WO2004031680A1 - Ameliorations apportees a des systemes de choix des objectifs - Google Patents

Ameliorations apportees a des systemes de choix des objectifs Download PDF

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Publication number
WO2004031680A1
WO2004031680A1 PCT/GB2003/004210 GB0304210W WO2004031680A1 WO 2004031680 A1 WO2004031680 A1 WO 2004031680A1 GB 0304210 W GB0304210 W GB 0304210W WO 2004031680 A1 WO2004031680 A1 WO 2004031680A1
Authority
WO
WIPO (PCT)
Prior art keywords
missile
launcher
control system
impact
tracking
Prior art date
Application number
PCT/GB2003/004210
Other languages
English (en)
Inventor
Francis Edward Charles Nurse
Original Assignee
Ams Limited
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 Ams Limited filed Critical Ams Limited
Priority to US10/530,197 priority Critical patent/US20050262993A1/en
Priority to CA002500159A priority patent/CA2500159A1/fr
Priority to EP03748347A priority patent/EP1546637A1/fr
Priority to AU2003267655A priority patent/AU2003267655A1/en
Publication of WO2004031680A1 publication Critical patent/WO2004031680A1/fr

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G3/00—Aiming or laying means
    • F41G3/14—Indirect aiming means
    • F41G3/142—Indirect aiming means based on observation of a first shoot; using a simulated shoot

Definitions

  • the present invention relates to targeting systems and is more particularly concerned with a control system for such systems.
  • a shell is fired from a barrel towards a target and, depending on where the shell lands, the targeting system is adjusted to improve the accuracy of the position of where the next shell fired lands. This process is repeated until a shell hits the target and then no further adjustment is required as subsequent shells should be on target.
  • a method of controlling the operation of a missile launcher which fires free fall ballistics missiles comprising the steps of: a) firing a missile from the missile launcher; b) tracking the trajectory of the fired missile; c) calculating a predicted point of impact of the missile after it reaches its trajectory apogee; d) feeding back the predicted point of impact to the missile launcher before the missile impacts; e) applying a correction prior to firing a subsequent missile; and f) repeating steps a) to e) until the missile impacts a chosen target.
  • step d) comprises feeding back the predicted range of the missile.
  • a control system for a free fall ballistics missile fired from a missile launcher including:- tracking means for tracking the trajectory of a missile fired from the missile launcher; calculation means for calculating a predicted point of impact of the missile, the calculation means being operable immediately after the missile reaches its trajectory apogee; and feedback means for feeding back the predicted point of impact to the missile launcher so that a correction can be applied before the fired missile makes impact prior to the launch of subsequent missile.
  • the calculation means comprises a processor connected to receive data from the tracking means and to provide data relating to the predicted point of impact in the form of range information. It is preferred that the processor includes the feedback means.
  • the tracking means comprises a tracking radar system which recognises the missile as it is fired from the missile launcher.
  • a targeting system including a control system as described above.
  • Figure 1 illustrates a missile launcher firing a missile towards a target in accordance with the present invention
  • Figure 2 is a block diagram of a control system in accordance with present invention.
  • a target 10 is shown being fired upon by a launcher system 12.
  • the target 10 may comprise a first ship and the launcher system 12 may be mounted on a platform located on land or on another ship. Only the barrel 14 of the launcher system 12 is shown for clarity.
  • the launcher system 12 When the target 10 is determined to be hostile and it is decided to fire on it, the launcher system 12 is positioned so that the barrel 14 is angled in position 14a to fire a shell 16a which follows a trajectory 18a.
  • the trajectory
  • a radar system (not shown) associated with the launcher system 12 tracks the shell 16a as it exits barrel 14a until it reaches the apogee 20a of its trajectory. From the data collected by the radar system up to the apogee 20a, it is possible to calculate the landing position 22a before the shell 16a reaches that position, and hence provide a range correction, ⁇ Ri, for the launcher system 12. This range correction effectively moves the barrel 14 to position 14b ready to fire another shell 16b before shell 16a hits position 22a.
  • Shell 16b follows trajectory 18b and has an apogee at 20b. However, although landing position 22b of shell 16b is nearer the ship 10, a further range correction, ⁇ R 2 , is required. As before, the further range correction is calculated before shell 16b reaches landing position 22b, and is applied to move the barrel 14 to position 14c ready to fire a further shell 16c before shell 16b hits position 22b.
  • Shell 16c follows trajectory 18c and has an apogee at 20c. In this case, it is calculated that landing position 22c of shell 16c is coincidental with the ship
  • the control system 30 comprises a target acquisition unit 32 which provides initial targeting instructions for a launcher control unit 34 which launches a shell 16a from a barrel 14 ( Figure 1).
  • the launcher control unit 34 is connected to a tracking radar unit 36 and a processor unit 38.
  • the target acquisition unit 32 is also connected to tracking radar unit 36 and the processor unit 38 as shown.
  • the target acquisition unit 32 When the target acquisition unit 32 provides the initial targeting instructions to the launcher control unit 34 via link 40, it provides the same instructions to the tracking radar unit 36 and the processor unit 38 via links 42 and 44 respectively. These instructions establish the starting point from which the tracking radar unit 36 provides data relating to the trajectory of a shell which is launched using those instructions, and from which the processor unit 38 calculates the range correction data for the launcher control unit 34.
  • the launcher control unit 34 provides data relating to the shell (not shown) which is to be launched by the launcher (not shown) to the tracking radar unit 36 over the link 46. This data provides the tracking radar unit 36 with details of how to recognise the shell which it is to track before or as the shell is launched.
  • the launcher control unit 34 also provides data relating to launch of the shell to the processor unit 38 over link 48.
  • Data from the tracking radar unit 36 is fed via link 50 to the processor unit 38, so that the processor unit 38 can calculate the predicted location of the shell impact once the apogee of the trajectory of the shell has been achieved, and provide range correction data for the launcher control unit 34 over link 52. It will be appreciated that once the tracking radar unit 36 has established a settled track on a shell which has been launched from a launcher (not shown) associated with the launcher control unit 34, the data sent to the processor unit 38 from that settled track allows the predicted shell impact location to be determined with some accuracy.
  • the accuracy of the predicted shell impact location will improve as a function of time, and it has been determined that a while after the shell has reached the apogee of its trajectory, the accuracy of the predicted shell impact location is adequate to use as the basis for a feedback signal for the launcher control unit 34 to correct the elevation of the barrel of the launcher.
  • This has the advantage that the predicted range of the shell is known at a time considerably before the shell impacts and the launch control unit 34 can apply a correction to a second shell from a shell which is yet to land. It will readily be understood that a filtering process can be used to provide a best estimate of the predicted shell impact location.
  • the system of the present invention has the advantage that the number of shells which need to be fired in an engagement, from the start of the engagement to hitting the target, can be substantially reduced. The time involved is also reduced. This, in turn, has the advantage that barrel life of the launcher can be extended in proportion.
  • the present invention has been described with reference to determining the landing position of a shell, it will be understood that the invention can be applied to any free fall ballistics missile. Furthermore, the invention can be used with any stationary or relatively slowly-moving target.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Abstract

