EP1196733B1 - Guidage de projectile a reseau en anneau a l'aide d'elements deflecteurs a declenchement optique - Google Patents
Guidage de projectile a reseau en anneau a l'aide d'elements deflecteurs a declenchement optique Download PDFInfo
- Publication number
- EP1196733B1 EP1196733B1 EP00986176A EP00986176A EP1196733B1 EP 1196733 B1 EP1196733 B1 EP 1196733B1 EP 00986176 A EP00986176 A EP 00986176A EP 00986176 A EP00986176 A EP 00986176A EP 1196733 B1 EP1196733 B1 EP 1196733B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- projectile
- sensing elements
- photoconductive sensing
- course
- 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.)
- Expired - Lifetime
Links
Images
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
- F41G7/22—Homing guidance systems
- F41G7/226—Semi-active homing systems, i.e. comprising a receiver and involving auxiliary illuminating means, e.g. using auxiliary guiding missiles
-
- 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
- F41G7/22—Homing guidance systems
- F41G7/2273—Homing guidance systems characterised by the type of waves
- F41G7/2293—Homing guidance systems characterised by the type of waves using electromagnetic waves other than radio waves
-
- 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
- This invention relates to a guidance seeker system effective to guide a projectile to a target. Moreover, it relates to a method to effect a course correction in a projectile. More particularly, the munition includes a plurality of photoconductive sensing elements that both enable calculation of a variance between the flight axis of the munition and an illuminated target and trigger at least one on-board diverter to reduce that variance.
- Projected munitions frequently include a guidance seeker system that enables the projectile to calculate a variance from a target and to make one or more in-flight course corrections to increase the likelihood of the projectile disabling or destroying the target.
- a guidance seeker system is disclosed in United States Patent No. 5,529,262 by Horwath that discloses a guidance seeker system actuated via a continuous beam of ultraviolet, visible or infrared light.
- This seeker system includes a reticle with concentric; alternating, bands of light transmitting and light non-transmitting rings. The beam generates pulses as the target moves across the reticle field. The periodisity of these pulses is used to determine deviation of the target from a center line of the reticle. Circumferential thrusters on the projectile are then used to effect a necessary course change.
- U.S.-A- 6,076,765 by Horwath utilizes a reticle having a pattern discontinuity effective to generate a singly periodic pulse once each projectile revolution.
- the periodisity of pulses generated by the target sweeping across the reticle field enables the projectile to determine the line of flight variance between the projectile and the target.
- the singly periodic pulse enables the projectile to determine its rotation position. Utilizing this information, an appropriate ring diverter is fired to reduce or eliminate the variance.
- US-A-5,695,152 discloses a system and a method for correcting the course of a projectile, wherein the projectile spins during flight.
- the projectile is launched by a launcher device.
- sensors provided on the projectile sense light emitted from target markers associated with the launcher device.
- a thruster provided on the projectile is activated if a largest permissible deviation angle of the projectile is detected.
- Spinning reticle-based guidance seeker systems require a constant light source.
- light is not limited to the visible spectrum, but includes infrared, ultra-violet as well as other portions of the spectrum.
- an infrared source on the target is utilized, i.e. a "heat seeking" missile.
- passive guidance systems Such systems where the seeker is drawn to a light source originating on the target are referred to as passive guidance systems.
- a semi-active guidance system guides a projectile to a target that is externally illuminated.
- external illumination is by a laser beam.
- the laser generating this laser beam may be mounted on the projectile, or alternatively, located on a separate platform, such as a helicopter or spotter plane.
- One semi-active guidance seeker system is disclosed in US-A-5,102,065 to Couderc et al. This patent discloses a homing system utilizing a laser that tracks both a target and a missile. The homing system determines the variance between the two and transmits course correction instructions to the missile that are then effected by small explosive charges or rudder adjustments.
- US-A-5,835,204 to Urbach discloses pulsed laser systems utilized to determine the distance to a target.
- the above mentioned guidance seeker systems require a steady state target signal or a steady state illumination signal from a target designator. They may also be amenable to pulsed signals having a repetition rate much faster than the highest frequency signal generated by the seekers.
- the guidance seeker system of the invention is described with particular emphasis on projected munitions whereby the projectile includes an explosive charge that is intended to detonate either on contact with a target or proximate to the target thereby disabling or destroying that target, the guidance seeker system is equally applicable to nondestructive applications where it is desirable to direct a projectile to a desired target.
- One method of identifying a target illuminates the target with an external light source. This is referred to as “designating” the target and the light source referred to as the "designator.”
- a guidance seeker system on-board a projectile locates the illuminated target and directs the projectile to that target.
- a highly focused coherent beam of light such as a beam generated by a laser, is particularly useful for target designation.
- the laser it is preferable for the laser to generate short duration pulses at a relatively slow repetition rate.
