EP0261091A2 - Verfahren und Vorrichtung zum Verfolgen eines Flugkörpers - Google Patents

Verfahren und Vorrichtung zum Verfolgen eines Flugkörpers Download PDF

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Publication number
EP0261091A2
EP0261091A2 EP87850265A EP87850265A EP0261091A2 EP 0261091 A2 EP0261091 A2 EP 0261091A2 EP 87850265 A EP87850265 A EP 87850265A EP 87850265 A EP87850265 A EP 87850265A EP 0261091 A2 EP0261091 A2 EP 0261091A2
Authority
EP
European Patent Office
Prior art keywords
sensor
rocket
projectile
trajectory
rocket projectile
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Withdrawn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
EP87850265A
Other languages
English (en)
French (fr)
Other versions
EP0261091A3 (de
Inventor
Peter Dahlström
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.)
Saab Bofors AB
Original Assignee
Bofors AB
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 Bofors AB filed Critical Bofors AB
Publication of EP0261091A2 publication Critical patent/EP0261091A2/de
Publication of EP0261091A3 publication Critical patent/EP0261091A3/de
Withdrawn legal-status Critical Current

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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 a method and an apparatus for tracking a missile during at least the first part of its trajectory.
  • the invention is primarily intended for utilization in the calculation of requisite trajectory corrections for artillery missiles in respect of, above all, ground winds in order that the missile make a hit within a predetermined target area.
  • artillery missiles is here intended to mean unguided missiles which are discharged in ballistic trajectories towards determined targets. Such artillery missiles are often discharged in salvoes for blanket bombardment. Initially, the aiming and direction of such artillery missiles towards their respective targets are effected by the launcher in compliance with theoretical ballistic calculations supplemented with measured correctional values in respect of wind forces etc. within the contemplated missile trajectory. Such artillery missiles may also be provided with means for course correction during the final - or homing - part of their trajectory without, as a result, being classified as guided missiles, since these latter are guided throughout all or the major part of their trajectory.
  • artillery missiles are highly sensitive to the effect of the wind, primarily during the first part of their trajectory while the motor is burning and the rocket is accelerating. While anemometrical indications and measurement of ground wind speed may provide a basis for adjusting or correcting the direction of discharge of the missile, a considerable amount of uncertainty remains because such anemometrical indication cannot - for practical reasons - be effected in immediate conjunction with launching, or discharge, of the missile, and because ground wind speed is not representative of the velocity of the wind throughout the entire range of altitude through which the missile passes during that time when the motor is burning.
  • One prior art method of reducing the influence of the wind is to discharge a test missile and track it by radar. By comparing the calculated trajectory with the physically measured trajectory, a correction may be introduced which reduces the deviation for a subsequent salvo to a minimum.
  • the test rocket is normally destroyed before it reaches the target, thereby revealing the contemplated target to the enemy.
  • the present invention calls, instead of the use of the radar echo of the test rocket, for the utilization of the powerful light and IR radiation of the rocket motor nozzle during the burning time of the motor, or alternatively their contrast against the background (the heavens) in order to track, using an IR sensor or TV camera, the rocket during at least the first part of its trajectory.
  • Figs. 1 and 2 show basic dispositions of rocket launchers discharging artillery rockets supplemented with an IR sensor or TV camera of the type contemplated herein; and Fig. 3 shows, on a larger scale, a cross section through the contemplated sensor; while Fig. 4 shows an indicator for direct monitoring of the deviation of the rocket from the reference alignment of the launcher.
  • Fig. 1 schematically illustrates a launcher 1 fitted with an IR sensor or TV camera 2 and a rocket 3 which is at that point along its trajectory where the motor cuts out.
  • the sensor or camera 2 may either be fixedly mounted to the elevating system and register the position of the rocket (the nozzle of the rocket) as a video signal or the like for subsequent image processing, or may be a tracking sensor which, by means of a servo system (not shown) aims the IR or light sensor towards the rocket and measures angular deviations between the sensor and the elevating system of the launcher. Both of these systems utilize prior-art technology.
  • Point E marks the point of destruction of the test rocket.
  • the result may be presented on an image generated by IR or TV technique of the type shown in Fig. 4 where point 10 marks the reference direction of the launcher and point 12 the actual position of the rocket.
  • y and z respectively, thus provide directly readable values of the deviation of the rocket from the reference line of the launcher, which, in its turn, coincides as a rule with the aiming alignment of the rocket launcher.
  • y and z In tracker sensors which, hence, follow or track the trajectory of the rocket projectile, corresponding values y and z will be obtained from angular indicators on the sensor. Irrespective of the type of sensor, y and z are suitably measured at one or a plurality of points along that part of the trajectory of the rocket where its motor is operative. By comparison with the values calculated by fire control, a measure will be obtained of the effect which the ground wind speed - and possibly other sources of disturbance - may have upon the rocket. This information is fed back to fire control for calculation of correctional aiming angles. If it is assumed that the ground wind conditions are the same at the launching site and the target, such calculation may also correctionally compensate for the effects of the groundowner during the homing phase of the ballistic trajectory.
  • Fire control is that function which calculates, either manually or by machine, the trajectories of the rockets. It may be disposed at the launcher or in a separate fire control central unit.
  • Fig. 2 illustrates the same principle as that shown in Fig. 1, but with that difference that the IR or TV sensor has been disposed a distance from the launcher.
  • the sensor is further protected from the rocket flame and those propellant gases which the rocket thrusts rearwardly on launching, but this is at the cost of a problem which occurs in parallel adjustment of the launcher and the sensor.
  • Such adjustment requires certain auxiliary equipment and adds to the entry error from the dispersion in the time-distance relationship of the projectile which always occurs.
  • the tracking may continue even after the motor has cut out. This is particularly possible if a TV sensor or a sensor in the close IR band is employed such that the rocket makes a clear contrast against the heavens. In such cases, the tracking may be extended as far as is permitted by the range of the sensor, which provides a further improved basis for correction of the aiming angles and parameters of the launcher.
  • the protective lid 5 is suitably operated by an electro­mechanical or electro-hydraulic apparatus 6 and is synchronized with the discharge of the rocket 3 such that the lid is closed and protects the optics until such time as the rocket projectile has travelled so far along its trajectory that its propellant gases can no longer damage the optics. Experience has shown that this point along the trajectory is reached well before the cut-out time of the rocket.
  • the senor 2 is provided with a protective casing 4 and a protective lid 5.
  • the opening movement is obtained by the intermediary of a hydraulic cylinder 6 which, via a linkage system 11, is in communication with the protective lid.
  • the hydraulic cylinder receives its operating oil from the hydraulic system of the launcher. Opening is controlled by means of an electro-hydraulic valve 8 in a per se known manner.
  • the hydraulic communication between the launcher and the cylinder is designated 7 in Figs. 1 and 2.
  • the electric communication between the launcher and the valve is designated 9.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Length Measuring Devices By Optical Means (AREA)
EP87850265A 1986-09-17 1987-09-03 Verfahren und Vorrichtung zum Verfolgen eines Flugkörpers Withdrawn EP0261091A3 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
SE8603911A SE460501B (sv) 1986-09-17 1986-09-17 Saett och anordning att foelja en raketprojektil i dess bana
SE8603911 1986-09-17

