EP0049778B1 - Procédé pour distribuer des munitions de combat - Google Patents

Procédé pour distribuer des munitions de combat Download PDF

Info

Publication number
EP0049778B1
EP0049778B1 EP81107358A EP81107358A EP0049778B1 EP 0049778 B1 EP0049778 B1 EP 0049778B1 EP 81107358 A EP81107358 A EP 81107358A EP 81107358 A EP81107358 A EP 81107358A EP 0049778 B1 EP0049778 B1 EP 0049778B1
Authority
EP
European Patent Office
Prior art keywords
distribution unit
sub
flight
bodies
arrangement
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
Application number
EP81107358A
Other languages
German (de)
English (en)
Other versions
EP0049778A1 (fr
Inventor
Walter Prof.Dr. Diesinger
Klaus Fischer
Heinz Kroschel
Rolf Menne
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.)
Huels Troisdorf AG
Dynamit Nobel AG
Original Assignee
Huels Troisdorf AG
Dynamit Nobel 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 Huels Troisdorf AG, Dynamit Nobel AG filed Critical Huels Troisdorf AG
Publication of EP0049778A1 publication Critical patent/EP0049778A1/fr
Application granted granted Critical
Publication of EP0049778B1 publication Critical patent/EP0049778B1/fr
Expired legal-status Critical Current

Links

Images

Classifications

    • 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
    • F42B12/36—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information
    • F42B12/56—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information for dispensing discrete solid bodies
    • F42B12/58—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles

