EP0536473A1 - Sous-tête militaire pour emploi à vol rasant - Google Patents

Sous-tête militaire pour emploi à vol rasant Download PDF

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Publication number
EP0536473A1
EP0536473A1 EP92109035A EP92109035A EP0536473A1 EP 0536473 A1 EP0536473 A1 EP 0536473A1 EP 92109035 A EP92109035 A EP 92109035A EP 92109035 A EP92109035 A EP 92109035A EP 0536473 A1 EP0536473 A1 EP 0536473A1
Authority
EP
European Patent Office
Prior art keywords
submunition
target
sensor
carrier
flight
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Withdrawn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
EP92109035A
Other languages
German (de)
English (en)
Inventor
Ulrich Rieger
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.)
Airbus Defence and Space GmbH
Original Assignee
Deutsche Aerospace AG
Daimler Benz Aerospace AG
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 Deutsche Aerospace AG, Daimler Benz Aerospace AG filed Critical Deutsche Aerospace AG
Publication of EP0536473A1 publication Critical patent/EP0536473A1/fr
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C11/00—Electric fuzes
    • F42C11/001—Electric circuits for fuzes characterised by the ammunition class or type
    • F42C11/002—Smart ammunition fuzes, i.e. having an integrated scanning, guiding and firing system
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G3/00—Aiming or laying means
    • F41G3/22—Aiming or laying means for vehicle-borne armament, e.g. on aircraft
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
    • F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
    • F42B12/04—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of armour-piercing type
    • F42B12/10—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of armour-piercing type with shaped or hollow charge

