EP0249677A1 - Fast-flying missile - Google Patents

Fast-flying missile Download PDF

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Publication number
EP0249677A1
EP0249677A1 EP87101159A EP87101159A EP0249677A1 EP 0249677 A1 EP0249677 A1 EP 0249677A1 EP 87101159 A EP87101159 A EP 87101159A EP 87101159 A EP87101159 A EP 87101159A EP 0249677 A1 EP0249677 A1 EP 0249677A1
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EP
European Patent Office
Prior art keywords
missile
tip
telescopic
telescopic cylinder
telescopic tube
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.)
Granted
Application number
EP87101159A
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German (de)
French (fr)
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EP0249677B1 (en
Inventor
Walter Kranz
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Airbus Defence and Space GmbH
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Messerschmitt Bolkow Blohm AG
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Publication of EP0249677A1 publication Critical patent/EP0249677A1/en
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    • 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
    • F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
    • F42B10/38—Range-increasing arrangements
    • F42B10/42—Streamlined projectiles
    • F42B10/46—Streamlined nose cones; Windshields; Radomes
    • 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
    • F42B10/62—Steering by movement of flight surfaces

Definitions

  • the invention relates to a fast-flying missile, in particular a grenade flying at supersonic speeds, according to the preamble of claim 1.
  • Such missiles can be stabilized in that aerodynamically effective structural parts, for. B. fins, oars, a tail cone or the like so interpreted that the pressure point from the missile tip comes to lie behind the center of gravity of the missile.
  • aerodynamically effective structural parts for. B. fins, oars, a tail cone or the like so interpreted that the pressure point from the missile tip comes to lie behind the center of gravity of the missile.
  • Such measures can limit the area of application of a missile, in particular a grenade flying at supersonic speed, or may require relatively complicated mechanical solutions, in particular if the missile has to be fired from a tube.
  • Either special constructions must be provided on the launch tube or the aerodynamically effective structural parts must be able to be swung into the contour of the missile during launch.
  • the invention has for its object to provide a structurally simple aerodynamic stabilizing device without increasing the caliber of the missile to be launched without swirl.
  • a stabilized device serves as a mass-balanced, freely movable tip shell of the missile, the center of gravity of which essentially coincides with the bearing point.
  • the pressure point lies behind the bearing point in order to keep the tip cover aerodynamically stable. Due to the pressure distribution, the tip cover is directed into the wind during flight, i.e. H. into the inflow device and thus generates no significant moments about the missile axis. This stabilizes the missile and pulls it into the wind when the usual pressure distribution behind the tip hull in connection with the center of gravity of the missile generates a stabilizing moment and when the disturbing torques on the tip hull - which are largely due to the events behind and in it - are low.
  • the construction and storage of the tip cover are relatively simple, in any case the caliber of the missile is not enlarged by the tip cover, so that it can be easily launched as a fast-flying grenade without swirl from a launch tube.
  • the tip cover is advantageously mounted at the front end of a telescopic cylinder, which is only extended a certain time after the missile has been launched, when the inflow conditions on the tip cover no longer have a destabilizing effect on it.
  • the telescopic cylinder can be extended mechanically or pyrotechnically according to claim 5.
  • Figures 1a to c each show a section through a grenade tip with a tip casing which is brought with the aid of a telescopic cylinder from a rest position according to Figure 1a via an intermediate position according to Figure 1b into the active position according to Figure 1c, in which it serves to stabilize the grenade.
  • a grenade 1 flying at supersonic speed has a cylindrical housing 2 with a longitudinal axis 3, only partially indicated in the figures, to which a thin-walled, conical tip shell 4 adjoins as the missile tip.