Definitions

  • the invention relates to a method for distributing war bodies in accordance with the preamble of claim 1.
  • Cluster munitions e.g. B. for mining the site, can be distributed by means of the ejection head described in DE-A-21 53 994, which is used in particular in connection with rockets and as a distribution unit, a payload carrier plate with several pivotally attached ejector pipes, which to the target area distributing body contain and be spread apart before distribution.
  • the distribution unit is released before the release. H. the beginning of the ejection or distribution of the ejection body by additional braking measures, for example by means of a brake parachute or by airbrakes in flight, braked so that it sinks vertically downward and has thus been transferred to a predetermined release position.
  • the distribution unit can still be connected to the remaining rocket or can also be separated from it and transferred to the vertical path on its own.
  • cluster munitions The effectiveness of cluster munitions is limited by the accuracy of the clarification of the moving targets to be combated and the possibility of being able to predict the paths of the targets with sufficient probability.
  • a disadvantage of every cluster ammunition is the only statistical hit probability, i.e. H. many active bodies reach no goal.
  • Guided missiles represent an expensive weapon with comparatively low cost effectiveness, the effectiveness of which is also limited by the accuracy of the reconnaissance and which require a great deal of effort not only in terms of electronics, but also for the drive.
  • End-phase guided missiles have the advantage over the guided missiles of simplifying the means of transport, in particular an unguided rocket as with cluster munitions.
  • the advantage over the latter is the increase in the probability of hitting in the final phase, i.e. H. shortly before the target by means of a simplified steering compared to conventional guided missiles. Since only the final phase is directed, the goal must be known comparatively precisely, just as with cluster munitions.
  • certain problems in the final phase steering have not yet been solved, e.g. B. the prevention of multiple bombardment of a target by several articulated missiles, a problem that also exists with conventional guided missiles. The problem of multiple bombardment arises particularly when, because of the total costs and / or the range of fire, several missile-guided missiles are fired into the target area with a rocket.
  • the invention has for its object to provide a method for distributing missiles with active charges to the fighter of in particular armored targets, in which two or more daughter missiles representing the missiles are transported together and distributed there by means of a carrier missile, without the above-mentioned Disadvantages occur, d. H. in which a more favorable ratio between the effort required and the attainable probability of being achieved is achieved.
  • the object is achieved on the basis of the method specified in the preamble of claim 1 in accordance with the characterizing part of this claim.
  • the determination of the time of release of the individual daughter missiles depending on the target acquisition by means of the central search and evaluation device on the distribution unit enables an optimal starting or starting position for each individual daughter missile in the target assigned to it by the search and evaluation device. This results in a significant increase in the probability of being hit without the need for a search and evaluation device on each individual daughter missile, as in the case of missiles guided in the final phase.
  • the use of only one central electronic search and evaluation device per distribution unit also makes it possible to design this device with still higher overall expenditure and with a higher performance than the corresponding separate devices of the daughter missiles.
  • Another advantage is the extension of the target phase that can be determined autonomously by the search device, ie. H. the period of time until the release of the daughter missile, which enables a longer target tracking and thus an optimization of the start coordinates of the individual daughter missiles.
  • the carrier missile is preferably a rocket, in particular an unguided rocket. But there are also other unmanned missiles, e.g. B. those with an air-breathing drive or projectiles in question.
  • the distribution unit or distribution structure of the carrier missile can preferably be separated from it before the additional braking measures are taken. Two or more separable distribution units per carrier missile can also be provided.
  • the daughter missiles which are designed as combat bodies to combat moving targets, are housed in or on the distribution unit by z. B. arranged in discharge pipes or on start rails or attached by means of notching devices.
  • the search device is designed in a known manner, for example as an optical or infrared sensor, but preferably as a radar sensor.
  • the likewise known electronic evaluation device arranged downstream of the sensor has at least one computer with a storage device.
  • the use of a more sophisticated sensor is provided according to claim 2, which works already in the launch phase of the carrier missile and does not first respond to the individual targets to be fought, but rather can detect a target area formed from several individual targets from a greater distance, which is only resolved by the sensor when the sensor approaches the individual targets.
  • the desired braking of the distribution unit and its preferred separation from the rest of the carrier missile are then triggered in an optimal manner.
  • This central search and evaluation device thus enables an autonomous determination of the times for the braking of the distribution unit and for the release of the daughter missiles and thus an independent correction of reconnaissance errors and the missile scatter.
  • a pre-phase guidance for the daughter missiles can be carried out after detecting the target area, in that for the carrier missile or the distribution unit separate therefrom a within the framework of the aeroballistic, ie. H. aerodynamic and ballistic possibilities optimal descent path is calculated, which by adjustable aerodynamic surfaces such as paraglider, wing etc. or z. B. can also be achieved by control nozzles. This allows an even more precise approximation to the area to be combated, in particular to an accumulation of individual targets in this area, in an advantageous manner.
  • a central search and command device is arranged on the carrier missile or on the distribution unit for the individual daughter missiles to be released one after the other, there are various possibilities for their separation.
