EP0054489A1 - Procédé de pointage du canon d'une arme à feu et dispositif pour la mise en oeuvre de ce procédé - Google Patents

Procédé de pointage du canon d'une arme à feu et dispositif pour la mise en oeuvre de ce procédé Download PDF

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Publication number
EP0054489A1
EP0054489A1 EP81401982A EP81401982A EP0054489A1 EP 0054489 A1 EP0054489 A1 EP 0054489A1 EP 81401982 A EP81401982 A EP 81401982A EP 81401982 A EP81401982 A EP 81401982A EP 0054489 A1 EP0054489 A1 EP 0054489A1
Authority
EP
European Patent Office
Prior art keywords
target
sight
line
time
ammunition
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Withdrawn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
EP81401982A
Other languages
German (de)
English (en)
French (fr)
Inventor
Yves Kocher
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.)
D'OPTIQUE PRECISION ELECTRONIQUE ET MECANIQUE - SOPELEM Ste
Societe dOptique Precision Electronique et Mecanique SOPELEM SA
Original Assignee
D'OPTIQUE PRECISION ELECTRONIQUE ET MECANIQUE - SOPELEM Ste
Societe dOptique Precision Electronique et Mecanique SOPELEM SA
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 D'OPTIQUE PRECISION ELECTRONIQUE ET MECANIQUE - SOPELEM Ste, Societe dOptique Precision Electronique et Mecanique SOPELEM SA filed Critical D'OPTIQUE PRECISION ELECTRONIQUE ET MECANIQUE - SOPELEM Ste
Publication of EP0054489A1 publication Critical patent/EP0054489A1/fr
Withdrawn legal-status Critical Current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
    • F41G3/06—Aiming or laying means with rangefinder
    • F41G3/065—Structural association of sighting-devices with laser telemeters