  • a balancing core 5 is located, which penetrates the target upon impact.
  • the cylindrical grenade housing 2 is closed off from the tip shell 4 by a partition 6 which carries a guide body 7 which is designed in the manner of a truncated cone and projects into the tip shell 4.
  • the balancing core 5 penetrating the partition 6 is surrounded over part of its length with a guide sleeve 8.
  • a first telescopic tube 9 slides between this fixed guide sleeve and the truncated cone guide body, which carries a stop 10 at the rear end facing the partition 6, to which a corresponding stop 11 on the guide body 7 is assigned at a distance.
  • a second extendable telescopic tube 12 is mounted in the first extendable telescopic tube 9.
  • the extension length of this telescopic tube 12 is limited by two stops 13 and 14 on the two telescopic tubes 12 and 9, respectively.
  • the telescopic tube 12 has at its front end a tip 15 located on the longitudinal axis 3, which is opposite a recess 16 with a triangular cross section in a front insert part of the tip cover 4.
  • the tip cover 4 In the rest position of the tip cover 4 according to FIG. 1a, the tip cover 4 is supported on the one hand by the guide body 7 in the region of the partition and on the other on an outer front shoulder 17 on the telescopic tube 9.
  • the tip 15 and the recess 16 do not interlock.
  • an annular gas generator 18 is located adjacent to the partition 6, the pyrotechnic propellant charge of which can be ignited by a mass ring 19.
  • the gas generator is connected via several channels 20 to the telescopic cylinder formed from the guide body 7, guide sleeve 8 and the two telescopic tubes 9 and 12, the channels 20 opening into the telescopic cylinder behind the stop 10 of the telescopic tube 9.
  • further channels 21 extend from the gas generator 18 and open into the space between the guide body 7 and the tip cover 4.
  • an annular slot 22 is released between the stop 10 of the telescopic tube 9 and the guide sleeve 8, so that the gas from the gas generator can now flow into the interior of the telescopic tube 9 and thereby push the second extendable telescopic tube 12 forward.
  • its tip 15 runs into the recess 16 of the tip cover, so that this in the manner of a tip bearing at the point of contact, i. H. is supported at bearing point 23.
  • the inner telescopic tube 12 is extended further, the positive connection of the tip cover 4 on the shoulder 17 of the first telescopic tube is released.
  • the stops 13 and 14 on the inner and outer telescopic tube come into contact, the tip cover 4 has reached a position according to FIG.
  • the bearing point 23 is selected so that it lies before the aerodynamic pressure point.
  • the tip sheath 4 can be directed into the incoming wind.
  • the described delayed release of the tip cover 4 takes place only after a sufficiently large distance between the rear edge 24 and the partition 6 has been reached, so that asymmetrical suction effects from the inside of the tip cover or backflow asymmetries in the region of the rear edge 24, which are caused by drawn-in air flows could be kept to a minimum. These disorders will be also kept low by blowing gas into the tip sheath via the channels 21. If the disturbances occurring when the rear edge 24 is detached from the support on the support body 7 are only slight, the tip cover 4 can also be pushed forward by jointly extending the two telescopic tubes 9 and 12. In such a case it is e.g. B. possible to extend the telescopic cylinder using a mechanical spring.
  • the grenade 1 If the grenade 1 is flown parallel to the axis in the position of the tip casing shown in FIG. 1c, it remains in the ideal flight state in which the direction of flight and the direction of the longitudinal axis 3 coincide. However, if this inflow changes due to an oscillation of the grenade, the freely movable tip cover 4 is directed into the wind, so that the tip cover axis no longer coincides with the longitudinal axis 3 of the grenade 1. This results in different flow conditions on opposite sides in the area of the grenade housing 2, so that it is pulled into the wind, so to speak. This counteracts the swinging of the grenade and stabilizes the grenade.
  • the tip bearing between the inner telescopic tube 12 and the tip cover 4 can of course by other bearings, for. B. be replaced by a ball guide of the tip cover on the telescopic tube.