  • the daughter missile can be ejected by means of a pyrotechnic charge from launch tubes attached to the distribution unit.
  • this simple solution is associated with reaction forces which cause the distribution unit or the carrier missile to oscillate after the individual launches.
  • the consideration of these pendulum movements when the subsequent daughter missiles are released by the computer of the search and command device can make the system undesirably complex, while an increased aerodynamic damping of the arrangement affects the system time, i. H. can make the period of time until the pendulum movement calms down sufficiently for the next launch.
  • the launch tubes, start rails or the like can be provided so as to be pivotable about the center of gravity of the distribution structure and to assign the daughter missiles to them - together with a compensation mass that may be provided that their focus coincides with that of the distribution structure.
  • This ensures that there is no shift in the center of gravity in the axial direction, ie. H. comes in the longitudinal direction of the distribution unit.
  • This applies to the observation in a side view of the distribution unit, in which the launch tubes, start rails or the like can be pivoted, so to speak, about the height coordinate of the center of gravity of the distribution unit.
  • the launch tubes, starting rails or the like cannot be arranged in one plane, but have to be slightly offset from one another, there is still a shift in the center of gravity in the lateral direction, which is, however, slight.
  • the demands on the daughter missiles are comparatively low.
  • the child missiles or child projectiles are therefore preferably unguided.
  • the task and the result of a possible system analysis are possible combinations that range, for example, from the targeted laying of cluster munitions and the launching of armored fighter-like missiles to simple orbit correction devices for the daughter missiles. But even daughter missiles that are directed to the final phase can be distributed using the method according to the invention, if this proves to be advantageous despite the effort in terms of the target probability.
  • the range of spread is not fixedly predetermined before the launch vehicle is fired, but is instead determined autonomously by the central search and evaluation device.
  • the carrier missile not shown, preferably an unguided rocket, is launched by means of the launcher 1 below the elevation 6 0 and moves on the orbit A.
  • the targets to be combated are assumed in the target area Z due to previous reconnaissance, it is known in Due to appropriate data input prior to launch, the head containing the distribution unit was separated from the rest of the carrier missile at point I and delayed, for example by means of a parachute or brake flaps, to point 11, at which the path speed was reduced sufficiently and the path inclination was so close to the vertical that accordingly DE-A-21 53 994 the launch tubes of the distribution unit can be spread apart.
  • the ogive 2 of the head or the distribution unit 3, which is only indicated by dashed lines in FIG. 2, is separated with a brake parachute 4, so that the search head 5, which is firmly connected to the distribution unit, already has a correspondingly large target area from a great height Z can capture.
  • the descent path of the distribution unit 3, which is optimal within the scope of the aeroballistic possibilities and which can be achieved by means of a paraglider or other correspondingly adjustable asymmetrical aerodynamic surfaces, is then preferably calculated via a computer connected to the search head 5.
  • the launch tubes 6, each with a subsidiary floor located therein are spread apart, which further reduces the speed of the distribution unit.
  • the distribution unit 3 has the configuration K shown in FIG. 2 and is located at a height h above the target area Z. From this height, the targets on the outer edge of the ' target area can first be passed due to the aeroballistic behavior of the subsidiary storeys stored in the computer The choice of a suitable time for shooting. Since the target area is a surface, all outer lines can be detected by a slight rotation of the distribution unit about its longitudinal axis 7. The necessary torque. ment about the longitudinal axis is preferably aerodynamically, for. B. generated by the parachute 4. The targets further in the center of the target area Z can be fought if the warhead has sunk further.
  • the processes at point I can be triggered autonomously by the search device when the target area Z is located.
  • This determination of the target coordinates only shortly before the combat is particularly advantageous in the case of targets that move quickly because - as shown in FIG. 1 - different target areas Z or Z on the same primary trajectory A, depending on the trigger points I or I 'and 11 or II' 'can be recorded.
  • the warhead is again at a height h above the target area Z', from which the targets according to FIG. 2 can be combated.
  • FIG. 3 shows a distribution unit 3 with a brake parachute 4 and a search evaluation device 5, the launch tubes 6 of which can be pivoted about their center of gravity S and that of the distribution unit 3. To simplify the drawing, only two launch tubes 6 arranged closely one behind the other are shown in their extended position.
  • the daughter missiles are also arranged within the launch tubes so that their center of gravity coincides with that of the distribution unit in the drawing plane, there is no ver when a daughter missile is launched shift of the center of gravity in the direction of the longitudinal axis 7.
  • the shift in the center of gravity due to the arrangement of the launch tubes 6 one behind the other is small, so that pendulum movements of the distribution unit 3 due to mass changes are largely eliminated.
  • the daughter missiles can be provided with simple correction devices for their trajectory. According to FIG. 4, a distribution unit 3 can then be used with launch tubes 6 that are only slightly or even not spread outwards, whereby the lateral shift in the center of gravity that occurs after a launch is advantageously kept small.
  • the daughter missiles can be provided with fold-out oars (control surfaces) so that they move on the trajectory B, while the distribution unit 3 moves on the vertical descent path C.
  • the separation from the tube 4 and flying through the web B can be done solely by the weight or supplemented by a drive.
  • the lateral distance of the daughter missiles on orbit B from the vertical orbit C of distribution unit 3, which is necessary to combat the targets, can be achieved, as in FIG. 2, by the ejection height and / or by varying the rudder setting angle.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Claims (6)