- an exemplary pulse duration 10 is between about 15 nanoseconds and 100 nanoseconds.
- the pulse spacing 12 is from about 0.033 seconds to about 0.05 seconds, generating between about 20 and 30 pulses per second (i.e. a pulse frequency of between 20 Hertz and 30 Hertz).
- Any laser capable of generating pulses meeting the above requirements may be utilized.
- One preferred laser is a neodymium/YAG (yttrium, aluminum, garnet) laser.
- the laser 14 is preferably mounted on a platform other than the projectile.
- the laser 14 may be mounted on a helicopter or spotting aircraft.
- the laser 14 generates a pulsed beam 16 that is reflected from a target 18.
- a reflected pulse 20 is collected by lens 22 and transmitted onto at least one of a plurality of photoconductive sensing elements 24 contained within a photodetector 26.
- the photoconductive sensing elements 24 are preferably symmetrically disposed about a central axis 28 of the photo detector 26.
- the central axis 28 is aligned with the line of flight of the projectile, such that if the line of flight is aligned with the line of the reflected pulse, the reflected pulse strikes the central axis and does not strike any one of the photoconductive sensing elements thereby indicating that no course correction is required.
- reflected pulse 20 strikes at least one photoconductive sensing element. Illumination of the photoconductive sensing element 24 generates an electric pulse that effects a projectile course correction.
- the course correctors are a plurality of diverter elements 44 encircling the center of gravity of the projectile 32.
- Each diverter is a small, on the order of one gram charge, explosive that when detonated creates an impulse that nudges the projectile to change the line of flight to one more likely to impact the target.
- from detonation of one diverter until the projectile is ready for a second course correction is on the order of 0.100 seconds.
- An exemplary number of diverters for a 69.85 mm (2.75 inch) rocket is from about 16 to 32.
- diverters are a preferred course corrector for the projectiles
- other course correctors such as small thrusters or rudders may also be employed with the invention.
- the photodetector 26 is mounted rearward, relative to the forward end 36, of the lens 22 such that lens 22 is disposed between the target and the photo-detector 26.
- a distance, D, between the lens 22 and photodetector 26 may be equal to the focal length of that lens, for a focused beam embodiment or may be a distance other than the focal length for a defocused beam.
- Output signals from the photoconductive elements mounted on photodetector 26 are pre-amplified and conditioned by electronics package 46 and then applied to the appropriate filing circuit associated with a desired diverter 44. Wires 48 may be utilized to transmit the output signal to the appropriate firing circuit.
- the projectile 32 may be either a spinning projectile or a non-spinning projectile. If a spinning projectile, the rate of spin is typically on the order of 1000 revolutions per second.
- output signals 50 from the photoconductive sensing elements 24, are typically voltage pulses having a voltage on the order of millivolts.
- the output signals 50 are passed through an amplifier 52 where the signal is pre-amplified and conditioned to 100 millivolts.
- a recirculating shift register 54 is clocked to a frequency, f, that is a multiple of the spin frequency of the projectile.
- a multiplication factor, n is equal to the number of photoconductive sensing elements in the ring.
- Shift register 54 transmits the conditioned output signal 50 1 via an appropriate firing circuit to the diverter 44 aligned with an irradiated photoconductive sensing element 24. Generation of the firing pulse and activation of the diverter occurs almost instantaneously and is effective to nudge the projectile to a line of flight closer to the target. It is anticipated that the next laser impacting the photodetector will strike closer to central axis 28.
- a focused designator beam applies a high intensity of light to a single photoconductive sensing element generating a high voltage pulse from that element.
- D it is desirable that D not equal the focal length of lens 22.
- photoconductive sensing elements 24 are irradiated with a defocused beam 56.
- Defocused beam 56 is sufficiently large to irradiate a plurality of photoconductive sensing elements 24.
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Fluid Mechanics (AREA)
- Electromagnetism (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
- Optical Radar Systems And Details Thereof (AREA)
Claims (11)
- Système chercheur de guidage servant à guider un projectile (32) vers une cible (18), caractérisé par :un boítier optique (40) disposé à une extrémité avant (36) dudit projectile (32), ledit boítier optique (40) comprenant une pluralité d'éléments de détection photoconducteurs (24) symétriquement disposés sur un plan commun autour d'un axe (28) aligné sur la ligne de vol (34) dudit projectile (32), et une lentille (22) disposée entre ladite cible (18) et lesdits éléments de détection photoconducteurs (24) à une distance D desdits éléments de détection photoconducteurs (24) ;une pluralité de correcteurs de trajectoire (44) montés sur une surface extérieure (38) dudit projectile (32) où l'illumination d'un ou de plusieurs desdits éléments de détection photoconducteurs (24) entraíne que ladite pluralité de correcteurs de trajectoire (44) réduise un écart (30) entre la trajectoire présente dudit projectile (34) et ladite cible (18) ;
caractérisé en ce queun registre à décalage à recirculation (54) étant disposé entre lesdits éléments de détection photoconducteurs (24) et lesdits correcteurs de trajectoire (44) synchronisés sur une fréquence FxN, où F est un multiple de la fréquence de rotation dudit projectile (32) et N est le nombre d'éléments de détection photoconducteurs (24). - Système chercheur de guidage selon la revendication 1, caractérisé en ce que lesdits éléments de détection photoconducteurs (24) sont logés à l'intérieur d'un photodétecteur (28) ayant un boítier métallique qui fonctionne comme une cathode commune.