Abstract

Die Erfindung bezieht sich auf einen schnellfliegenden Flugkörper, insbesondere eine mit Überschallgeschwindigkeit fliegende Granate (1) mit einer Vorrichtung zum Stabilisieren des Flugkörpers und zur Verminderung von dessen Pendelung. Der Flugkörper (1) weist im Bereich der Flugkörperspitze eine rotationssymmetrische Spitzenhülle (4) auf, die massenausgeglichen um einen auf der Flugkörperlängsachse (3) gelegenen Lagerpunkt (23) allseitig frei schwenkbar gelagert ist.The invention relates to a fast-flying missile, in particular a grenade (1) flying at supersonic speeds, with a device for stabilizing the missile and for reducing its oscillation. The missile (1) has a rotationally symmetrical tip cover (4) in the area of the missile tip, which is mass-balanced and freely pivotable on all sides about a bearing point (23) located on the missile longitudinal axis (3).

Description

Die Erfindung bezieht sich auf einen schnellfliegenden Flugkörper, insbesondere eine mit Überschallgeschwin­digkeit fliegende Granate gemäß dem Oberbegriff des Patentanspruches 1.The invention relates to a fast-flying missile, in particular a grenade flying at supersonic speeds, according to the preamble of claim 1.

Derartige Flugkörper können dadurch stabilisiert werden, daß man aerodynamisch wirksame Strukturteile, z. B. Finnen, Ruder, einen Heckkonus oder dergleichen so auslegt, daß der Druckpunkt von der Flugkörperspitze aus betrachtet hinter dem Flugkörperschwerpunkt zu liegen kommt. Derartige Maßnahmen können den Anwendungs­bereich eines Flugkörpers, insbesondere einer mit Über­schallgeschwindigkeit fliegenden Granate einschränken oder erfordern gegebenenfalls relativ komplizierte mechanische Lösungen, insbesondere dann, wenn der Flug­körper aus einem Rohr verschossen werden muß. Hier müssen entweder Sonderkonstruktionen am Abschußrohr vorgesehen werden oder die aerodynamisch wirksamen Strukturteile müssen während des Abschusses in die Kontur des Flugkörpers eingeschwenkt werden können.Such missiles can be stabilized in that aerodynamically effective structural parts, for. B. fins, oars, a tail cone or the like so interpreted that the pressure point from the missile tip comes to lie behind the center of gravity of the missile. Such measures can limit the area of application of a missile, in particular a grenade flying at supersonic speed, or may require relatively complicated mechanical solutions, in particular if the missile has to be fired from a tube. Either special constructions must be provided on the launch tube or the aerodynamically effective structural parts must be able to be swung into the contour of the missile during launch.

Eine weitere Möglichkeit ist eine Drallstabilisierung von Granaten. Dies setzt einen hohen Konstruktionsauf­wand für das Abschußrohr mit Drallzügen voraus, wobei beim Abschuß sowohl das Abschußrohr als auch der Flug­körper stark mechanisch belastet werden. Außerdem verrin­gert sich durch eine Drallstabiliserung die Reichweite des Flugkörpers.Another possibility is swirl stabilization of grenades. This requires a high design effort for the launch tube with twist trains, whereby both the launch tube and the missile are subjected to high mechanical loads during launch. Swirl stabilization also reduces the range of the missile.

Der Erfindung liegt die Aufgabe zugrunde, eine konstruk­tiv einfache aerodynamische Stabilisiervorrichtung anzugeben, ohne das Kaliber des ohne Drall abzuschießenden Flugkörpers zu vergrößern.The invention has for its object to provide a structurally simple aerodynamic stabilizing device without increasing the caliber of the missile to be launched without swirl.

Diese Aufgabe ist gemäß der Erfindung durch die im kennzeichnenden Teil des ersten Patentanspruchs angegebe­nen Merkmale gelöst.This object is achieved according to the invention by the features specified in the characterizing part of the first claim.

Demnach dient als Stabilisiervorrichtung eine massenausge­glichen allseitig frei bewegbare Spitzenhülle des Flugkörpers, deren Schwerpunkt im wesentlichen mit dem Lagerpunkt zusammenfällt. Deren Druckpunkt liegt hinter dem Lagerpunkt, um die Spitzenhülle aerodynamisch stabil zu halten. Aufgrund der Druckverteilung richtet sich die Spitzenhülle während des Fluges in den Wind, d. h. in die Anströmvorrichtung und erzeugt somit keine wesentlichen Momente um die Flugkörperachse. Hierdurch wird der Flugkörper stabilisiert und in den Wind gezogen, wenn die übliche Duckverteilung hinter der Spitzenhülle im Zusammenhang mit dem Flugkörperschwerpunkt ein stabilisierendes Moment erzeugt und wenn die Störmomente auf die Spitzenhülle - die weitgehend bedingt sind vom Geschehen hinter und in ihr - gering sind.Accordingly, a stabilized device serves as a mass-balanced, freely movable tip shell of the missile, the center of gravity of which essentially coincides with the bearing point. The pressure point lies behind the bearing point in order to keep the tip cover aerodynamically stable. Due to the pressure distribution, the tip cover is directed into the wind during flight, i.e. H. into the inflow device and thus generates no significant moments about the missile axis. This stabilizes the missile and pulls it into the wind when the usual pressure distribution behind the tip hull in connection with the center of gravity of the missile generates a stabilizing moment and when the disturbing torques on the tip hull - which are largely due to the events behind and in it - are low.

Die Konstruktion und Lagerung der Spitzenhülle sind relativ einfach, auf jeden Fall wird durch die Spitzenhülle das Ka­liber des Flugkörpers nicht vergrößert, so daß dieser als schnellfliegende Granate ohne Drall aus einem Abschußrohr ein­fach abgeschossen werden kann. Die Spitzenhülle ist gemäß Anspruch 2 vorteilhaft am vorderen Ende eines Teleskopzylinders gelagert, der erst gewisse Zeit nach dem Abschuß des Flugkörpers ausgefahren wird, wenn die Anströmverhältnisse an der Spitzenhülle auf diese nicht mehr destabilisierend wirken.The construction and storage of the tip cover are relatively simple, in any case the caliber of the missile is not enlarged by the tip cover, so that it can be easily launched as a fast-flying grenade without swirl from a launch tube. The tip cover is advantageously mounted at the front end of a telescopic cylinder, which is only extended a certain time after the missile has been launched, when the inflow conditions on the tip cover no longer have a destabilizing effect on it.

