EP0329523B1 - Durch Laserstrahl und pyrotechnische Impulsgeber geführter Vektor - Google Patents

Durch Laserstrahl und pyrotechnische Impulsgeber geführter Vektor Download PDF

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Publication number
EP0329523B1
EP0329523B1 EP89400335A EP89400335A EP0329523B1 EP 0329523 B1 EP0329523 B1 EP 0329523B1 EP 89400335 A EP89400335 A EP 89400335A EP 89400335 A EP89400335 A EP 89400335A EP 0329523 B1 EP0329523 B1 EP 0329523B1
Authority
EP
European Patent Office
Prior art keywords
carrier
vector
target
trajectory
pyrotechnic
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.)
Expired - Lifetime
Application number
EP89400335A
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English (en)
French (fr)
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EP0329523A1 (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
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Thomson Brandt Armements SA
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Filing date
Publication date
Application filed by Thomson Brandt Armements SA filed Critical Thomson Brandt Armements SA
Publication of EP0329523A1 publication Critical patent/EP0329523A1/de
Application granted granted Critical
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 vector intended for the interception of maneuvering targets such as planes, helicopters or tanks. It also relates to a guidance system, by laser beam and pyrotechnic boosters of one or more such vectors.
  • vehicle 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 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 vector as defined by claim 1.
  • FIG. 1 therefore schematically represents an embodiment of the vector according to the invention.
  • the vector comprises a tail unit E, disposed 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 tracking 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 imprinted 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 has been 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 has also been 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 also known by the English name of "beam riding" 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 performed 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 of center O, around the axis A L.
  • a predefined threshold value R which defines at a given instant a circle C L of 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 vector pilot 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 magnitude 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 rolling vector, whether or not to deduce therefrom a firing order for a defined pyrotechnic impeller.
  • FIG. 4 represents an embodiment of the system according to the invention applied to guiding several vectors, simultaneously.
  • each of the vectors proceeds independently of 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.
  • a vector guidance system which is simple and inexpensive, especially in terms of on-board equipment, while having a high probability of impact on a drifting target.
  • a pyrotechnic impeller guidance device easily lends itself to miniaturization, thus making it possible to reduce the mass of the vector and, consequently, to provide weapon systems capable of firing several vectors simultaneously.
  • the vector has been described as launched and guided by a laser beam emitted from the ground, but may be 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 real 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.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Optical Radar Systems And Details Thereof (AREA)

Claims (7)

  1. Geschoß (V), das von einem Führungssystem gelenkt wird, um ein Ziel zu erreichen, wobei das System einen Abschußposten enthält, der Mittel zum Abschuß des Geschosses und Mittel zur Verfolgung des Ziels und zur Führung des Geschosses mit Hilfe eines Energiestrahlungsbündels besitzt, die dem Vektor eine Angabe über die ideale Bahn (AL) liefern, wobei das Geschoß enthält:
    - erste Mittel (IP), die je einen die Bahn des Geschosses verändernden Schubimpuls liefern können,
    - zweite Mittel (31) zur Erfassung des Energiestrahlungsbündels,
    - dritte Mittel (PE) zur Bestimmung der Lage des Geschosses bezüglich der vom Strahl gelieferten idealen Bahn, aufgrund der vorhergehenden Erfassung,
    - vierte Mittel (PE) zur Steuerung der ersten Mittel, dadurch gekennzeichnet, daß die ersten Mittel pyrotechnische Impulsgeber (11) sind und daß die vierten Mittel die Zündung eines bestimmten pyrotechnischen Impulsgebers steuern, wenn der Abstand (D) des Geschosses von der idealen Bahn größer als ein vordefinierten Abstandsschwellwert (R) ist und wenn die Radialgeschwindigkeit (VR) der Annäherung des Geschosses an die Idealbahn geringer als ein vorgegebener Geschwindigkeitsschwellwert (VS) ist.
  2. Geschoß nach Anspruch 1, dadurch gekennzeichnet, daß es ein Leitwerk (E) aufweist, dessen Flügel bezüglich der Längsachse des Geschosses so versetzt sind, daß sich eine Eigenrotation des Geschosses ergibt.
  3. Geschoß nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß es Mittel zur Bestimmung seiner Drehlage aufweist, die die Drehlage an die Steuermittel zum Zünden eines Impulsgebers meldet.
  4. Geschoß nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß es weiter Eigenantriebsmittel enthält.
  5. Geschoß nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß der von jedem der pyrotechnischen Impulsgeber (11) gelieferte Schubstoß im wesentlichen im Schwerpunkt des Geschosses (V) wirksam wird.
  6. Geschoß nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß der von jedem der pyrotechnischen Impulsgeber (11) gelieferte Schubstoß im wesentlichen radial bezüglich des Geschosses (V) ausgerichtet ist.
  7. Geschoß nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß der Entfernungsschwellwert (R) abhängig vom Abstand zwischen Geschoß und Ziel und/oder abhängig von der Ausdehnung des Ziels variiert.
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 EP0329523A1 (de) 1989-08-23
EP0329523B1 true EP0329523B1 (de) 1994-06-15

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EP89400335A Expired - Lifetime EP0329523B1 (de) 1988-02-12 1989-02-07 Durch Laserstrahl und pyrotechnische Impulsgeber geführter Vektor

Country Status (4)

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

Families Citing this family (11)

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Publication number Priority date Publication date Assignee Title
FR2627269B1 (fr) * 1988-02-17 1993-05-14 Thomson Csf Systeme de correction de la trajectoire d'un projectile
FR2647540B1 (fr) * 1989-05-23 1994-03-25 Thomson Csf Dispositif de ralliement de missile
DE4210375A1 (de) * 1992-03-30 1993-10-07 Deutsch Franz Forsch Inst Ablagemeßvorrichung
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
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
FR2983289B1 (fr) * 2011-11-29 2014-12-12 Nexter Munitions Procede de controle du declenchement d'une charge militaire, dispositif de controle et fusee de projectile 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

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US3028807A (en) * 1959-08-24 1962-04-10 Mcdonnell Aircraft Corp Guidance system
US3860199A (en) * 1972-01-03 1975-01-14 Ship Systems Inc Laser-guided projectile system
GB1524122A (en) * 1976-01-29 1978-09-06 Elliott Brothers London Ltd Guidance systems for mobile craft
US4300736A (en) * 1979-08-17 1981-11-17 Raytheon Company Fire control system
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
US4728057A (en) * 1985-11-22 1988-03-01 Ship Systems, Inc. Spin-stabilized projectile with pulse receiver and method of use
ES2019870B3 (es) * 1986-01-30 1991-07-16 Werkzeugmaschinenfabrik Oerlikon-Buhrle Ag Dispositivo para guiar una particula volatil.

Also Published As

Publication number Publication date
US4901946A (en) 1990-02-20
DE68916058D1 (de) 1994-07-21
EP0329523A1 (de) 1989-08-23
DE68916058T2 (de) 1994-09-22
FR2627268A1 (fr) 1989-08-18
FR2627268B1 (fr) 1993-05-14

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