EP1546637A1 - Improvements in or relating to targeting systems - Google Patents

Improvements in or relating to targeting systems

Info

Publication number
EP1546637A1
EP1546637A1 EP03748347A EP03748347A EP1546637A1 EP 1546637 A1 EP1546637 A1 EP 1546637A1 EP 03748347 A EP03748347 A EP 03748347A EP 03748347 A EP03748347 A EP 03748347A EP 1546637 A1 EP1546637 A1 EP 1546637A1
Authority
EP
European Patent Office
Prior art keywords
missile
launcher
control system
impact
tracking
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.)
Withdrawn
Application number
EP03748347A
Other languages
German (de)
French (fr)
Inventor
Francis Edward Charles AMS Radar Systems NURSE
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.)
BAE Systems Integrated System Technologies Ltd
Original Assignee
AMS Ltd
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 Ltd filed Critical AMS Ltd
Publication of EP1546637A1 publication Critical patent/EP1546637A1/en
Withdrawn legal-status Critical Current

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

Described herein is a method of controlling the operation of a missile launcher (12) by predicting the landing position (22) of a missile (16) in flight before it lands. The method includes tracking the missile (16) as it travels along its trajectory (18) until it reaches its apogee (20) and calculating the landing position (22) to provide a feedback correction signal to launcher (12) for the next missile to be launched. By utilising a feedback correction signal in this way, the time to hitting a target (10) from the time of engagement is substantially reduced.

Description

IMPROVEMENTS IN OR RELATING TO TARGETING SYSTEMS
The present invention relates to targeting systems and is more particularly concerned with a control system for such systems.
In conventional targeting 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.
As the time to acquire an exact 'lock' on the target may be protracted, a number of shells may be wasted in the process of acquiring the range to hit the target. This has the consequence of reducing the overall life of the barrel from which the shell is fired.
It is therefore an object of the present invention to provide an improved targeting system which overcomes the disadvantages mentioned above. In accordance with one aspect of the present invention, there is provided a method of controlling the operation of a missile launcher which fires free fall ballistics missiles, the method 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.
Advantageously, step d) comprises feeding back the predicted range of the missile. ln accordance with a second aspect of the present invention, there is provided a control system for a free fall ballistics missile fired from a missile launcher, the control system 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.
Advantageously, 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.
In one embodiment of the present invention, the tracking means comprises a tracking radar system which recognises the missile as it is fired from the missile launcher.
In accordance with a further aspect of the present invention, there is provided a targeting system including a control system as described above.
For a better understanding of the present invention, reference will now be made, by way of example only, to the accompanying drawings in which:-
Figure 1 illustrates a missile launcher firing a missile towards a target in accordance with the present invention; and Figure 2 is a block diagram of a control system in accordance with present invention.
Referring initially to Figure 1 , a target 10 is shown being fired upon by a launcher system 12. For example, 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.
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
18a passes through an apogee 20a before splashing down at 22a and misses the ship 10.
In accordance with the present invention, 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, ΔRi, 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, ΔR2, 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
10 before shell 16c reaches that position and at least one further shell (not shown) can be directed along substantially the same trajectory as trajectory 18c to impact the ship 10.
Turning now to Figure 2, a block diagram illustrating a control system 30 for launcher 12 of Figure 1 is shown. 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.
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.
Moreover, 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.
Although 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.

Claims

1. A method of controlling the operation of a missile launcher which fires free fall ballistics missiles, the method 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.
2. A method according to claim 1 , wherein step d) comprises feeding back the predicted range of the missile.
3. A control system for a free fall ballistics missile fired from a missile launcher, the control system 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.
4. A control system according to claim 3, wherein 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.
5. A control system according to claim 4, wherein the processor includes the feedback means.
6. A control system according to any one of claims 3 to 5, wherein the tracking means comprises a tracking radar system.
7. A control system according to claim 6, wherein the tracking radar system recognises the missile as it is fired from the missile launcher.
8. A targeting system including a control system according to any one of claims 3 to 7.
9. A method of controlling the operation of a missile launcher substantially as hereinbefore described with reference to the accompanying drawings.
10. A control system substantially as hereinbefore described with reference to the accompanying drawings.
EP03748347A 2002-10-03 2003-09-30 Improvements in or relating to targeting systems Withdrawn EP1546637A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
GBGB0223437.5A GB0223437D0 (en) 2002-10-03 2002-10-03 Improvements in or relating to targeting systems
GB0223437 2002-10-03
PCT/GB2003/004210 WO2004031680A1 (en) 2002-10-03 2003-09-30 Improvements in or relating to targeting systems

Publications (1)

Publication Number Publication Date
EP1546637A1 true EP1546637A1 (en) 2005-06-29

Family

ID=9945576

Family Applications (1)

Application Number Title Priority Date Filing Date
EP03748347A Withdrawn EP1546637A1 (en) 2002-10-03 2003-09-30 Improvements in or relating to targeting systems