- Système chercheur de guidage selon la revendication 1 ayant de 4 à 20 éléments de détection photoconducteurs (24).
- Système chercheur de guidage selon la revendication 1, caractérisé en ce que D est sensiblement égal à une distance focale de ladite lentille (26).
- Système chercheur de guidage selon la revendication 1, caractérisé en ce que D est sensiblement différent d'une distance focale de ladite lentille (26).
- Système chercheur de guidage selon la revendication 4 ou la revendication 5, caractérisé en ce que chaque élément de détection photoconducteur (24) est associé à un réseau linéaire (58) contenant une pluralité de dérouteurs de correction de trajectoire (44).
- Système chercheur de guidage selon la revendication 6, caractérisé en ce que au moins un de ladite pluralité de dérouteurs de correction de trajectoire (44''') a une obliquité dans son vecteur d'impulsion effective pour induire une rotation du projectile (32).
- Procédé pour effectuer une correction de trajectoire dans un projectile (32), caractérisé par les étapes consistant à :munir ledit projectile (32) d'une pluralité d'éléments de détection photoconducteurs (24) symétriquement disposés dans un plan commun autour d'un axe (28), ledit axe (28) étant aligné sur la ligne de vol (34) dudit projectile (32) ;irradier une cible (18) avec une lumière de désignation (16) générée par un laser pulsé (14), où la durée de l'impulsion dudit laser (10) est sensiblement plus courte qu'un intervalle entre lesdites impulsions laser (12) ;recevoir une lumière de désignation réfléchie par ladite cible (18) sur un ou plusieurs desdits éléments de détection photoconducteurs (24), ettransmettre une impulsion de tension (50) à partir d'un ou de plusieurs éléments de détection photoconducteurs (24) pour activer au moins un parmi une pluralité de correcteurs de trajectoire (44) attenant audit projectile (32), en procédant de cette manière à une correction de trajectoire, caractérisé en ce qu'un registre à décalage à recirculation (54) est disposé entre lesdits éléments de détection photoconducteurs (24) et ladite pluralité de correcteurs de trajectoire (44) où, si un correcteur sélectionné de ladite pluralité de correcteurs de trajectoire (44) est inactif, l'activation est retardée jusqu'à ce qu'un correcteur différent de ladite pluralité de correcteurs de trajectoire (44) soit effectif pour procéder à ladite correction de trajectoire, le registre à décalage étant synchronisé sur une fréquence FxN, où F est un multiple de la fréquence de rotation dudit projectile (32) et N est le nombre desdits éléments de détection photoconducteurs (24).
- Procédé selon la revendication 8, caractérisé en ce que ledit intervalle entre les impulsions (12) est changé selon un code prédéfini.
- Procédé selon la revendication 8, comprenant l'étape consistant à focaliser lesdites impulsions laser (20) pour qu'elles ne frappent qu'un seul élément de détection photoconducteur à la fois.
- Procédé selon la revendication 8, comprenant l'étape consistant à défocaliser lesdites impulsions laser (20) pour qu'elles frappent plusieurs éléments de détection photoconducteurs à la fois.
