EP0329523A1 - Durch Laserstrahl und pyrotechnische Impulsgeber geführter Vektor - Google Patents

Durch Laserstrahl und pyrotechnische Impulsgeber geführter Vektor Download PDF

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Publication number
EP0329523A1
EP0329523A1 EP89400335A EP89400335A EP0329523A1 EP 0329523 A1 EP0329523 A1 EP 0329523A1 EP 89400335 A EP89400335 A EP 89400335A EP 89400335 A EP89400335 A EP 89400335A EP 0329523 A1 EP0329523 A1 EP 0329523A1
Authority
EP
European Patent Office
Prior art keywords
vector
trajectory
pyrotechnic
ideal trajectory
target
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.)
Granted
Application number
EP89400335A
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English (en)
French (fr)
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EP0329523B1 (de
Inventor
Philippe Arnaud
Marc Bernard
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.)
Thomson Brandt Armements SA
Original Assignee
Thomson Brandt Armements SA
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Publication date
Application filed by Thomson Brandt Armements SA filed Critical Thomson Brandt Armements SA
Publication of EP0329523A1 publication Critical patent/EP0329523A1/de
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Publication of EP0329523B1 publication Critical patent/EP0329523B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/24—Beam riding guidance systems
    • F41G7/26—Optical guidance systems
    • F41G7/266—Optical guidance systems for spin-stabilized missiles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/60—Steering arrangements
    • F42B10/66—Steering by varying intensity or direction of thrust
    • F42B10/661—Steering by varying intensity or direction of thrust using several transversally acting rocket motors, each motor containing an individual propellant charge, e.g. solid charge