1. Procédé pour distribuer des projectiles de combat, selon lequel un missile porteur (ou selon le cas une unité distributrice (3) affectée à ce missile porteur) de projectiles de combat consistant en deux missiles portés ou plus est, avant que les projectiles ne soient libérés, décéléré au moyen de dispositifs de freinage auxiliaires (4) et amené à une position de libération des projectiles prédéterminée, caractérisé par le fait que la libération individuelle de chacun des missiles portés est commandée, en fonction de l'acquisition de l'objectif correspondant, par une centrale de détection (5) commune, affectée à l'unité distributrice (3), et à laquelle est reliée un dispositif d'interprétation.
2. Procédé selon la revendication 1, caractérisé en ce que le dispositif de détection (5) sert également à commander, en fonction de l'acquisition de la zone des objectifs (Z), le début du freinage du missile porteur ou de l'unité distributrice (3) et le déclenchement de la séparation préférable de l'unité distributrice (3) du reste du missile porteur.
3. Procédé selon la revendication 1 ou 2, caractérisé en ce que, à la suite de l'acquisition par le dispositif (5) de la zone visée (Z), le dispositif d'interprétation relié au dispositif de détection (5) détermine la trajectoire de descente optimale du missile porteur ou, selon le cas, de l'unité distributrice (3), et des corrections adéquates de trajectoire sont effectuées.
4. Procédé selon l'une quelconque des revendications 1, 2, 3, caractérisé en ce que, afin d'éviter le bombardement multiple d'un objectif, les coordonnées de l'objectif d'un projectile libéré sont mémorisées dans le dispositif d'interprétation, et interdites aux projectiles restants.
5. Procédé selon l'une quelconque des revendications 1, 2, 3, 4, caractérisé en ce que, pour libérer les projectiles, on utilise le principe de la propulsion par fusée ou du canon de Davis, avec une masse compensatrice éjectable en sens opposé du projectile.
6. Procédé selon l'une quelconque des revendications 1, 2, 3, 4, 5, caractérisé en ce que, les projectiles sont éjectés hors des tubes de lancement (6), rails de lancement ou autres dispositifs similaires qui - si l'on considère l'unité distributrice (3) en vue latérale - peuvent pivoter autour du centre de gravité (S) de celle-ci, et dans ou sur lesquels les projectiles sont disposés de telle sorte que - en se plaçant toujours dans la même vue latérale - leur centre de gravité coïncide au moins approximativement avec celui de l'unité distributrice (3) ; ainsi, la libération des projectiles n'entraîne pratiquement aucune modification de la position du centre de gravité de l'unité distributrice (3) sur l'axe longitudinal de celle-ci.
EP81107358A 1980-10-10 1981-09-17 Procédé pour distribuer des munitions de combat Expired EP0049778B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3038295 1980-10-10
DE19803038295 DE3038295A1 (de) 1980-10-10 1980-10-10 Verfahren zum verteilen von gefechtskoerpern