Publications (2)

Publication Number Publication Date
EP0261091A2 true EP0261091A2 (de) 1988-03-23
EP0261091A3 EP0261091A3 (de) 1989-03-15

Family

ID=20365619

Family Applications (1)

Application Number Title Priority Date Filing Date
EP87850265A Withdrawn EP0261091A3 (de) 1986-09-17 1987-09-03 Verfahren und Vorrichtung zum Verfolgen eines Flugkörpers

Country Status (4)

Country Link
EP (1) EP0261091A3 (de)
BR (1) BR8704785A (de)
IL (1) IL83889A0 (de)
SE (1) SE460501B (de)

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1990008936A1 (de) * 1989-01-24 1990-08-09 Contraves Ag Verfahren und vorrichtung zur verbesserung der treffgenauigkeit
FR2643769A1 (fr) * 1989-02-28 1990-08-31 Aerospatiale Dispositif de restitution de mouvement rapide par observation de mire retroreflechissante et procede pour la mise en oeuvre du dispositif
EP0433538A3 (en) * 1989-12-22 1992-05-20 U.P.F. Di Zanieri Ugo Pietro Optic-electronic telemetry device with variable base
EP0519315A1 (de) * 1991-06-20 1992-12-23 DIEHL GMBH & CO. Einrichtung zur Messung des Höhenprofils eines Bodenwindes
US5454265A (en) * 1991-06-20 1995-10-03 Diehl Gmbh & Co. Installation for the measurement of the altitude of a surface wind, particularly for improving the hitting accuracy of unguided projectiles
WO1997048963A1 (en) * 1996-06-19 1997-12-24 Pylkkaenen Pekka Method for correcting the trajectory of a projectile of a gun, a mortar or a rocket launcher or the like
GB2324360A (en) * 1997-04-18 1998-10-21 Rheinmetall Ind Ag Method and apparatus for aiming a weapon
FR2762905A1 (fr) * 1997-05-05 1998-11-06 Adolf Weber Projectile pilote a assistance gps et procede d'affectation de projectiles actifs sur une zone d'utilisation definie
WO2004031680A1 (en) * 2002-10-03 2004-04-15 Ams Limited Improvements in or relating to targeting systems
WO2011114277A1 (en) * 2010-03-14 2011-09-22 Rafael Advanced Defense Systems Ltd. System and method for registration of artillery fire
US10648775B2 (en) * 2013-03-21 2020-05-12 Nostromo Holdings, Llc Apparatus for correcting ballistic aim errors using special tracers