Definitions

  • the present invention relates to a method and a device for pointing the barrel of a firearm by means of an offset between the line of sight and the line of fire taking account in particular of the mobility of the target.
  • the mobility of the target is also a pointing parameter.
  • attempts have been made to take into account the transverse or lateral speed of the target. From the distance from the target evaluated by telemetry, the flight time of the munition is determined. The direction of sight remaining pointed at the target, the telescope is moved in rotation so as to measure the angular deviation in bearing traveled by the target in a period of time depending on the flight time of the ammunition. The average angular velocity can thus be determined. The axis of fire is pointed in front of the target relative to the direction of sight with, in bearing, an angular difference equal to the average angular speed of the target multiplied by the time of flight of the ammunition.
  • the known fire control devices do not take into account the radial speed of the target, that is to say the speed of the target in a direction joining the target to the weapon. As a result, there is a difference between the position of the target at the time when the telemetry measurement is carried out allowing the calculation of the increase and the effective position of the target at the time when the ammunition arrives at this measured position.
  • the present invention relates to a method and a device for pointing the barrel of a weapon making it possible in particular to take account of the radial speed of the target in order to adjust accordingly the angular offset of the line of fire with the line of sight. This correction is determined by two distance measurements only, which allows the use of a simple laser rangefinder.
  • the method according to the invention uses a laser and a telescopic sight equipped with a movable sight reticle capable of displacing the line of sight in elevation, and it is - essentially characterized by the fact that it consists in controlling the laser rangefinder so that it performs - two measurements of the distance from the target at two instants separated by a period of time, to be calculated , by means of these distance measurements and the time interval between these measurements, the radial speed of the target, to calculate the radial position of the target at the end of the flight time of the ammunition, to control the displacement of the aiming reticle to an increase value corresponding to the calculated distance from the target at an instant covering the duration of repointing of the line of sight on the target and the duration of flight of the ammunition and repoin the line of sight on target.
  • the method consists in moving the line of sight while remaining pointed at the target in order to measure the lateral speed of the target and in ordering the first telemetry measurement at the start of this tracking sequence and in ordering the second measurement from telemetry at the end of this chase sequence.
  • the method consists in determining the radial distance from the target continuously as a function of time.
  • the method consists in calculating the radial distance from the target at an instant covering a predetermined duration necessary for the repointing of the line of sight on the target and the duration of flight of the ammunition.
  • the device for implementing the method according to the invention comprises a laser rangefinder and a telescopic sight equipped with a movable aiming reticle capable of displacing the line of sight in elevation and it is essentially characterized in that it comprises means for controlling two laser telemetries separated by a period of time, means for calculating the average radial speed of the target, the radial distance from the target at the end of the flight time of the ammunition, the increase value corresponding to this calculated radial distance, means for controlling the movement of the sighting reticle as a function of this increase value.
  • the single figure is a schematic view of the pointing device according to the invention.
  • the pointing device represented by the appended figure comprises a laser scope and rangefinder assembly 1 mounted on a stand 61 by relation to which it can pivot around two orthogonal axes, one of which is substantially vertical.
  • the riflescope comprises, from front to rear, a porthole 12, a lens 13, a narrative 14, a reticle 15 and an eyepiece 16. These different components are centered on the optical axis 11 of the rifle which is moreover provided, in a manner known per se, with optical conveying and reflectors.
  • the objective 13 is movable in a direction perpendicular to the vertical axis of rotation of the telescope-rangefinder assembly and perpendicular to the optical axis 11.
  • the sighting reticle 15 can be moved in a direction perpendicular to the direction of movement of the objective 13 and perpendicular to the optical axis 11. It is provided with a line of sight perpendicular to the direction of its movement.
  • the reticle 15 cooperates with the reticle 14 defining a vertical line of sight and provided with a simbleautage mark defining the reference line of sight which is parallel to the axis of the barrel.
  • the movement of the objective 13 deflects the line of sight in field.
  • the movement of the aiming reticle 15 deflects the line of sight in elevation.
  • the movement of the target reticle5 is controlled by a position control comprising a motor 21 which linearly displaces this reticle by means of a known mechanism transforming the rotary movement of the motor shaft into linear movement.
  • This motor 21 is coupled in rotation to a potentiometer or servo encoder 22.
  • the motor control signal 21 comes from the output of an amplifier 24 receiving on the one hand the signal coming from the potentiometer 22 and on the other hand share a control signal.
  • the displacement in bearing of the objective 13 is controlled by a position control comprising a motor 31 which linearly displaces this objective by means of a mechanism transforming the rotary movement of the motor shaft into linear movement.
  • This motor 31 is rotatably coupled to a potentiometer or servo encoder 32.
  • the motor control signal comes from the output of an amplifier 34 receiving on the one hand the signal from potentiometer 32 and a control signal.
  • the telescope is associated with a laser rangefinder whose laser material is glass and which does not include a cooling system.
  • This laser does not work by close pulses and is distinguished in this from the cadence laser. It comprises a laser emitter emitting the beam sebn a direction 41 parallel to the reference sighting direction and on the other hand a laser receiver receiving the laser beam in a direc tion 51 parallel to the direction of emission 41.
  • the laser receiver comprises, in a known manner, an optic 52-53 centered on the axis 51 and focusing the beam backscattered by the target on a photosensitive reception sensor 54 constituted by example by a photo-diode,
  • the rotation of the telescope-rangefinder-barrel assembly around the vertical axis of the stand 61 is identified by a position encoder 62 called "lateral tachymetry". This position encoder is of the incremental type.
  • the control signals to the position servos of the objective 13 and of the reticle 15 are supplied by the control and calculation unit 7.
  • This unit controls the laser generator (arming and triggering of the laser emission) and receives the signal. of the laser receiver allowing the acquisition of the distance data. It controls the display of the distance on a display module. It receives the signal from the lateral tachometer encoder 62 and the signals from other sensors. Depending on the measured distance from the target, it deduces the flight time of the ammunition from the firing table that has been stored. The integration of the pulses from the encoder 62 is carried out for a time equal to the flight time of the ammunition. This makes it possible to calculate the angular offset in bearing due to the lateral speed of the target.
  • the duration of repointing the line of sight on the target can be a predetermined value corresponding to an average value of the time necessary for a shooter to perform this operation.
  • the signal applied to the rise servo has then a determined value invariable in time.
  • the signal applied to the rising servo can also vary continuously over time.
  • the radial distance is then continuously calculated and the rise signal determined by the firing table varies continuously with the distance itself varying continuously as a function of time.
  • the control and calculation unit 7 comprises a microprocessor 76, a memory RAM77 and a memory RCM 78. It controls the laser generator by an interface circuit 72. It receives the signal from the sensor 54 of the laser receiver by a circuit d interface 73. It controls the servo in position of the lens 13 by a digital analog converter 71 and controls the servo in position of the reticle 15 by a digital analog converter 74. It receives the signal from the position encoder 62 by a interface circuit 75.
  • control unit 7 instead of being produced from a microprocessor-based microcomputer could be produced by an automation and analog calculation system.