L'invention concerne un procédé permettant de commander le fonctionnement d'un lance-missiles (12), au moyen de la prévision de la position d'atterrissage (22) d'un missile (16) en vol, avant son atterrissage. Ledit procédé comprend la localisation du missile (16), lorsqu'il effectue sa trajectoire (18), jusqu'à ce qu'il atteigne le sommet de sa trajectoire (20), et le calcul de la position d'atterrissage (22), ce qui permet d'envoyer un signal de correction de réaction au lance-missiles (12) pour le prochain missile à lancer. Grâce à l'utilisation dudit signal de correction de réaction de cette manière, le temps nécessaire pour atteindre une cible (10) est sensiblement réduit par rapport au temps d'enclenchement.
PCT/GB2003/004210 2002-10-03 2003-09-30 Ameliorations apportees a des systemes de choix des objectifs WO2004031680A1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
US10/530,197 US20050262993A1 (en) 2002-10-03 2003-09-30 Targeting systems
CA002500159A CA2500159A1 (fr) 2002-10-03 2003-09-30 Ameliorations apportees a des systemes de choix des objectifs
EP03748347A EP1546637A1 (fr) 2002-10-03 2003-09-30 Ameliorations apportees a des systemes de choix des objectifs
AU2003267655A AU2003267655A1 (en) 2002-10-03 2003-09-30 Improvements in or relating to targeting systems

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB0223437.5 2002-10-03
GBGB0223437.5A GB0223437D0 (en) 2002-10-03 2002-10-03 Improvements in or relating to targeting systems

Publications (1)

Publication Number Publication Date
WO2004031680A1 true WO2004031680A1 (fr) 2004-04-15

Family

ID=9945576

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/GB2003/004210 WO2004031680A1 (fr) 2002-10-03 2003-09-30 Ameliorations apportees a des systemes de choix des objectifs

Country Status (6)

Country Link
US (1) US20050262993A1 (fr)
EP (1) EP1546637A1 (fr)
AU (1) AU2003267655A1 (fr)
CA (1) CA2500159A1 (fr)
GB (1) GB0223437D0 (fr)
WO (1) WO2004031680A1 (fr)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2007008186A1 (fr) * 2004-03-29 2007-01-18 Honeywell International Inc. Procedes et systemes d'estimation de l'efficacite d'armes
US8845442B2 (en) 2005-03-03 2014-09-30 Trackman A/S Determination of spin parameters of a sports ball
US8912945B2 (en) 2004-07-02 2014-12-16 Trackman A/S Method and an apparatus for determining a deviation between an actual direction of a launched projectile and a predetermined direction
US9645235B2 (en) 2005-03-03 2017-05-09 Trackman A/S Determination of spin parameters of a sports ball
US9855481B2 (en) 2009-01-29 2018-01-02 Trackman A/S Systems and methods for illustrating the flight of a projectile
US9958527B2 (en) 2011-12-16 2018-05-01 Trackman A/S Method and a sensor for determining a direction-of-arrival of impingent radiation
US10379214B2 (en) 2016-07-11 2019-08-13 Trackman A/S Device, system and method for tracking multiple projectiles
US10393870B2 (en) 2005-03-03 2019-08-27 Trackman A/S Determination of spin parameters of a sports ball
US10444339B2 (en) 2016-10-31 2019-10-15 Trackman A/S Skid and roll tracking system
US10989791B2 (en) 2016-12-05 2021-04-27 Trackman A/S Device, system, and method for tracking an object using radar data and imager data