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN116704389B (zh) * 2022-02-23 2026-01-30 中国科学院长春光学精密机械与物理研究所 一种火箭发射关键事件识别方法、装置及计算机设备

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1253257A (fr) * 1959-12-11 1961-02-10 Dispositif protecteur d'appareil d'observation optique
BE623121A (de) * 1961-10-02
CH501203A (de) * 1969-08-15 1970-12-31 Contraves Ag Schiess-Anlage
FR2181148A5 (de) * 1972-04-19 1973-11-30 Cnim

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1990008936A1 (de) * 1989-01-24 1990-08-09 Contraves Ag Verfahren und vorrichtung zur verbesserung der treffgenauigkeit
FR2643769A1 (fr) * 1989-02-28 1990-08-31 Aerospatiale Dispositif de restitution de mouvement rapide par observation de mire retroreflechissante et procede pour la mise en oeuvre du dispositif
EP0385852A1 (de) * 1989-02-28 1990-09-05 AEROSPATIALE Société Nationale Industrielle Einrichtung zur Wiedergabe von schnellen Bewegungen durch Wahrnehmung einer retroreflektierenden Figur und Verfahren zur Ausführung der Einrichtung
EP0433538A3 (en) * 1989-12-22 1992-05-20 U.P.F. Di Zanieri Ugo Pietro Optic-electronic telemetry device with variable base
EP0519315A1 (de) * 1991-06-20 1992-12-23 DIEHL GMBH & CO. Einrichtung zur Messung des Höhenprofils eines Bodenwindes
US5454265A (en) * 1991-06-20 1995-10-03 Diehl Gmbh & Co. Installation for the measurement of the altitude of a surface wind, particularly for improving the hitting accuracy of unguided projectiles
WO1997048963A1 (en) * 1996-06-19 1997-12-24 Pylkkaenen Pekka Method for correcting the trajectory of a projectile of a gun, a mortar or a rocket launcher or the like
FR2762384A1 (fr) * 1997-04-18 1998-10-23 Rheinmetall Ind Ag Procede de pointage de l'arme d'un systeme d'arme et systeme d'arme pour la mise en oeuvre de ce procede
GB2324360A (en) * 1997-04-18 1998-10-21 Rheinmetall Ind Ag Method and apparatus for aiming a weapon
US6038955A (en) * 1997-04-18 2000-03-21 Rheinmetall W.& M. Gmbh Method for aiming the weapon of a weapon system and weapon system for implementing the method
GB2324360B (en) * 1997-04-18 2001-08-29 Rheinmetall Ind Ag Method and apparatus for aiming a weapon
FR2762905A1 (fr) * 1997-05-05 1998-11-06 Adolf Weber Projectile pilote a assistance gps et procede d'affectation de projectiles actifs sur une zone d'utilisation definie
GB2325044A (en) * 1997-05-05 1998-11-11 Adolf Weber Pilot projectile and method for artillery ranging
US6037899A (en) * 1997-05-05 2000-03-14 Rheinmetall W&M Gmbh Method for vectoring active or combat projectiles over a defined operative range using a GPS-supported pilot projectile
GB2325044B (en) * 1997-05-05 2000-11-15 Adolf Weber Pilot projectile and method for artillery ranging
WO2004031680A1 (en) * 2002-10-03 2004-04-15 Ams Limited Improvements in or relating to targeting systems
WO2011114277A1 (en) * 2010-03-14 2011-09-22 Rafael Advanced Defense Systems Ltd. System and method for registration of artillery fire
US8794119B2 (en) 2010-03-14 2014-08-05 Rafael Advanced Defense Systems Ltd. System and method for registration of artillery fire
US10648775B2 (en) * 2013-03-21 2020-05-12 Nostromo Holdings, Llc Apparatus for correcting ballistic aim errors using special tracers

Also Published As

Publication number Publication date
EP0261091A3 (de) 1989-03-15
SE8603911L (sv) 1988-03-18
IL83889A0 (en) 1988-02-29
BR8704785A (pt) 1988-05-17
SE460501B (sv) 1989-10-16
SE8603911D0 (sv) 1986-09-17

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Inventor name: DAHLSTROEM, PETER