Country Status (6)

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

Families Citing this family (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7121183B2 (en) * 2004-03-29 2006-10-17 Honeywell International Inc. Methods and systems for estimating weapon effectiveness
EP3098624A1 (en) 2004-07-02 2016-11-30 Trackman A/S A method and apparatus for determining a deviation between an actual direction of a launched projectile and a predetermined direction
ATE471746T1 (en) 2005-03-03 2010-07-15 Interactive Sports Games As 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
US10393870B2 (en) 2005-03-03 2019-08-27 Trackman A/S Determination of spin parameters of a sports ball
WO2009094004A1 (en) * 2007-09-28 2009-07-30 Kevin Michael Sullivan Methodology for bore sight alignment and correcting ballistic aiming points using an optical (strobe) tracer
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
KR101845503B1 (en) 2009-01-29 2018-04-04 트랙맨 에이/에스 An assembly comprising a radar and an imaging element
IL204455A (en) * 2010-03-14 2015-03-31 Shlomo Cohen System and method for registration of artillery fire
US10565629B2 (en) * 2011-10-11 2020-02-18 Carrier Services Group, Inc. Computerized valuation of electronic equipment
EP2605036B1 (en) 2011-12-16 2019-10-23 Trackman A/S A method and a sensor for determining a direction-of-arrival of impingent radiation
US9677864B1 (en) * 2014-11-19 2017-06-13 Orbital Research Inc. Closed, self-contained ballistic apogee detection module and method
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
CN111912289A (en) * 2020-08-10 2020-11-10 安徽信息工程学院 A self-propelled electromagnetic artillery control system, method and device

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SE460501B (en) * 1986-09-17 1989-10-16 Bofors Ab SET UP AND DEVICE TO FOLLOW A ROCKET PROJECT IN ITS RANGE
EP0411073A1 (en) * 1989-01-24 1991-02-06 Contraves Ag Process and device for improving the accuracy of aim
SE463990B (en) * 1989-06-28 1991-02-18 Bofors Ab DEVICE MEASURING EFFECTIVE SHOOTING OF A TARGET
US5140329A (en) * 1991-04-24 1992-08-18 Lear Astronics Corporation Trajectory analysis radar system for artillery piece
GB9620614D0 (en) * 1996-10-03 1997-03-12 Barr & Stroud Ltd Target aiming system

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2004031680A1 *

Also Published As

Publication number Publication date
US20050262993A1 (en) 2005-12-01
AU2003267655A1 (en) 2004-04-23
GB0223437D0 (en) 2003-02-26
CA2500159A1 (en) 2004-04-15
WO2004031680A1 (en) 2004-04-15

Similar Documents

Publication Publication Date Title
US20050262993A1 (en) Targeting systems
US8288698B2 (en) Method for correcting the trajectory of terminally guided ammunition
KR101919883B1 (en) Intelligent Closed-loop System for correcting impact point
EP0138942B1 (en) Means for reducing spread of shots in a weapon system
WO2002101317A3 (en) Precision-guided hypersonic projectile weapon system
US6467721B1 (en) Process for the target-related correction of a ballistic trajectory
GB2325044A (en) Pilot projectile and method for artillery ranging
KR20130109017A (en) A method of guiding a salvo of guided projectiles to a target, a system and a computer program product
KR102924735B1 (en) Method, computer program and weapon system for calculating the rupture point of a projectile
JP2662042B2 (en) Path correction system for wireless correction of the path of the launched projectile
EP0261091A2 (en) A method and an apparatus for tracking a missile in its trajectory
GB2073382A (en) Method of compensation for target location changes when firing ballistic missiles
US11300670B2 (en) Weapon on-board velocity and range tracking
KR100653341B1 (en) How to modify ballistics by target
JPH10122793A (en) Method for aiming gun according to trajectory locus, aiming apparatus and firearm controller
US6488231B1 (en) Missile-guidance method
US20220412693A1 (en) Method to combat a target
RU2188381C2 (en) Method for command telecontrol of missile
KR102467374B1 (en) Apparatus and method for controlling fire on surface ship
KR102312652B1 (en) Guided missile system and operation method of the same
KR102312653B1 (en) Guided weapon system using weather data and operation method of the same
TR2022014253A1 (en) ORBITAL INCLINE METHOD AND SYSTEM FOR INCREASING THE HIT PRECISION OF SPIN STABILIZED ARTILLERY AMMUNITIONS
GB1571811A (en) Ballistic fire control systems
WO2001094871A3 (en) Fire control method and system
JPS58219400A (en) Predicting system of trajectory of next ball

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IT LI LU MC NL PT RO SE SI SK TR

17P Request for examination filed

Effective date: 20050715

R17P Request for examination filed (corrected)

Effective date: 20050715

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20080402