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2009094004A1 (fr) * 2007-09-28 2009-07-30 Kevin Michael Sullivan Méthodologie d'alignement de ligne de visée et de correction de points de pointage balistiques à l'aide d'un traceur optique (stroboscope)
US8074555B1 (en) * 2008-09-24 2011-12-13 Kevin Michael Sullivan Methodology for bore sight alignment and correcting ballistic aiming points using an optical (strobe) tracer
IL204455A (en) * 2010-03-14 2015-03-31 Shlomo Cohen Artillery firing system and method
US10565629B2 (en) * 2011-10-11 2020-02-18 Carrier Services Group, Inc. Computerized valuation of electronic equipment
US9677864B1 (en) * 2014-11-19 2017-06-13 Orbital Research Inc. Closed, self-contained ballistic apogee detection module and method
CN111912289A (zh) * 2020-08-10 2020-11-10 安徽信息工程学院 一种自行式电磁火炮控制系统、方法和装置

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0261091A2 (fr) * 1986-09-17 1988-03-23 Aktiebolaget Bofors Méthode et dispositif de poursuite de missile
WO1990008936A1 (fr) * 1989-01-24 1990-08-09 Contraves Ag Procede et dispositif d'amelioration de la precision du tir
WO1998014747A1 (fr) * 1996-10-03 1998-04-09 Barr & Stroud Limited Systeme de visee de cible

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SE463990B (sv) * 1989-06-28 1991-02-18 Bofors Ab Anordning foer att medelst snabbskjutande pjaes effektuera beskjutning av ett maal
US5140329A (en) * 1991-04-24 1992-08-18 Lear Astronics Corporation Trajectory analysis radar system for artillery piece

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0261091A2 (fr) * 1986-09-17 1988-03-23 Aktiebolaget Bofors Méthode et dispositif de poursuite de missile
WO1990008936A1 (fr) * 1989-01-24 1990-08-09 Contraves Ag Procede et dispositif d'amelioration de la precision du tir
WO1998014747A1 (fr) * 1996-10-03 1998-04-09 Barr & Stroud Limited Systeme de visee de cible

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2007008186A1 (fr) * 2004-03-29 2007-01-18 Honeywell International Inc. Procedes et systemes d'estimation de l'efficacite d'armes
US8912945B2 (en) 2004-07-02 2014-12-16 Trackman A/S Method and an apparatus for determining a deviation between an actual direction of a launched projectile and a predetermined direction
US9857459B2 (en) 2004-07-02 2018-01-02 Trackman A/S Method and an apparatus for determining a deviation between an actual direction of a launched projectile and a predetermined direction
US10052542B2 (en) 2004-07-02 2018-08-21 Trackman A/S Systems and methods for coordinating radar data and image data to track a flight of a projectile
US10473778B2 (en) 2004-07-02 2019-11-12 Trackman A/S Method and an apparatus for determining a deviation between an actual direction of a launched projectile and a predetermined direction
US10393870B2 (en) 2005-03-03 2019-08-27 Trackman A/S Determination of spin parameters of a sports ball
US8845442B2 (en) 2005-03-03 2014-09-30 Trackman A/S Determination of spin parameters of a sports ball
US9645235B2 (en) 2005-03-03 2017-05-09 Trackman A/S Determination of spin parameters of a sports ball
US9855481B2 (en) 2009-01-29 2018-01-02 Trackman A/S Systems and methods for illustrating the flight of a projectile
US10315093B2 (en) 2009-01-29 2019-06-11 Trackman A/S Systems and methods for illustrating the flight of a projectile
US9958527B2 (en) 2011-12-16 2018-05-01 Trackman A/S Method and a sensor for determining a direction-of-arrival of impingent radiation
US10379214B2 (en) 2016-07-11 2019-08-13 Trackman A/S Device, system and method for tracking multiple projectiles
US10444339B2 (en) 2016-10-31 2019-10-15 Trackman A/S Skid and roll tracking system
US10989791B2 (en) 2016-12-05 2021-04-27 Trackman A/S Device, system, and method for tracking an object using radar data and imager data

Also Published As

Publication number Publication date
US20050262993A1 (en) 2005-12-01
GB0223437D0 (en) 2003-02-26
AU2003267655A1 (en) 2004-04-23
CA2500159A1 (fr) 2004-04-15
EP1546637A1 (fr) 2005-06-29

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