Der Teleskopzylinder kann mechanisch oder pyrotechnisch gemäß Anspruch 5 ausfahrbar sein.The telescopic cylinder can be extended mechanically or pyrotechnically according to claim 5.

Weitere Ausgestaltungen gehen aus den Unteransprüchen hervor. Die Erfindung ist in einem Ausführungsbeispiel anhand der Zeichnung näher erläutert:Further developments emerge from the subclaims. The invention is explained in more detail in an exemplary embodiment with reference to the drawing:

Figuren 1a bis c zeigen jeweils einen Schnitt durch eine Granatenspitze mit einer Spitzenhülle die mit Hilfe eines Teleskopzylinders aus einer Ruheposition gemäß Figur 1a über eine Zwischenposition gemäß Figur 1b in die Wirk­stellung gemäß Figur 1c gebracht wird, in der sie zum Stabilisieren der Granate dient.Figures 1a to c each show a section through a grenade tip with a tip casing which is brought with the aid of a telescopic cylinder from a rest position according to Figure 1a via an intermediate position according to Figure 1b into the active position according to Figure 1c, in which it serves to stabilize the grenade.

Eine mit Überschallgeschwindigkeit fliegende Granate 1 weist ein in den Figuren nur teilweise angedeutetes zylindrisches Gehäuse 2 mit einer Längsachse 3 auf, an das sich als Flugkörperspitze eine dünnwandige kege­lige Spitzenhülle 4 anschließt. In der Längsachse 3 der Granate ist ein Wuchtkern 5 gelegen, der das Ziel beim Aufschlag durchdringt. Das zylindrische Granatenge­häuse 2 ist zur Spitzenhülle 4 durch eine Trennwand 6 abgeschlossen, die einen in Art eines Kegelstumpfes ausgebildeten, in die Spitzenhülle 4 hineinragenden Führungskörper 7 trägt. Der die Tennwand 6 durchdrin­gende Wuchtkern 5 ist über einen Teil seiner Länge mit einer Führungshülse 8 umgeben. Zwischen dieser feststehenden Führungshülse und dem Kegelstumpf-Füh­rungskörper 7 gleitet ein erstes Teleskoprohr 9, welches am hinteren, der Trennwand 6 zugewandten Ende einen Anschlag 10 trägt, dem im Abstand ein korrespondieren­der Anschlag 11 an dem Führungskörper 7 zugeorndnet ist. In dem ersten ausfahrbaren Teleskoprohr 9 ist ein zweites ausfahrbares Teleskoprohr 12 gelagert.A grenade 1 flying at supersonic speed has a cylindrical housing 2 with a longitudinal axis 3, only partially indicated in the figures, to which a thin-walled, conical tip shell 4 adjoins as the missile tip. In the longitudinal axis 3 of the grenade, a balancing core 5 is located, which penetrates the target upon impact. The cylindrical grenade housing 2 is closed off from the tip shell 4 by a partition 6 which carries a guide body 7 which is designed in the manner of a truncated cone and projects into the tip shell 4. The balancing core 5 penetrating the partition 6 is surrounded over part of its length with a guide sleeve 8. A first telescopic tube 9 slides between this fixed guide sleeve and the truncated cone guide body, which carries a stop 10 at the rear end facing the partition 6, to which a corresponding stop 11 on the guide body 7 is assigned at a distance. A second extendable telescopic tube 12 is mounted in the first extendable telescopic tube 9.

Die Ausfahrlänge dieses Teleskoprohres 12 ist durch zwei Anschläge 13 und 14 an den beiden Teleskoprohren 12 bzw. 9 begrenzt. Das Teleskoprohr 12 trägt an seinem vorderen Ende eine auf der Längsachse 3 gelegene Spitze 15, der in einem vorderen Einsatzteil der Spitzenhülle 4 eine im Querschnitt dreieckförmige Ausnehmung 16 gegenüberliegt.The extension length of this telescopic tube 12 is limited by two stops 13 and 14 on the two telescopic tubes 12 and 9, respectively. The telescopic tube 12 has at its front end a tip 15 located on the longitudinal axis 3, which is opposite a recess 16 with a triangular cross section in a front insert part of the tip cover 4.