Definitions

  • the present invention relates to a submunition, in particular for low-altitude use, which can be transported to a target area and ejected there by means of a carrier.
  • the submunition travels a predetermined distance at a constant, low altitude with a controlled rolling movement, which runs at an angle to the carrier's flight axis, the submunition having a target sensor and an active charge.
  • a submunition equipped with a search detonator scans the ground in a decelerating spiral strip in the braked steep descent according to target criteria.
  • search fuse submunition either a projectile-forming charge is fired in a targeted manner (search fuse submunition) or the submunition itself is directed to the target.
  • the submunition has to be brought to a high starting altitude, which means with air-to-surface weapons either an emission at this height and thus a great danger to the carrier, or a high effort for the ascent of the submunition plus a corresponding distribution of width in the event of a low-altitude launch .
  • the submunition is designed as a guided missile with a forward-looking seeker.
  • the submunition directs itself automatically to the target after target acquisition, but such a guided missile design is very complex and therefore very expensive.
  • both possible solutions require larger target acquisition distances and thus a high sensitivity to influences other than those of the targets to be combated, whereby these targets still have the option of countermeasures; the risk of multiple targets cannot be ruled out.
  • a submunition body which can be fired by means of an artillery projectile and can be ejected from it over a target area by executing a rotary movement; the submunition is equipped with a target detection sensor and a combat charge in a hollow cylinder.
  • the structurally complex, space-consuming and function-critical measure for the destruction of the kinetic energy after the ejection and for the parachute-braked descent into the target area can be dispensed with by the gyroscopic movement of a dimensioned as a thick disc, ie flat cylinder, body ejected from the carrier floor with self-rotation is used for scanning the target area by means of a target detection sensor spot.
  • Such an arrangement is unsuitable for deployment at high airspeeds, since a sufficiently stable position of the body can only be expected at very high internal speeds, but this is not yet technologically controllable for scanning and target accuracy.
  • the other is detectable target area, ie the area covered by the spiral movement during low-flying is very limited, especially since only a very short free-flight distance can be used due to the inevitable wobble movement.
  • the object of the present invention is to provide a submunition for combating hard, mobile group targets, which can be launched at low altitude, has a high effect against modern main battle tanks, ensures autonomous target recognition with a large search area and offers a low risk of multiple target combat with moderate effort .
  • the submunition is provided with an altimeter and with a circuit that evaluates the altitude measurement results and with at least one rudder that can be controlled from this circuit and that is used for altitude and roll control.
  • the submunition is ejected from a carrier during flight and controls - guided by the altimeter - a trajectory at low altitude parallel to the contour of the terrain.
  • the submunition does not require a drive due to its large kinetic energy, but can be equipped with a drive.
  • the submunition In this free flight at a constant low altitude above ground, the submunition continuously searches for targets in a strip below with the help of its target-detecting sensor. When the target is detected, it directs an effective charge onto the target and triggers it.
  • the altimeter is advantageously a laser rangefinder, which can also serve as a target contour sensing sensor. Additional sensors can be used as a support or alternatively for target acquisition.
  • the submunition is equipped with a laser range finder for height and target measurement, and also with a magnetic field sensor as the second target sensor, which are connected to a circuit which triggers the ignition of the active charge.
  • the laser sensor and active charge are rigidly installed axially parallel to the direction of flight.
  • the submunition continuously performs an oscillating rolling movement for scanning the search strip and for height measurement.
  • the target-detecting sensor and the active charge have a certain broad effect, which is coordinated with one another. Both are again rigidly installed axially parallel to the direction of flight. The submunition flies here without any aim-related roll movements.
  • the submunition according to the invention which is particularly suitable for use in fast low-altitude flight, offers a favorable compromise between the cost of the weapon and the required transportation. Due to the small target distance (a range of 20 to 50 m), the requirements for sensors, signal processing and tolerances can be kept low. The small target distance also leads to good target acquisition opportunities, since only small target concealments due to environmental influences are to be expected and there is little sensitivity to weather and countermeasures.
  • the submunition according to the invention covers a relatively large area strip of a few thousand m2.
  • the overlap of the search strips of several submunitions can be minimized. This means that a high degree of efficiency can be achieved in relation to the weight of the weapon and the entire target area, i.e. a high probability for the detection of all individual parts and a low probability for double combat of the mobile targets.
  • the submunition according to the invention can also be used to combat other groups of mobile targets or also the position according to only roughly known vehicles, such as Rocket positions, helicopter bases, motorized rifle companies, artillery positions, control stations, etc.
  • the trajectory can be curved horizontally either by structural design or selectable by appropriate roll control.
  • the arrow running to the right denotes a submunition carrier track, which therefore takes the carrier that ejects one or more submunitions.
  • a submunition After the release of a submunition, it goes into gliding flight and controls the predetermined height above ground, which e.g. With its height-maintaining device, it is 20 m and holds it until the minimum flight speed is undershot.
