectile.
  • the corrected decomposition time Tz (Vm) is interpolated or extrapolated depending on the validity for the current running time t.
  • the disassembly time Tz (Vm, t) now calculated is supplied to the transmitter coil 27 of the programming part 23 of the measuring device 14 and, as already described above with reference to FIG. 2 , is transmitted inductively to a projectile 18 flying by.
  • the disassembly distance Dz ( FIG. 3, 4 ) can be kept constant regardless of the variations in the projectile speed , and / or caused by the use of non-updated values, so that an optimal meeting or Probability of shooting can be achieved.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Electrotherapy Devices (AREA)
  • Control Of Ac Motors In General (AREA)
  • Control Of Electric Motors In General (AREA)
  • Generation Of Surge Voltage And Current (AREA)
  • Investigating, Analyzing Materials By Fluorescence Or Luminescence (AREA)
  • Fishing Rods (AREA)
  • Testing Of Balance (AREA)
EP96118044A 1996-04-19 1996-11-11 Verfahren zur Bestimmung einer korrigierten Zerlegungszeit eines programmierbar zerlegbaren Geschosses Expired - Lifetime EP0802391B1 (de)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
CH1001/96 1996-04-19
CH100196 1996-04-19
CH100196 1996-04-19

Publications (2)

Publication Number Publication Date
EP0802391A1 EP0802391A1 (de) 1997-10-22
EP0802391B1 true EP0802391B1 (de) 2000-12-13

Family

ID=4200143

Family Applications (1)

Application Number Title Priority Date Filing Date
EP96118044A Expired - Lifetime EP0802391B1 (de) 1996-04-19 1996-11-11 Verfahren zur Bestimmung einer korrigierten Zerlegungszeit eines programmierbar zerlegbaren Geschosses

Country Status (12)

Country Link
US (1) US5834675A (ko)
EP (1) EP0802391B1 (ko)
JP (1) JP3891619B2 (ko)
KR (1) KR100410718B1 (ko)
AT (1) ATE198103T1 (ko)
AU (1) AU716346B2 (ko)
CA (1) CA2190384C (ko)
DE (1) DE59606214D1 (ko)
NO (1) NO311954B1 (ko)
SG (1) SG83658A1 (ko)
TR (1) TR199600952A1 (ko)
ZA (1) ZA969536B (ko)

Families Citing this family (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2761767B1 (fr) * 1997-04-03 1999-05-14 Giat Ind Sa Procede de programmation en vol d'un instant de declenchement d'un element de projectile, conduite de tir et fusee mettant en oeuvre un tel procede
EP0992762B1 (de) 1998-10-08 2002-03-06 Oerlikon Contraves Ag Verfahren und Vorrichtung zur Übertragung von Informationen auf programmierbare Geschosse
DE59914323D1 (de) 1998-10-08 2007-06-14 Contraves Ag Verfahren und Vorrichtung zur Korrektur der Zerlegungszeit bzw. der Zerlegungsumdrehungszahl eines drallstabilisierten programmierbaren Geschosses
ATE227839T1 (de) * 1998-10-08 2002-11-15 Contraves Pyrotec Ag Verfahren zum korrigieren einer vorprogrammierten auslösung eines vorganges in einem drallstabilisierten geschoss, vorrichtung zur durchführung des verfahrens und verwendung der vorrichtung
US20040237762A1 (en) * 1999-11-03 2004-12-02 Metal Storm Limited Set defence means
US6497170B1 (en) * 2001-07-05 2002-12-24 The United States Of America As Represented By The Secretary Of The Army Muzzle brake vibration absorber
DE50309574D1 (de) * 2003-02-26 2008-05-21 Rwm Schweiz Ag Verfahren zur Programmierung der Zerlegung von Projektilen und Rohrwaffen mit Programmiersystem
US7533612B1 (en) * 2004-09-23 2009-05-19 The United States Of America As Represented By The Secretary Of The Army Projectile height of burst determination method and system
DE102009011447B9 (de) * 2009-03-03 2012-08-16 Diehl Bgt Defence Gmbh & Co. Kg Verfahren zum Zünden eines Gefechtskopfs einer Granate und Fahrzeug
US11047663B1 (en) * 2010-11-10 2021-06-29 True Velocity Ip Holdings, Llc Method of coding polymer ammunition cartridges
DE102011018248B3 (de) 2011-04-19 2012-03-29 Rheinmetall Air Defence Ag Vorrichtung und Verfahren zur Programmierung eines Geschosses
DE102011106198B3 (de) * 2011-06-07 2012-03-15 Rheinmetall Air Defence Ag Verfahren zur Bestimmung der Mündungsaustrittsgeschwindigkeit eines Projektils
US10514234B2 (en) 2013-03-27 2019-12-24 Nostromo Holdings, Llc Method and apparatus for improving the aim of a weapon station, firing a point-detonating or an air-burst projectile
US11933585B2 (en) 2013-03-27 2024-03-19 Nostromo Holdings, Llc Method and apparatus for improving the aim of a weapon station, firing a point-detonating or an air-burst projectile
EP2894429B1 (en) * 2014-01-08 2018-08-15 Nostromo Holdings, LLC Mortar safety device
US9740326B2 (en) * 2015-03-31 2017-08-22 Synaptics Incorporated Sensor array with split-drive differential sensing
FR3071596B1 (fr) * 2017-09-27 2019-10-18 Thales Procede et dispositif de lancement de projectiles sur une cible a atteindre
US10883809B1 (en) * 2019-05-07 2021-01-05 U.S. Government As Represented By The Secretary Of The Army Muzzle velocity correction

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US4142442A (en) * 1971-12-08 1979-03-06 Avco Corporation Digital fuze
US4267776A (en) * 1979-06-29 1981-05-19 Motorola, Inc. Muzzle velocity compensating apparatus and method for a remote set fuze
US4449041A (en) * 1980-10-03 1984-05-15 Raytheon Company Method of controlling antiaircraft fire
US4625646A (en) * 1980-10-06 1986-12-02 The Boeing Aerospace Company Aerial missile having multiple submissiles with individual control of submissible ejection
FR2514884B1 (fr) * 1981-10-20 1985-07-12 Sfim Procede et dispositif pour corriger globalement, d'un tir au suivant, le tir d'une arme a tir tendu
DE3309147A1 (de) * 1983-03-15 1984-09-20 Rainer Dipl.-Phys. 6901 Gaiberg Berthold Verfahren und anordnung zur korrektur eines zuendzeitpunktes
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Also Published As

Publication number Publication date
JPH09287899A (ja) 1997-11-04
US5834675A (en) 1998-11-10
EP0802391A1 (de) 1997-10-22
TR199600952A1 (xx) 1997-11-21
NO964757L (no) 1997-10-20
NO311954B1 (no) 2002-02-18
ATE198103T1 (de) 2000-12-15
DE59606214D1 (de) 2001-01-18
CA2190384A1 (en) 1997-10-20
JP3891619B2 (ja) 2007-03-14
CA2190384C (en) 2003-09-30
SG83658A1 (en) 2001-10-16
NO964757D0 (no) 1996-11-08
KR100410718B1 (ko) 2004-04-03
AU7172796A (en) 1997-10-23
KR970070943A (ko) 1997-11-07
ZA969536B (en) 1997-06-17
AU716346B2 (en) 2000-02-24

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