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US14491899P | 1999-07-21 | 1999-07-21 | |
US144918P | 1999-07-21 | ||
PCT/US2000/019925 WO2001016547A2 (fr) | 1999-07-21 | 2000-07-20 | Guidage de projectile a reseau en anneau a l'aide d'elements deflecteurs a declenchement optique |
Publications (3)
Publication Number | Publication Date |
---|---|
EP1196733A2 EP1196733A2 (fr) | 2002-04-17 |
EP1196733A4 EP1196733A4 (fr) | 2003-07-02 |
EP1196733B1 true EP1196733B1 (fr) | 2005-10-05 |
Family
ID=22510742
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP00986176A Expired - Lifetime EP1196733B1 (fr) | 1999-07-21 | 2000-07-20 | Guidage de projectile a reseau en anneau a l'aide d'elements deflecteurs a declenchement optique |
Country Status (4)
Country | Link |
---|---|
EP (1) | EP1196733B1 (fr) |
AU (1) | AU2245801A (fr) |
DE (1) | DE60023007T2 (fr) |
WO (1) | WO2001016547A2 (fr) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102007002336A1 (de) * | 2007-01-16 | 2008-07-17 | Lfk-Lenkflugkörpersysteme Gmbh | Suchkopf für einen Lenkflugkörper zur Erfassung und Verfolgung eines Zieles und Verfahren zu dessen Anwendung |
DE102009016147A1 (de) | 2009-04-03 | 2010-10-07 | Rheinmetall Soldier Electronics Gmbh | Zerlegendes Geschoss |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE10147837A1 (de) | 2001-09-27 | 2003-04-24 | Rheinmetall Landsysteme Gmbh | Wurfsystem für einen Gefechtskopf mit einer Richtvorrichtung zur Neutralisierung von Minen |
DE102004029343B4 (de) * | 2004-06-17 | 2009-04-30 | Diehl Bgt Defence Gmbh & Co. Kg | Zielführungsvorrichtung für ein Fluggerät |
US8164037B2 (en) * | 2009-09-26 | 2012-04-24 | Raytheon Company | Co-boresighted dual-mode SAL/IR seeker including a SAL spreader |
Family Cites Families (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3000307A (en) * | 1953-08-04 | 1961-09-19 | Jr Herbert Trotter | Device for correcting the course of a missile |
US4006356A (en) * | 1961-10-27 | 1977-02-01 | Aeronutronic Ford Corporation | Radiant energy tracking device |
GB1605228A (en) * | 1970-10-01 | 1985-03-20 | British Aerospace | Missiles |
US4231533A (en) * | 1975-07-09 | 1980-11-04 | The United States Of America As Represented By The Secretary Of The Air Force | Static self-contained laser seeker system for active missile guidance |
US5102065A (en) | 1988-02-17 | 1992-04-07 | Thomson - Csf | System to correct the trajectory of a projectile |
US5127604A (en) * | 1989-08-18 | 1992-07-07 | Raytheon Company | Optical system |
DE4007712A1 (de) * | 1990-03-10 | 1991-09-12 | Tzn Forschung & Entwicklung | Geschoss mit einem bugseitig angeordneten ir-suchsystem |
US5529262A (en) | 1993-06-23 | 1996-06-25 | Horwath; Tibor G. | Guidance seeker for small spinning projectiles |
US5456429A (en) * | 1993-08-02 | 1995-10-10 | Loral Corp. | Thrust maneuver system |
DE4408085C2 (de) * | 1994-03-10 | 1999-08-12 | Rheinmetall W & M Gmbh | Vorrichtung zur Lenkung eines nicht um seine Längsachse rotierenden Flugkörpers |
DE4410326C2 (de) * | 1994-03-25 | 1998-07-02 | Rheinmetall Ind Ag | Geschoß mit einer Vorrichtung zur Flugbahnkorrektur |
DE4443134C2 (de) * | 1994-12-03 | 2001-07-05 | Diehl Stiftung & Co | Sensoreinrichtung für einen Flugkörper |
IL116438A (en) | 1995-12-18 | 2000-01-31 | Israel State | Laser sensor |
US5695152A (en) * | 1996-09-18 | 1997-12-09 | Israel Aircraft Industries Ltd. | System for correcting flight trajectory of a projectile |
US6076765A (en) | 1997-01-02 | 2000-06-20 | Primex Technologies, Inc. | Reticle for use in a guidance seeker for a spinning projectile |
-
2000
- 2000-07-20 WO PCT/US2000/019925 patent/WO2001016547A2/fr active IP Right Grant
- 2000-07-20 EP EP00986176A patent/EP1196733B1/fr not_active Expired - Lifetime
- 2000-07-20 DE DE60023007T patent/DE60023007T2/de not_active Expired - Fee Related
- 2000-07-20 AU AU22458/01A patent/AU2245801A/en not_active Abandoned
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102007002336A1 (de) * | 2007-01-16 | 2008-07-17 | Lfk-Lenkflugkörpersysteme Gmbh | Suchkopf für einen Lenkflugkörper zur Erfassung und Verfolgung eines Zieles und Verfahren zu dessen Anwendung |
DE102009016147A1 (de) | 2009-04-03 | 2010-10-07 | Rheinmetall Soldier Electronics Gmbh | Zerlegendes Geschoss |
Also Published As
Publication number | Publication date |
---|---|
WO2001016547A2 (fr) | 2001-03-08 |
EP1196733A2 (fr) | 2002-04-17 |
AU2245801A (en) | 2001-03-26 |
DE60023007D1 (de) | 2006-02-16 |
WO2001016547A3 (fr) | 2001-06-21 |
EP1196733A4 (fr) | 2003-07-02 |
DE60023007T2 (de) | 2006-07-13 |
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