Publications (2)

Publication Number Publication Date
EP0049778A1 EP0049778A1 (fr) 1982-04-21
EP0049778B1 true EP0049778B1 (fr) 1985-01-30

Family

ID=6114077

Family Applications (1)

Application Number Title Priority Date Filing Date
EP81107358A Expired EP0049778B1 (fr) 1980-10-10 1981-09-17 Procédé pour distribuer des munitions de combat

Country Status (2)

Country Link
EP (1) EP0049778B1 (fr)
DE (2) DE3038295A1 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2534370B1 (fr) * 1982-10-11 1986-12-19 Luchaire Sa Engin destine a l'attaque en survol d'objectifs tels que notamment des blindes
DE3319824A1 (de) * 1983-06-01 1984-12-06 Diehl GmbH & Co, 8500 Nürnberg Verfahren zum bekaempfen von zielobjekten mittels bomblets und bomblet-traegerkoerper zum ausueben des verfahrens
GB2392227A (en) * 2002-08-20 2004-02-25 Eric Robinson Warhead

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3216321A (en) * 1964-01-07 1965-11-09 Fay E Null Multi-ring dart warhead
DE2032126C3 (de) * 1970-06-30 1980-08-28 Messerschmitt-Boelkow-Blohm Gmbh, 8000 Muenchen Sperrsystem für Gewässer
FR2144917A5 (fr) * 1971-07-02 1973-02-16 Serat
BE790638A (fr) * 1971-10-29 1973-02-15 Dynamit Nobel Ag Tete d'ejection, en particulier pour des fusees
FR2204294A5 (fr) * 1972-10-25 1974-05-17 Cnim
DE2347374C2 (de) * 1973-09-20 1982-05-13 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Abstandszünder für einen Gefechtskopf
DE2532479C3 (de) * 1975-07-19 1980-11-27 Messerschmitt-Boelkow-Blohm Gmbh, 8000 Muenchen Verfahren zur Bekämpfung von Erdzielen mittels eines zur Luftaufklärung ausgerüsteten fernlenkbaren Fluggerätes und eines weiteren mit Waffen ausgerüsteten fernlenkbaren Fluggerätes sowie zweier ortsfester Sendestationen

Also Published As

Publication number Publication date
DE3038295A1 (de) 1982-05-27
DE3168645D1 (en) 1985-03-14
EP0049778A1 (fr) 1982-04-21

Similar Documents

Publication Publication Date Title
EP0636852B1 (fr) Roquette d'artillerie comportant des ailettes de guidage du type canard
DE19740888C2 (de) Verfahren zum autonomen Lenken eines drallstabilisierten Artilleriegeschosses und autonom gelenktes Artilleriegeschoß zur Durchführung des Verfahrens
EP0062750B1 (fr) Procédé pour disperser des charges actives à partir d'un engin porteur
EP0049005B1 (fr) Dispositif pour le lancement d'objets à partir d'un avion
DE2803036A1 (de) Gelenkte bombe fuer den tiefflugeinsatz
DE69121427T2 (de) Geschoss und sein Verwendungsverfahren
DE1954540A1 (de) Spin- und rippenstabilisierte Rakete
DE3427227A1 (de) Endphasen-steuerbarer munitionsartikel und verfahren zu seiner zielnavigation
DE69523064T2 (de) Verfahren und vorrichtung zur verwendung eines von einem trägerflugzeug gestarteten gefechtskopfes zur bekämpfung von an der flugbahn des trägerflugzeuges entlang identifizierten zielen
EP2413086A2 (fr) Procédé de commande d'un corps volent articlé guidé par turbine
DE68916058T2 (de) Durch Laserstrahl und pyrotechnische Impulsgeber geführter Vektor.
EP2594891B1 (fr) Procédé destiné à repousser une fusée balistique se rapprochant en volant et système d'interception
EP0049778B1 (fr) Procédé pour distribuer des munitions de combat
DE3013405C2 (de) Verfahren zum Vermeiden des Nachrichtens von Abschußgeräten für ballistische Flugkörper
DE3522154C2 (fr)
EP3667226A1 (fr) Dispositif de commande d'un projectile avec unité de freinage activable
DE2627183C2 (de) Einrichtung zur Bekämpfung von Bodenzielen an einem fliegenden Waffenträger
EP1612504B1 (fr) Tête militaire pour munition d'artillerie
EP0187900B1 (fr) Avion non équipé pour la lutte contre cibles terrestres
DE19540252C2 (de) Verfahren zum Führen von Submunition in ein Ziel und Träger hierfür
DE4133405C2 (de) Submunition für Tiefflugeinsatz
DE19845611A1 (de) Verfahren zur Flugbahnkorrektur von Flugkörpern
DE3821218A1 (de) Verfahren zum bekaempfen eines zielobjektes von einem ueberflugprojektil aus und ueberflugprojektil zum ausueben des verfahrens
DE102011089584B4 (de) Waffensystem, insbesondere Verfahren zur effektiven Bekämpfung von Schiffszielen
DE3722038C2 (fr)

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Designated state(s): DE FR GB IT

17P Request for examination filed

Effective date: 19820813

ITF It: translation for a ep patent filed
GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Designated state(s): DE FR GB IT

REF Corresponds to:

Ref document number: 3168645

Country of ref document: DE

Date of ref document: 19850314

ET Fr: translation filed
PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed
PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 19870527

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Effective date: 19870602

GBPC Gb: european patent ceased through non-payment of renewal fee
REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Effective date: 19881118