Definitions

  • the invention relates to a guidance system, by laser beam and pyrotechnic boosters, of one or more vectors, intended for the interception of maneuvering targets such as planes, helicopters or tanks. It also relates to a vector suitable for guiding by such a system.
  • the term “vector” is understood here to mean a guided vehicle, self-propelled or not.
  • the guide means located in the vector are generally of the aerodynamic type, so as to produce a continuous servo-control of the ideal trajectory provided by the ground.
  • the subject of the present invention is a vector guidance system which uses a beam of radiated energy, for example laser beam, tracking the target from the shooting station, for example on the ground, and pyrotechnic boosters arranged on board the vector. , the latter thus knowing at all times its position relative to the ideal trajectory provided by the laser beam; the vector corrects its trajectory by triggering a pyrotechnic impeller when its distance from the ideal trajectory becomes greater than a predefined threshold value and when its radial speed of approach to this ideal trajectory is less than a predefined threshold.
  • a beam of radiated energy for example laser beam
  • tracking the target from the shooting station for example on the ground
  • pyrotechnic boosters arranged on board the vector.
  • the subject of the invention is a system for guiding a vector as defined by claim 1.
  • FIG. 1 therefore schematically represents an embodiment of the vector according to the invention.
  • This vector globally identified V, has four parts, successively from front to back: - a front part T forming an ogive, of aerodynamic shape; a part I P in which are placed pyrotechnic impellers, the orifices 11 of which are shown, their firing devices and their control wires; the orifices 11 are arranged in a cross section of the vector so as to exert on the latter thrusts capable of modifying its trajectory; they are preferably substantially radial and, also preferably, pass substantially through the center of gravity of the vector; such impellers barrel is for example described in the French patent application No.
  • the vector comprises a tail E, arranged at the rear.
  • the vector comprises motor means, ensuring its self-propulsion in at least a first phase of setting in speed of its trajectory.
  • motor means consist, for example as described in French patent application No. 2567197 in the name of BRANDT-ARMS. They are then attached to the back of the vector V and, optionally, released at the end of the first phase.
  • FIG. 2 schematically illustrates the system according to the invention applied to guiding a vector.
  • the vector is for example launched by a shooting station located on the ground, comprising launching means (not shown) and a turret carrying a laser L.
  • the vector can be launched by cannon effect and / or self-propelled in the first phase of its trajectory. It is preferably self-rotating around its longitudinal axis, this self-rotation being printed on the vector either by the barrel or by the wedging angle, relative to the longitudinal axis, of the fins forming the empennage E.
  • the laser L is shown emitting a beam scanning a fraction of the space, the section of which, in a plane normal to emission, is marked B L in the figure; section B L is hereinafter called "laser plane".
  • the scanning is carried out for example along parallel lines describing a square with center O, the point O being located on an axis A L permanently joining the laser L to a target C, of speed V C.
  • the vector is also represented in the form of an arrow V, situated at a given instant, for example at a distance D from the axis A L.
  • this type of laser beam guidance is carried out in the following manner: the laser beam scans a portion of the space whose axis (A L ) is slaved to target C and represents the ideal trajectory of the vector. This scanning is carried out so that, when the vector is illuminated by the laser beam, it can deduce its position relative to the axis A L in the plane B L.
  • the vector pilot triggers a trajectory correction only when the distance D which separates it from the axis A L is greater than a predefined threshold value R, which defines at a given instant a circle C L with center O, around the axis A L.
  • a predefined threshold value R which defines at a given instant a circle C L with center O, around the axis A L.
  • the correction to be made not being independent of the radial speed V R of approximation of the vector of the axis A L an additional condition for triggering a trajectory correction is imposed: the correction is only triggered if the speed V R is less than a certain threshold V s .
  • the impellers may not all provide the same thrust: they are then chosen by the pilot of the vector both according to their position and their thrust, according to the position of the vector and its speed V R.
  • the auto-rotation of the vector makes it possible to carry out a trajectory correction in the desired direction, by overcoming the position in the vector of the impellers not yet used.
  • the threshold distance R from which a trajectory correction can be triggered can be variable, for a given vector, depending on the distance from the target and / or its extent.
  • the scanning of the plane B L by the laser beam can be carried out in a variable manner with the vector-to-ground distance, so that the electronics on board has no correction to make on the determination of the quantity D as a function of this vector-ground distance.
  • FIG. 3 represents a block diagram of an embodiment of the electronic guidance means on board the vector.
  • the optical receiver 31 which provides a computer 33 an indication of lighting or non-lighting of the vector by the laser beam; from this indication, the computer determines the position of the vector with respect to the axis A L , knowing the law of scanning of the plane B L by the laser beam.
  • the computer 33 also receives, if necessary, the measurement of the roll position of the vector, supplied by a device 32 such as a gyroscope. Finally, it receives, for example recorded in a memory 34, the elements constituting the trajectory correction law, namely the radius R, the speed V s , etc.
  • the computer 33 determines the radial speed V r of the vector, compares its distance D to the axis A L with the threshold value R, the speed V r with the threshold value V s and, depending on the position of the roll vector, whether or not to deduce a firing order from a defined pyrotechnic impeller.
  • FIG. 4 represents an embodiment of the system according to the invention applied to the guidance of several vectors, simultaneously.
  • each of the vectors proceeds independently from one another to a trajectory correction and this only when the criteria of distance and speed are fulfilled as in the case of a single vector described in FIG. 2.
  • each of the circles C L1 ... C L3 is centered on the axis A L : there are thus areas of intersection. However, it is estimated that the probability that two or more vectors are simultaneously in an intersection zone is low enough to be neglected.
  • the vector has been described as launched and guided by a laser beam emitted from the ground, but may be so from a shooting station on board an aircraft for example.
  • the guidance system from the ground has been described as seeking pure alignment, at all times, with the actual target, but may, in a variant, seek alignment with the future position of the target, calculated (on the ground) from its speed vector and, at least at the start of guidance.
  • the beam providing guidance has been described as a laser beam, but this can be replaced by any beam of radiated energy, thin enough to fulfill the function described, such as a microwave energy brush whose frequency is in the range used for radars.
  • the laser beam has been described as directly tracking the target, but it can similarly pursue the ideal trajectory (calculated elsewhere) in the case where the target is not visible: case of a ground-ground system by example.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Optical Radar Systems And Details Thereof (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
EP89400335A 1988-02-12 1989-02-07 Durch Laserstrahl und pyrotechnische Impulsgeber geführter Vektor Expired - Lifetime EP0329523B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8801684 1988-02-12
FR8801684A FR2627268B1 (fr) 1988-02-12 1988-02-12 Systeme de guidage de vecteur par faisceau laser et impulseurs pyrotechniques, et vecteur guide par un tel systeme

Publications (2)

Publication Number Publication Date
EP0329523A1 true EP0329523A1 (de) 1989-08-23
EP0329523B1 EP0329523B1 (de) 1994-06-15

Family

ID=9363217

Family Applications (1)

Application Number Title Priority Date Filing Date
EP89400335A Expired - Lifetime EP0329523B1 (de) 1988-02-12 1989-02-07 Durch Laserstrahl und pyrotechnische Impulsgeber geführter Vektor

Country Status (4)

Country Link
US (1) US4901946A (de)
EP (1) EP0329523B1 (de)
DE (1) DE68916058T2 (de)
FR (1) FR2627268B1 (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2689644A1 (fr) * 1992-03-30 1993-10-08 Saint Louis Inst Dispositif de détection et mesure de l'écart de trajectoire d'un projectile.
EP2390616A1 (de) * 2010-05-27 2011-11-30 Nederlandse Organisatie voor toegepast -natuurwetenschappelijk onderzoek TNO Verfahren zur sicheren Führung von gelenkten Projektilen zu einem Ziel, System und Computerprogrammprodukt
FR2983289A1 (fr) * 2011-11-29 2013-05-31 Nexter Munitions Procede de controle du declenchement d'une charge militaire, dispositif de controle et fusee de projectile mettant en oeuvre un tel procede