In der Ruheposition der Spitzenhülle 4 gemäß Figur 1a wird die Spitzenhülle 4 einmal durch den Führungs­körper 7 im Bereich der Trennwand und zum anderen auf einer äußeren vorderen Schulter 17 am Teleskoprohr 9 abgestützt. Die Spitze 15 und die Ausnehmung 16 grei­fen nicht ineinander.In the rest position of the tip cover 4 according to FIG. 1a, the tip cover 4 is supported on the one hand by the guide body 7 in the region of the partition and on the other on an outer front shoulder 17 on the telescopic tube 9. The tip 15 and the recess 16 do not interlock.

In dem Führungskörper 7 ist benachbart zu der Trennwand 6 ein kreisringförmiger Gasgenerator 18 gelegen, dessen pyrotechnische Treibladung durch einen Massenring 19 gezündet werden kann. Der Gasgenerator steht über mehre­re Kanäle 20 mit dem aus Führungskörper 7, Führungs -­hülse 8 und den beiden Teleskoprohren 9 und 12 gebilde­ten Teleskopzylinder in Verbindung, wobei die Kanäle 20 hinter dem Anschlag 10 des Teleskoprohres 9 in den Teleskopzylinder münden. Außerdem gehen vom Gasgenera­tor 18 noch weitere Kanäle 21 aus, die in dem Zwischen­raum zwischen Führungskörper 7 und Spitzenhülle 4 münden.In the guide body 7, an annular gas generator 18 is located adjacent to the partition 6, the pyrotechnic propellant charge of which can be ignited by a mass ring 19. The gas generator is connected via several channels 20 to the telescopic cylinder formed from the guide body 7, guide sleeve 8 and the two telescopic tubes 9 and 12, the channels 20 opening into the telescopic cylinder behind the stop 10 of the telescopic tube 9. In addition, further channels 21 extend from the gas generator 18 and open into the space between the guide body 7 and the tip cover 4.

Beim Abschuß der Granate aus dem nicht gezeigten Ab­schußrohr, wird der Massering 19 aufgrund seiner Träg­heit in Richtung auf die pyrotechnische Ladung des Gasgenerators beschleunigt und zündet diese. Über die Kanäle 20 strömt jetzt Gas in den Teleskopzylinder und drückt auf den Anschlag 10 des ersten Teleskoproh­res 9. Dieses wird nach vorn geschoben, bis der Anschlag 10 auf den Anschlag 11 am Führungskörper 7 aufläuft.When the grenade is fired from the launch tube, not shown, the mass ring 19 is accelerated due to its inertia in the direction of the pyrotechnic charge of the gas generator and ignites it. Gas now flows into the telescopic cylinder via the channels 20 and presses on the stop 10 of the first telescopic tube 9. This is pushed forward until the stop 10 hits the stop 11 on the guide body 7.

Während dieser Ausfahrbewegung wird die Spitzenhülle 4 weiterhin auf der Schulter 17 des Teleskoprohres abgestützt. Die Spitzenhülle 4 wird außerdem durch das aus den Kanälen 21 austretende Gas stabilisiert. Dieser Zwischenzustand ist in Figur 1b gezeigt.During this extension movement, the tip cover 4 is still supported on the shoulder 17 of the telescopic tube. The tip cover 4 is also stabilized by the gas emerging from the channels 21. This intermediate state is shown in Figure 1b.

In diesen Zwischenzustand wird ein Ringschlitz 22 zwi­schen dem Anschlag 10 des Teleskoprohres 9 und der Führungshülse 8 freigegeben, so daß jetzt auch das Gas des Gasgenerators in das Innere des Teleskoprohres 9 strömen kann und dabei das zweite ausfahrbare Teles­koprohr 12 nach vorne schiebt. Zunächst läuft dessen Spitze 15 in die Ausnehmung 16 der Spitzenhülle, so daß diese in Art eines Spitzenlagers am Berührungspunkt, d. h. am Lagerpunkt 23 abgestützt wird. Beim weiteren Ausfahren des inneren Teleskoprohres 12 löst sich die formschlüssige Verbindung der Spitzenhülle 4 an der Schulter 17 des ersten Teleskoprohres. Wenn die Anschlä­ge 13 und 14 am inneren und äußeren Teleskoprohr in Kontakt kommen, hat die Spitzenhülle 4 eine Lage gemäß Figur 1c erreicht, in der sie um den Lagerpunkt 23 in allen Richtungen frei schwenkbar ist. Um die Spitzen­hülle aerodynamisch zu stabilisieren, ist der Lagerpunkt 23 so gewählt, daß er vor dem aerodynamischen Druckpunkt liegt. Die Spitzenhülle 4 kann sich in dem in Figur 1c gezeigten Zustand in den anströmenden Wind richten.In this intermediate state, an annular slot 22 is released between the stop 10 of the telescopic tube 9 and the guide sleeve 8, so that the gas from the gas generator can now flow into the interior of the telescopic tube 9 and thereby push the second extendable telescopic tube 12 forward. First, its tip 15 runs into the recess 16 of the tip cover, so that this in the manner of a tip bearing at the point of contact, i. H. is supported at bearing point 23. When the inner telescopic tube 12 is extended further, the positive connection of the tip cover 4 on the shoulder 17 of the first telescopic tube is released. When the stops 13 and 14 on the inner and outer telescopic tube come into contact, the tip cover 4 has reached a position according to FIG. 1c in which it can be freely pivoted in all directions about the bearing point 23. In order to aerodynamically stabilize the tip cover, the bearing point 23 is selected so that it lies before the aerodynamic pressure point. In the state shown in FIG. 1c, the tip sheath 4 can be directed into the incoming wind.