  • the flight course over the ground is not guided and runs essentially in a straight line at an angle to the carrier web, which depends on the ejection conditions (FIG. 1c).
  • the submunition controls its rollage so that its targeting sensor looks at the ground.
  • the target detection device is pivoted continuously, essentially perpendicular to the flight axis, and thus searches for targets in a strip below the submunition (FIG. 1b).
  • the target detection device has a wide detection window.
  • the active charge is triggered, which is aligned with the target parallel to the axis of the target acquisition device.
  • the carrier can contain a large number of submunitions, which are ejected in a defined sequence, possibly also adapted to the target geometry, in such a way that the search strips of the individual submunitions lie next to one another. As is indicated in FIG. 1c, the entire target area is thus searched for targets x.
  • a narrow, undetected alley remains below the carrier path, which is dependent on the ejection height and which is due to the fact that the submunitions are only activated for a certain time after ejection from the carrier in such a way that they target the region below them can scan for targets.
  • Fig. 2 shows the schematic structure of a submunition according to the invention, with 1 denoting the main axis in the direction of flight, with 2 meandering arrows which are intended to indicate an oscillation around the main axis 1, with 3 an active charge, e.g. a projectile-forming hollow charge with a suitable securing device, with 4 the axis of the shaped charge, with 5 a height and target sensor, with 6 a second target sensor, with 7 a pair of adjustable rudders serving for height and roll control, with 8 a rigid tail unit for aerodynamic stabilization and with 9 a power supply and a signal processing circuit both for the target sensor system and for the roll and height control.
  • active charge e.g. a projectile-forming hollow charge with a suitable securing device
  • 4 the axis of the shaped charge
  • 5 a height and target sensor
  • 6 a second target sensor
  • 7 a pair of adjustable rudders serving for height and roll control
  • 8 a rigid tail unit for aero
  • a laser rangefinder is particularly suitable as an altimeter, which can be used not only for height information, but also for target acquisition by measuring the characteristic target contours.
  • a second target sensor for example a magnetic sensor, is provided, which supplies a second target determination criterion.
  • the laser sensor is arranged such that its sensor direction essentially runs perpendicular to the main axis 1 of the submunition.
  • the adjustable aerodynamic surfaces, ie the wings or rudders 7, serve to maintain a substantially constant distance above the ground and to hold the target-measuring laser sensor with the direction of detection to the ground.
  • the submunition is e.g. high transverse speed ejected from a carrier in fast low-altitude flight at a speed of e.g. 0.8 Ma and at a height of 40 m. It unfolds into a free-flight configuration, stabilizes its main axis in the direction of flight and, with the help of its rudders 7, sets in rapid oscillatory movements.
  • the laser range finder 6 determines - starting with its max. Detection range - the shortest echo range with each vibration of the submunition. This is interpreted as a height above ground and vertical, the control element for the rudder 7 being actuated depending on the distance in such a way that the predetermined target height of, for example, 20 m is controlled. At this height, the submunition glides over the ground (Fig. 1a). Furthermore, the rudders are deflected by superimposing a roll command for oscillation and height control so that the vertical corresponds to the center of the oscillation oscillation.
  • the second target sensor for example a magnetic sensor, searches for target criteria. If this sensor responds in the presence of battle tanks, the signal from the altimeter, ie the laser rangefinder, is evaluated for changes in height profile, for example, which are characteristic of large vehicles. Such a jump in height with a simultaneous positive target message from the second sensor is interpreted as the target and the projectile-forming charge is ignited. As a result of their position parallel to the axis of the laser, the active charge is shot in a direction in which, according to the contour evaluation, the target lies.
  • the signal from the altimeter ie the laser rangefinder
  • 3a to d show sections through the submunition in planes perpendicular to the trajectory.
  • 3a shows the shortest distance, which is interpreted as height above ground and vertical.
  • Fig. 3c shows that a target has been detected and
  • Fig. 3d shows schematically the fight against this target.
  • 4a to d show these phases of targeting in plan view.
  • the ignition timing can be chosen such that the maximum effect is achieved, e.g. an angle of impact that is as steep as possible or the control of horizontal high areas, e.g. the surfaces of the main battle tanks.
  • the control circuit 9 can work with a time offset compared to the passage of the minimum distance, so that, depending on the setting, trajectories curved to the right or left can be generated over the ground. This means e.g. Course variations of submunitions emitted at the same time or in the same direction are possible, i.e. less double coverage of a strip of land or also reduction or closure of uncovered strips, i.e. the alleys below the beam (Fig. 1c).
  • the setting of the courses followed by the submunitions can be determined by the carrier.
  • optimal surface coverage can be achieved in spite of structurally identical submunition, and the detected surface can also be adapted to the relative position of the carrier-target and the target geometry.
  • the submunition according to the invention enables a high combat probability even against widely spread main battle tanks from deep flight, with effective use of the weapon weight and moderate costs.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
EP92109035A 1991-10-09 1992-05-29 Sous-tête militaire pour emploi à vol rasant Withdrawn EP0536473A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4133405A DE4133405C2 (de) 1991-10-09 1991-10-09 Submunition für Tiefflugeinsatz
DE4133405 1991-10-09

