EP1196733B1 - Geschosslenkung mittels einer ringanordnung und optisch ausgelösten ablenkvorrichtungen - Google Patents
Geschosslenkung mittels einer ringanordnung und optisch ausgelösten ablenkvorrichtungen 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.
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- 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)
- Zielsuchsystem zum Leiten eines Projektils (32) in ein Ziel (18), gekennzeichnet durch:eine Optikbaugruppe (40), die an einem vorderen Ende (36) des Projektils (32) angeordnet ist und eine Mehrzahl von fotoleitenden Sensorelementen (24) aufweist, welche symmetrisch in einer gemeinsamen Ebene um eine Achse (28) angeordnet sind, die mit einer Flugbahn (34) des Projektils (32) fluchtet, und eine Linse (22) aufweist, die zwischen dem Ziel (18) und den fotoleitenden Sensorelementen (24) mit einem Abstand (D) von den photoleitenden Sensorelementen (24) angeordnet ist;mehrere Kurskorrektoren (44), die an einer Außenfläche (38) des Projektils (32) angebracht sind, wobei die Beleuchtung von einem oder mehreren der fotoleitenden Sensorelemente (24) bewirkt, dass die mehreren Kurskorrektoren (44) eine Abweichung (30) zwischen der derzeitigen Flugbahn des Projektils (34) und dem Ziel (18) verringern, dadurch gekennzeichnet, dassein Umlauf-Schieberegister (54) zwischen den fotoleitenden Sensorelementen (24) und den Kurskorrektoren (44) angeordnet ist, welches mit einer Frequenz (F x N) getaktet wird, wobei F ein Vielfaches der Drehfrequenz des Projektils (32) und N die Anzahl von fotoleitenden Sensorelementen (24) ist.
- System nach Anspruch 1, dadurch gekennzeichnet, dass
die fotoleitenden Sensorelemente (24) in einem Fotodetektor (28) gehäust sind, der ein Metallgehäuse enthält, welches als gemeinsame Kathode fungiert. - System nach Anspruch 1, mit vier bis zwanzig fotoleitenden Sensorelementen (24).
- System nach Anspruch 1, dadurch gekennzeichnet, dass D im wesentlichen der Brennweite der Linse (24) entspricht.
- System nach Anspruch 1, dadurch gekennzeichnet, dass D wesentlich verschieden ist von der Brennweite der Linse (26).
- System nach Anspruch 4 oder 5, dadurch gekennzeichnet, dass jedem fotoleitenden Sensorelement (24) ein lineares Array (58) aus mehreren Kurskorrektur-Ableitern (44) zugeordnet ist.
- System nach Anspruch 6, dadurch gekennzeichnet, dass mindestens einer der mehreren Kurskorrekturableitern (44''') in seinem Impulsvektor einen Versatz aufweist, der die Wirkung hat, einen Projektilspin (32) hervorzurufen.
- Verfahren zum Bewirken einer Kurskorrektur eines Projektils (32), gekennzeichnet durch folgende Schritte:Austatten des Projektils (32) mit einer Mehrzahl von fotoleitenden Sensorelementen (24), die symmetrisch in einer gemeinsamen Ebene um eine Achse (28) angeordnet sind, welche mit einer Flugbahn (34) des Projektils (32) fluchtet;Anstrahlen eines Ziels (18) mit einem von einem gepulsten Laser (14) erzeugten Bestimmungslicht (16), wobei die Laserpulsdauer (10) wesentlich kürzer ist als ein zwischen den Laserpulsen (12) liegendes Intervall;Empfangen von durch das Ziel (18) reflektiertem Bestimmungslicht auf einem oder mehreren der fotoieitenden Sensorelemente (24); undÜbertragen eines Spannungsimpulses (50) von dem einen oder mehreren fotoleitenden Sensorelement (24), um mindestens einen der mehreren Kurskorrektoren (40) zu aktivieren, die sich an dem Projektil (32) befinden, um dadurch eine Kurskorrektur vorzunehmen, dadurch gekennzeichnet, dasszwischen den fotoleitenden Sensorelementen (24) und den mehreren Kurskorrektoren (44) ein Umlauf-Schieberegister (54) angeordnet ist, wodurch, wenn ein ausgewählter Kurskorrektor der mehreren Kurskorrektoren (44) inaktiv ist, die Aktivierung solange verzögert wird, bis ein anderer Kurskorrektor der mehreren Kurskorrektoren (44) zur Ausführung der Kurskorrektur wirksam ist, wobei das Schieberegister mit einer Frequenz (F x N) getaktet wird, wobei F ein Vielfaches der Drehfrequenz des Projektils (32) und N die Anzahl von fotoleitenden Sensorelemente (24) ist.
- Verfahren nach Anspruch 8, dadurch gekennzeichnet, dass das Intervall zwischen Pulsen (12) abhängig von einem voreingestellten Code variiert wird.
- Verfahren nach Anspruch 8, enthaltend den Schritt des Fokussierens der Laserpulse (20) derart, dass diese zu gegebener Zeit auf einzelnes fotoleitendes Sensorelement auftreffen.
- Verfahren nach Anspruch 8, enthaltend den Schritt des Defokussierens der Laserpulse (20) zum Treffen mehrerer einzelner fotoleitender Sensorelemente gleichzeitig.
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 (en) | 1999-07-21 | 2000-07-20 | Ring array projectile steering with optically-triggered diverter elements |
Publications (3)
Publication Number | Publication Date |
---|---|
EP1196733A2 EP1196733A2 (de) | 2002-04-17 |
EP1196733A4 EP1196733A4 (de) | 2003-07-02 |
EP1196733B1 true EP1196733B1 (de) | 2005-10-05 |
Family
ID=22510742
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP00986176A Expired - Lifetime EP1196733B1 (de) | 1999-07-21 | 2000-07-20 | Geschosslenkung mittels einer ringanordnung und optisch ausgelösten ablenkvorrichtungen |
Country Status (4)
Country | Link |
---|---|
EP (1) | EP1196733B1 (de) |
AU (1) | AU2245801A (de) |
DE (1) | DE60023007T2 (de) |
WO (1) | WO2001016547A2 (de) |
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 |
FR2627269B1 (fr) | 1988-02-17 | 1993-05-14 | Thomson Csf | Systeme de correction de la trajectoire d'un 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 |
EP0950165A4 (de) | 1997-01-02 | 2000-03-22 | Tibor G Horwath | Zielfernrohr für ein drallprojektil |
-
2000
- 2000-07-20 WO PCT/US2000/019925 patent/WO2001016547A2/en active IP Right Grant
- 2000-07-20 AU AU22458/01A patent/AU2245801A/en not_active Abandoned
- 2000-07-20 DE DE60023007T patent/DE60023007T2/de not_active Expired - Fee Related
- 2000-07-20 EP EP00986176A patent/EP1196733B1/de not_active Expired - Lifetime
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 |
---|---|
EP1196733A2 (de) | 2002-04-17 |
AU2245801A (en) | 2001-03-26 |
WO2001016547A2 (en) | 2001-03-08 |
WO2001016547A3 (en) | 2001-06-21 |
DE60023007D1 (de) | 2006-02-16 |
EP1196733A4 (de) | 2003-07-02 |
DE60023007T2 (de) | 2006-07-13 |
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