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5102065A (en) * 1988-02-17 1992-04-07 Thomson - Csf System to correct the trajectory of a projectile
FR2647540B1 (fr) * 1989-05-23 1994-03-25 Thomson Csf Dispositif de ralliement de missile
DE4416211C2 (de) * 1994-05-07 1996-09-26 Rheinmetall Ind Gmbh Verfahren und Vorrichtung zur Flugbahnkorrektur von Geschossen
US5647558A (en) * 1995-02-14 1997-07-15 Bofors Ab Method and apparatus for radial thrust trajectory correction of a ballistic projectile
US5695152A (en) * 1996-09-18 1997-12-09 Israel Aircraft Industries Ltd. System for correcting flight trajectory of a projectile
DE10147837A1 (de) * 2001-09-27 2003-04-24 Rheinmetall Landsysteme Gmbh Wurfsystem für einen Gefechtskopf mit einer Richtvorrichtung zur Neutralisierung von Minen
FR2885213B1 (fr) 2005-05-02 2010-11-05 Giat Ind Sa Procede de commande d'une munition ou sous-munition, systeme d'attaque, munition et designateur mettant en oeuvre un tel procede
CN114279272A (zh) * 2021-12-08 2022-04-05 中国运载火箭技术研究院 一种可用于微小载荷发射的组合模式激光推进系统

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3860199A (en) * 1972-01-03 1975-01-14 Ship Systems Inc Laser-guided projectile system
US4300736A (en) * 1979-08-17 1981-11-17 Raytheon Company Fire control system
WO1987003359A1 (en) * 1985-11-22 1987-06-04 Ship Systems, Inc. Spin-stabilized projectile with pulse receiver and method of use

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Publication number Priority date Publication date Assignee Title
US3028807A (en) * 1959-08-24 1962-04-10 Mcdonnell Aircraft Corp Guidance system
GB1524122A (en) * 1976-01-29 1978-09-06 Elliott Brothers London Ltd Guidance systems for mobile craft
FR2469345A1 (fr) * 1979-11-09 1981-05-22 Thomson Brandt Procede de pilotage et de guidage de projectiles en phase terminale et projectiles comportant les moyens de mise en oeuvre de ce procede
US4347996A (en) * 1980-05-22 1982-09-07 Raytheon Company Spin-stabilized projectile and guidance system therefor
JPS57192129A (en) * 1981-05-21 1982-11-26 Omron Tateisi Electronics Co Semiconductor relay
FR2567197B1 (fr) * 1984-07-06 1988-09-30 Brandt Armements Propulseur a poudre pour projectile tire dans un tube de lancement
DE3675926D1 (de) * 1986-01-30 1991-01-10 Oerlikon Buehrle Ag Vorrichtung zum lenken eines flugkoerpers.

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3860199A (en) * 1972-01-03 1975-01-14 Ship Systems Inc Laser-guided projectile system
US4300736A (en) * 1979-08-17 1981-11-17 Raytheon Company Fire control system
WO1987003359A1 (en) * 1985-11-22 1987-06-04 Ship Systems, Inc. Spin-stabilized projectile with pulse receiver and method of use

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
PATENT ABSTRACTS OF JAPAN, vol. 8, no. 192 (P-298)[1629], 4 septembre 1984; & JP-A-59 81 710 (MITSUBISHI DENKI K.K.) *

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2689644A1 (fr) * 1992-03-30 1993-10-08 Saint Louis Inst Dispositif de détection et mesure de l'écart de trajectoire d'un projectile.
EP2390616A1 (de) * 2010-05-27 2011-11-30 Nederlandse Organisatie voor toegepast -natuurwetenschappelijk onderzoek TNO Verfahren zur sicheren Führung von gelenkten Projektilen zu einem Ziel, System und Computerprogrammprodukt
WO2011149350A1 (en) 2010-05-27 2011-12-01 Nederlandse Organisatie Voor Toegepast-Natuurwetenschappelijk Onderzoek Tno A method of guiding a salvo of guided projectiles to a target, a system and a computer program product
US8748787B2 (en) 2010-05-27 2014-06-10 Nederlandse Organisatie Voor Toegepast-Natuurwetenschappelijk Onderzoek Tno Method of guiding a salvo of guided projectiles to a target, a system and a computer program product
FR2983289A1 (fr) * 2011-11-29 2013-05-31 Nexter Munitions Procede de controle du declenchement d'une charge militaire, dispositif de controle et fusee de projectile mettant en oeuvre un tel procede
EP2600097A1 (de) * 2011-11-29 2013-06-05 Nexter Munitions Kontrollverfahren zur Auslösung eines Gefechtskopfes, Kontrollvorrichtung und Zünder eines Geschosses, in dem ein solches Verfahren zur Anwendung kommt

Also Published As

Publication number Publication date
FR2627268B1 (fr) 1993-05-14
DE68916058D1 (de) 1994-07-21
EP0329523B1 (de) 1994-06-15
US4901946A (en) 1990-02-20
DE68916058T2 (de) 1994-09-22
FR2627268A1 (fr) 1989-08-18

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