Die geschilderte verzögerte Freigabe der Spitzenhülle 4 erfolgt erst, nachdem ein genügend großer Abstand zwischen deren Hinterkante 24 und der Trennwand 6 er­reicht ist, so daß unsymmetrische Saugeffekte aus dem Inneren der Spitzenhülle bzw. Rückstauunsymmetrien im Bereich der Hinterkante 24, die durch eingezogene Luftströmungen verursacht werden könnten, auf ein Min­destmaß beschränkt bleiben. Diese Störungen werden auch durch das Einblasen von Gas in die Spitzenhülle über die Kanäle 21 gering gehalten. Wenn die beim Ablö­sen der Hinterkante 24 von der Auflage an dem Stützkör­per 7 auftretenden Störungen nur gering sind, kann die Spitzenhülle 4 auch durch gemeinsames Ausfahren der beiden Teleskoprohre 9 und 12 nach vorne gescho­ben werden. In einem solchen Fall ist es z. B. möglich, den Teleskopzylinder mit Hilfe einer mechanischen Feder auszufahren.The described delayed release of the tip cover 4 takes place only after a sufficiently large distance between the rear edge 24 and the partition 6 has been reached, so that asymmetrical suction effects from the inside of the tip cover or backflow asymmetries in the region of the rear edge 24, which are caused by drawn-in air flows could be kept to a minimum. These disorders will be also kept low by blowing gas into the tip sheath via the channels 21. If the disturbances occurring when the rear edge 24 is detached from the support on the support body 7 are only slight, the tip cover 4 can also be pushed forward by jointly extending the two telescopic tubes 9 and 12. In such a case it is e.g. B. possible to extend the telescopic cylinder using a mechanical spring.

Wird die Granate 1 in der in Figur 1c gezeigten Lage der Spitzenhülle während des Fluges achsparallel ange­strömt, so verbleibt sie in dem idealen Flugzustand, in dem Flugrichtung und Richtung der Längsachse 3 zusammenfallen. Ändert sich jedoch diese Anströmung durch eine Pendelung der Granate, so richtet sich die frei bewegliche Spitzenhülle 4 in den Wind, so daß die Spitzenhüllenachse nicht mehr mit der Längsachse 3 der Granate 1 zusammenfällt. Hierdurch ergeben sich unterschiedliche Strömungsverhältnisse an entgegenge­setzten Seiten im Bereich des Granatengehäuses 2, so daß dieses sozusagen in den Wind gezogen wird. Der Pendelung der Granate wird hierdurch entgegengewirkt, die Granate stabilisiert.If the grenade 1 is flown parallel to the axis in the position of the tip casing shown in FIG. 1c, it remains in the ideal flight state in which the direction of flight and the direction of the longitudinal axis 3 coincide. However, if this inflow changes due to an oscillation of the grenade, the freely movable tip cover 4 is directed into the wind, so that the tip cover axis no longer coincides with the longitudinal axis 3 of the grenade 1. This results in different flow conditions on opposite sides in the area of the grenade housing 2, so that it is pulled into the wind, so to speak. This counteracts the swinging of the grenade and stabilizes the grenade.

Es wäre im übrigen auch möglich, über die Kanäle 21 gesteuert Gas in den Innenraum der Spitzenhülle 4 zu blasen, um diese gewollt aus der mit dem Granatengehäuse 2 koaxialen Lage zu zwingen. Auch hierdurch ändern sich dann die Anströmverhältnisse im Bereich des Grana­tengehäuses 2. Auf diese Möglichkeit wäre in gewissen Grenzen eine Steuerung der Granate möglich.It would also be possible to blow gas into the interior of the tip cover 4 in a controlled manner via the channels 21 in order to force it out of the position coaxial with the grenade housing 2. This also changes the inflow conditions in the area of the grenade housing 2. This option would allow the grenade to be controlled within certain limits.