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  • Physics & Mathematics (AREA)
  • Optics & Photonics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Optical Radar Systems And Details Thereof (AREA)
EP81401982A 1980-12-12 1981-12-11 Procédé de pointage du canon d'une arme à feu et dispositif pour la mise en oeuvre de ce procédé Withdrawn EP0054489A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8026464 1980-12-12
FR8026464A FR2496251A1 (fr) 1980-12-12 1980-12-12 Procede de pointage du canon d'une arme a feu et dispositif pour la mise en oeuvre de ce procede

Publications (1)

Publication Number Publication Date
EP0054489A1 true EP0054489A1 (fr) 1982-06-23

Family

ID=9249036

Family Applications (1)

Application Number Title Priority Date Filing Date
EP81401982A Withdrawn EP0054489A1 (fr) 1980-12-12 1981-12-11 Procédé de pointage du canon d'une arme à feu et dispositif pour la mise en oeuvre de ce procédé

Country Status (2)

Country Link
EP (1) EP0054489A1 (enrdf_load_stackoverflow)
FR (1) FR2496251A1 (enrdf_load_stackoverflow)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0418062A3 (en) * 1989-09-12 1993-01-13 Astra Holdings Plc Lead computing sight
GB2284653A (en) * 1990-07-23 1995-06-14 Aerospatiale Weapon system for detecting and countering an aerial threat
RU2150068C1 (ru) * 1999-02-22 2000-05-27 АООТ "ОКБ Сухого" Прицельная система самолета
RU2150069C1 (ru) * 1999-02-22 2000-05-27 АООТ "ОКБ Сухого" Прицельная система самолета с лазерным дальномером
RU2158407C1 (ru) * 1999-02-22 2000-10-27 АООТ "ОКБ Сухого" Оптикоэлектронная прицельная система самолета
RU2158406C1 (ru) * 1999-02-22 2000-10-27 АООТ "ОКБ Сухого" Оптикоэлектронная прицельная система самолета
RU2312296C1 (ru) * 2006-07-31 2007-12-10 Василий Васильевич Ефанов Оптико-электронная прицельная система самолета
RU2344969C1 (ru) * 2007-05-15 2009-01-27 Василий Васильевич Ефанов Оптикоэлектронная прицельная система самолета

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2737344A (en) * 1948-08-26 1956-03-06 Lewis M Mott-Smith Range and range-rate indicating unit
CH338121A (fr) * 1955-03-18 1959-04-30 Joyau Guy Dispositif de pointage pour déterminer la position d'un point de l'espace
US3694095A (en) * 1970-08-05 1972-09-26 Ltv Aerospace Corp Fire control system
FR2197458A5 (enrdf_load_stackoverflow) * 1971-12-17 1974-03-22 Hughes Aircraft Co

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2737344A (en) * 1948-08-26 1956-03-06 Lewis M Mott-Smith Range and range-rate indicating unit
CH338121A (fr) * 1955-03-18 1959-04-30 Joyau Guy Dispositif de pointage pour déterminer la position d'un point de l'espace
US3694095A (en) * 1970-08-05 1972-09-26 Ltv Aerospace Corp Fire control system
FR2197458A5 (enrdf_load_stackoverflow) * 1971-12-17 1974-03-22 Hughes Aircraft Co

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0418062A3 (en) * 1989-09-12 1993-01-13 Astra Holdings Plc Lead computing sight
GB2284653A (en) * 1990-07-23 1995-06-14 Aerospatiale Weapon system for detecting and countering an aerial threat
GB2284653B (en) * 1990-07-23 1996-01-17 Aerospatiale System for detecting and countering an aerial threat
RU2150068C1 (ru) * 1999-02-22 2000-05-27 АООТ "ОКБ Сухого" Прицельная система самолета
RU2150069C1 (ru) * 1999-02-22 2000-05-27 АООТ "ОКБ Сухого" Прицельная система самолета с лазерным дальномером
RU2158407C1 (ru) * 1999-02-22 2000-10-27 АООТ "ОКБ Сухого" Оптикоэлектронная прицельная система самолета
RU2158406C1 (ru) * 1999-02-22 2000-10-27 АООТ "ОКБ Сухого" Оптикоэлектронная прицельная система самолета
RU2312296C1 (ru) * 2006-07-31 2007-12-10 Василий Васильевич Ефанов Оптико-электронная прицельная система самолета
RU2344969C1 (ru) * 2007-05-15 2009-01-27 Василий Васильевич Ефанов Оптикоэлектронная прицельная система самолета

Also Published As

Publication number Publication date
FR2496251B1 (enrdf_load_stackoverflow) 1984-09-07
FR2496251A1 (fr) 1982-06-18

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Inventor name: KOCHER, YVES