Publications (1)

Publication Number Publication Date
EP0536473A1 true EP0536473A1 (fr) 1993-04-14

Family

ID=6442322

Family Applications (1)

Application Number Title Priority Date Filing Date
EP92109035A Withdrawn EP0536473A1 (fr) 1991-10-09 1992-05-29 Sous-tête militaire pour emploi à vol rasant

Country Status (3)

Country Link
US (1) US5301614A (fr)
EP (1) EP0536473A1 (fr)
DE (1) DE4133405C2 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2721997A1 (fr) * 1994-07-01 1996-01-05 Thomson Csf Systeme individuel de grenade intelligente et son moyen de lancement
RU2274823C1 (ru) * 2004-09-13 2006-04-20 Научно-исследовательский институт специального машиностроения Московского государственного технического университета им. Н.Э. Баумана Танковый противовертолетный снаряд

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SE505189C2 (sv) * 1994-11-16 1997-07-14 Bofors Ab Sätt och anordning för att med från en bärfarkost frigjorda stridsdelar bekämpa längs bärfarkostens färdväg identifierade mål
DE29703458U1 (de) * 1997-02-27 1997-04-30 Schmitz, Oliver, 60325 Frankfurt Lasche für Druckerzeugnisse
AUPQ524000A0 (en) * 2000-01-24 2000-06-15 Metal Storm Limited Anti-missile missiles
AU2002950846A0 (en) * 2002-08-16 2002-09-12 Metal Storm Limited Interception missile and method of interception

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0071757A2 (fr) * 1981-08-05 1983-02-16 Rheinmetall GmbH Dispositif de contrôle de la position d'un missile
DE3323685A1 (de) * 1983-07-01 1985-01-10 Dornier Gmbh, 7990 Friedrichshafen Einrichtung zur bekaempfung von bodenzielen aus der luft
DE3345601C2 (de) * 1983-12-16 1986-01-09 Diehl GmbH & Co, 8500 Nürnberg Submunitionskörper
DE3421140A1 (de) * 1984-06-07 1986-01-30 Messerschmitt-Bölkow-Blohm GmbH, 8012 Ottobrunn Verfahren zur ortung und zielsuche von mit motorkraft angetriebenen zielen und munitionskoerper zur durchfuehrung des verfahrens
DE3843006A1 (de) * 1988-12-21 1990-06-28 Messerschmitt Boelkow Blohm Vorrichtung fuer das auffinden und die identifizierung von einzelzielen

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3964694A (en) * 1967-02-14 1976-06-22 The United States Of America As Represented By The Secretary Of The Army Aerial acoustic target seeker
US4522356A (en) * 1973-11-12 1985-06-11 General Dynamics, Pomona Division Multiple target seeking clustered munition and system
DE2538665A1 (de) * 1975-08-30 1977-03-10 Messerschmitt Boelkow Blohm Verfahren und einrichtung zum streuwurf von bomben
FR2406800A1 (fr) * 1977-10-18 1979-05-18 Aerospatiale Missile d'attaque en survol
US4172407A (en) * 1978-08-25 1979-10-30 General Dynamics Corporation Submunition dispenser system
US4417520A (en) * 1980-04-14 1983-11-29 General Dynamics, Pomona Division Sequential time discrimination system for sub-delivery systems
DE3524925A1 (de) * 1985-07-12 1987-01-22 Diehl Gmbh & Co Verfahren zum ansteuern eines zieles

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0071757A2 (fr) * 1981-08-05 1983-02-16 Rheinmetall GmbH Dispositif de contrôle de la position d'un missile
DE3323685A1 (de) * 1983-07-01 1985-01-10 Dornier Gmbh, 7990 Friedrichshafen Einrichtung zur bekaempfung von bodenzielen aus der luft
DE3345601C2 (de) * 1983-12-16 1986-01-09 Diehl GmbH & Co, 8500 Nürnberg Submunitionskörper
DE3421140A1 (de) * 1984-06-07 1986-01-30 Messerschmitt-Bölkow-Blohm GmbH, 8012 Ottobrunn Verfahren zur ortung und zielsuche von mit motorkraft angetriebenen zielen und munitionskoerper zur durchfuehrung des verfahrens
DE3843006A1 (de) * 1988-12-21 1990-06-28 Messerschmitt Boelkow Blohm Vorrichtung fuer das auffinden und die identifizierung von einzelzielen

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2721997A1 (fr) * 1994-07-01 1996-01-05 Thomson Csf Systeme individuel de grenade intelligente et son moyen de lancement
RU2274823C1 (ru) * 2004-09-13 2006-04-20 Научно-исследовательский институт специального машиностроения Московского государственного технического университета им. Н.Э. Баумана Танковый противовертолетный снаряд

Also Published As

Publication number Publication date
DE4133405A1 (de) 1993-04-15
US5301614A (en) 1994-04-12
DE4133405C2 (de) 1995-02-23

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