Das Spitzenlager zwischen innerem Teleskoprohr 12 und Spitzenhülle 4 kann selbstverständlich durch andere Lager, z. B. durch eine Kugelführung der Spitzenhülle auf dem Teleskoprohr ersetzt werden.The tip bearing between the inner telescopic tube 12 and the tip cover 4 can of course by other bearings, for. B. be replaced by a ball guide of the tip cover on the telescopic tube.

Claims (6)

1. Schnellfliegender Flugkörper, insbesondere mit Über­schallgeschwindigkeit fliegende Granate, mit einer Vorrichtung zum Stabilisieren des Flugkörpers und zur Verminderung von dessen Pendelung, dadurch gekennzeich­net, daß der Flugkörper (1) als Stabilisiervorrichtung im Bereich der Flugkörperspitze eine rotationssymmetri­sche , im wesentlichen kegelige Spitzenhülle (4) auf­weist, die massenausgeglichen um einen auf der Flugkör­per-Längsachse (3) gelegenen Lagerpunkt (23) allseitig frei schwenkbar gelagert ist.1. Fast-flying missile, in particular grenade flying at supersonic speed, with a device for stabilizing the missile and for reducing its oscillation, characterized in that the missile (1) as a stabilizing device in the region of the missile tip has a rotationally symmetrical, essentially conical tip shell (4). has the mass-balanced freely pivotable on all sides around a bearing point (23) located on the missile longitudinal axis (3). 2. Flugkörper nach Anspruch 1, dadurch gekennzeichnet, daß die Spitzenhülle am vorderen Ende (15) eines in Richtung der Flugkörperlängsachse (3) ausfahr­baren Teleskopzylinders (7, 8, 9, 12) gelagert ist, der auf seiner anderen Seite mit dem Gehäuse (2) des Flugkörpers verbunden ist.2. Missile according to claim 1, characterized in that the tip cover at the front end (15) of a telescopic cylinder (7, 8, 9, 12) extendable in the direction of the missile longitudinal axis (3) is mounted, which on its other side with the housing ( 2) the missile is connected. 3. Flugkörper nach Anspruch 2, dadurch gekennzeichnet, daß der Teleskopzylinder (7, 8, 9, 12) ein mit dem Flugkörpergehäuse (2) fest verbundenes (7, 8) und zwei nacheinander ausfahrbare Teleskoprohre (9, 12) aufweist, daß die Spitzenhülle (4) während des Ausfahrens des in dem feststehenden Teleskoprohr (7, 8) gleitenden, zuerst ausfahrbaren Teleskoproh­res (9) auf einer vorderen Schulter (17) dieses Teleskoprohres (9) formschlüssig gehalten ist, und daß der Lagerpunkt (23) für die Spitzenhülle (4) an dem vorderen Ende (15) des zweiten anschließend unter Freigeben der formschlüssigen Verbindung zwi­schen Schulter (17) und Spitzenhülle (4) ausfahrbaren Teleskoprohres (12) vorgesehen ist.3. Missile according to claim 2, characterized in that the telescopic cylinder (7, 8, 9, 12) with the missile housing (2) firmly connected (7, 8) and two successively extendable telescopic tubes (9, 12) that Tip cover (4) during the extension of the telescopic tube (9) sliding in the fixed telescopic tube (7, 8), first extendable on a front shoulder (17) of this telescopic tube (9) is positively held, and that the bearing point (23) for the Tip sleeve (4) is provided at the front end (15) of the second telescopic tube (12) which can then be extended by releasing the positive connection between the shoulder (17) and the tip sleeve (4). 4. Flugkörper nach Anspruch 2 oder 3, dadurch gekennzei­chnet, daß der Teleskopzylinder (7, 8, 9, 12) pneu­matisch betätigbar ist.4. Missile according to claim 2 or 3, characterized in that the telescopic cylinder (7, 8, 9, 12) can be actuated pneumatically. 5. Flugkörper nach Anspruch 4, dadurch gekennzeichnet, daß für die Betätigung des Teleskopzylinders (7, 8, 9, 12) ein Gasgenerator (18) vorgesehen ist.5. Missile according to claim 4, characterized in that a gas generator (18) is provided for the actuation of the telescopic cylinder (7, 8, 9, 12). 6. Flugkörper nach Anspruch 5, dadurch gekennzeichnet, daß der Gasgenerator (18) zusätzlich mit Ausblas­öffnungen (21) kommuniziert, die zwischen Teleskop­zylinder und Innenwand der Spitzenhülloe (7) rota­tionssymmetrisch um die Flugkörperlängsachse (3) angeordnet sind.6. Missile according to claim 5, characterized in that the gas generator (18) additionally communicates with blow-out openings (21) which are arranged between the telescopic cylinder and the inner wall of the tip envelope (7) in a rotationally symmetrical manner about the missile longitudinal axis (3).
EP87101159A 1986-04-11 1987-01-28 Fast-flying missile Expired - Lifetime EP0249677B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3612175 1986-04-11
DE3612175A DE3612175C1 (en) 1986-04-11 1986-04-11 Fast flying missile

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EP0249677A1 true EP0249677A1 (en) 1987-12-23
EP0249677B1 EP0249677B1 (en) 1990-05-09

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EP (1) EP0249677B1 (en)
DE (1) DE3612175C1 (en)
NO (1) NO161463C (en)

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4998994A (en) * 1989-09-20 1991-03-12 The United States Of America As Represented By The Secretary Of The Army Aerodynamically compliant projectile nose
GB8925397D0 (en) * 1989-11-10 1992-11-04 Secr Defence Kinetic energy penetrator
DE4239589A1 (en) * 1992-11-25 1994-05-26 Deutsche Aerospace Guidance system for flying missiles - has guiding spoiler and adjuster comprising spring drive with controlled holding and release mechanism
US5794887A (en) * 1995-11-17 1998-08-18 Komerath; Narayanan M. Stagnation point vortex controller
FR2761769B1 (en) * 1997-04-08 1999-07-02 Tda Armements Sas MICRO-GOVERNOR DEVICE FOR CORRECTION OF ROTATION-STABILIZED AMMUNITION TRAJECTORY
US6389977B1 (en) * 1997-12-11 2002-05-21 Lockheed Martin Corporation Shrouded aerial bomb
US6845718B2 (en) 2002-12-18 2005-01-25 Lockheed Martin Corporation Projectile capable of propelling a penetrator therefrom and method of using same
US6796532B2 (en) * 2002-12-20 2004-09-28 Norman D. Malmuth Surface plasma discharge for controlling forebody vortex asymmetry
DE102006003638B4 (en) * 2006-01-26 2008-01-17 Deutsches Zentrum für Luft- und Raumfahrt e.V. Missile for the supersonic range
US7834301B2 (en) * 2008-04-30 2010-11-16 The Boeing Company System and method for controlling high spin rate projectiles
IL210370A (en) * 2010-12-30 2015-08-31 Israel Aerospace Ind Ltd Projectile
CN102167162A (en) * 2011-03-10 2011-08-31 洪瑞庆 Ultra-high pressure fluid jetting power track transferring system and method for aircraft
US9132908B1 (en) * 2013-03-15 2015-09-15 The Boeing Company Expandable nose cone
US10928169B2 (en) * 2019-02-07 2021-02-23 Bae Systems Rokar International Ltd. Seal for a projectile guiding kit

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3292879A (en) * 1965-06-25 1966-12-20 Canrad Prec Ind Inc Projectile with stabilizing surfaces
WO1982003453A1 (en) * 1981-04-08 1982-10-14 Thomson Keith Donald Directional control device for airborne or seaborne missiles
DE3347005A1 (en) * 1983-12-24 1985-07-04 Dynamit Nobel Ag, 5210 Troisdorf Missile

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3067682A (en) * 1960-02-18 1962-12-11 Aerojet General Co Gyro pull rocket
US3195462A (en) * 1961-05-17 1965-07-20 Aerojet General Co Pull rocket shroud
US3262655A (en) * 1963-12-26 1966-07-26 Jr Warren Gillespie Alleviation of divergence during rocket launch
IL46548A (en) * 1975-02-03 1978-06-15 Drori Mordeki Stabilized projectile with pivotable fins
US4399962A (en) * 1981-08-31 1983-08-23 General Dynamics, Pomona Division Wobble nose control for projectiles

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3292879A (en) * 1965-06-25 1966-12-20 Canrad Prec Ind Inc Projectile with stabilizing surfaces
WO1982003453A1 (en) * 1981-04-08 1982-10-14 Thomson Keith Donald Directional control device for airborne or seaborne missiles
DE3347005A1 (en) * 1983-12-24 1985-07-04 Dynamit Nobel Ag, 5210 Troisdorf Missile

Also Published As

Publication number Publication date
US4756492A (en) 1988-07-12
NO871505D0 (en) 1987-04-10
EP0249677B1 (en) 1990-05-09
NO161463C (en) 1989-08-16
DE3612175C1 (en) 1987-10-08
NO871505L (en) 1987-10-12
NO161463B (en) 1989-05-08

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