EP0249677B1 - Fast-flying missile - Google Patents

Fast-flying missile Download PDF

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Publication number
EP0249677B1
EP0249677B1 EP87101159A EP87101159A EP0249677B1 EP 0249677 B1 EP0249677 B1 EP 0249677B1 EP 87101159 A EP87101159 A EP 87101159A EP 87101159 A EP87101159 A EP 87101159A EP 0249677 B1 EP0249677 B1 EP 0249677B1
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EP
European Patent Office
Prior art keywords
missile
tip
telescopic
telescopic tube
tip casing
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
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EP87101159A
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German (de)
French (fr)
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EP0249677A1 (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.
  • a fast-flying missile in the form of a grenade to be fired from a tube is known from US Pat. No. 3,292,879, in which a tail-tail unit is extended after the launch to stabilize the flight and to reduce pendulum vibrations.
  • This tail unit is received in the shell of the grenade when it is launched and is connected to the piston of a cylinder-piston unit which extends along the central axis of the grenade.
  • a small pyrotechnic charge is detonated at the bottom of the tail unit, the propellant gases of which flow through a channel inside the piston into the cylinder space and, when the piston is acted on, the tail unit connected to it extend out of the shell of the grenade to the rear.
  • the aerodynamic pressure point of the grenade viewed from the missile tip, is moved relatively far behind the center of gravity of the grenade, as a result of which the aerodynamic flight stability is increased.
  • the grenade reacts to disturbing aerodynamic transverse forces only relatively slowly, so that it maintains the ballistic predetermined trajectory relatively reliably and, in addition, pendulum vibrations around the pitch axis are noticeably reduced.
  • a missile which contains an active control, which consists in that the missile tip is articulated to the missile housing and can be pivoted with the aid of actuators in the form of cylinder-piston units. This pivoting takes place e.g. on the basis of the signals from a target-searching sensor, the tip of the missile then being pivoted with the aid of the actuators in such a way that it points to the target to be targeted. After swiveling the tip, the remaining grenade housing is retightened until the center axis of the tip and the grenade coincide again.
  • the invention has for its object to provide a structurally simple aerodynamic stabilizing device for a missile, with which a pendulum of the missile is counteracted.
  • 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. in the direction of flow and therefore does not generate any significant moments around the missile axis. This stabilizes the missile and pulls it into the wind when the usual pressure distribution behind the tip shell in connection with the center of gravity of the missile creates a stabilizing moment and when the disturbing torques on the tip shell - which are largely due to what is happening 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 la 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 FIG. 1a through an intermediate position according to FIG. 1b into the active position according to FIG. 1c, in which it is used to stabilize the grenade serves.
  • 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.
  • 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.
  • 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 through the channels 20 into the telescopic cylinder 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.
  • 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.e. 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 come into contact on the inner and outer telescopic tube, 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. In the state shown in FIG. 1 c, 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 currents could be kept to a minimum. These disturbances are 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 in the position of the tip casing shown in FIG. 1c, flows parallel to the axis during the flight, 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.

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)
  • Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
  • Escalators And Moving Walkways (AREA)
  • Transition And Organic Metals Composition Catalysts For Addition Polymerization (AREA)

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.

Aus der US-A 3 292 879 ist ein schnellfliegender Flugkörper in Form einer aus einem Rohr abzuschie- ßenden Granate bekannt, bei der nach dem Abschuß zur Stabilisierung des Fluges und zur Verminderung von Pendelschwingungen ein heckseitiges Leitwerk ausgefahren wird. Dieses Leitwerk ist beim Abschuß im Gehäuse der Granate aufgenommen und mit dem Kolben einer Zylinder-Kolbeneinheit verbunden, die sich entlang der Mittelachse der Granate erstreckt. Beim Abschuß wird eine kleine pyrotechnische Ladung am Boden des Leitwerkes gezündet, dessen Treibgase durch einen Kanal innerhalb des Kolbens in den Zylinderraum strömen und durch Beaufschlagung des Kolbens das mit diesem verbundene Leitwerk aus dem Gehäuse der Granate nach hinten ausfahren. Durch diese Maßnahme wird der aerodynamische Druckpunkt der Granate von der Flugkörperspitze aus betrachtet relativ weit hinter den Massenschwerpunkt der Granate verlegt, wodurch die aerodynamische Flugstabilität erhöht wird. Die Granate reagiert auf störende aerodynamische Querkräfte nur relativ träge, so daß sie die ballistisch vorgegebene Flugbahn relativ sicher einhält und zudem Pendelschwingungen um die Nickachse merklich reduziert werden.A fast-flying missile in the form of a grenade to be fired from a tube is known from US Pat. No. 3,292,879, in which a tail-tail unit is extended after the launch to stabilize the flight and to reduce pendulum vibrations. This tail unit is received in the shell of the grenade when it is launched and is connected to the piston of a cylinder-piston unit which extends along the central axis of the grenade. When fired, a small pyrotechnic charge is detonated at the bottom of the tail unit, the propellant gases of which flow through a channel inside the piston into the cylinder space and, when the piston is acted on, the tail unit connected to it extend out of the shell of the grenade to the rear. As a result of this measure, the aerodynamic pressure point of the grenade, viewed from the missile tip, is moved relatively far behind the center of gravity of the grenade, as a result of which the aerodynamic flight stability is increased. The grenade reacts to disturbing aerodynamic transverse forces only relatively slowly, so that it maintains the ballistic predetermined trajectory relatively reliably and, in addition, pendulum vibrations around the pitch axis are noticeably reduced.

Mit der bekannten Konstruktion ist es jedoch nicht möglich, schnell auf auch kurzfristige Querkräfte zu reagieren; insbesondere kann bei dieser Konstruktion der Granate keine Gegenkraft erzeugt werden, die eine störende Querkraft kompensiert. Die Flugbahn der Granate wird daher mehr oder minder von der ballistisch vorgegebenen Flugbahn abweichen.With the known construction, however, it is not possible to react quickly to short-term transverse forces; in particular, with this design of the grenade, no counterforce can be generated that compensates for a disruptive transverse force. The trajectory of the grenade will therefore deviate more or less from the ballistic trajectory.

Aus der WO A-82/03453 ist ein Flugkörper bekannt, der eine aktive Steuerung enthält, die darin besteht, daß die Flugkörperspitze gelenkig an dem Flugkörpergehäuse befestigt und mit Hilfe von Aktuatoren in Form von Zylinder-Kolbeneinheiten verschwenkt werden kann. Diese Verschwenkung erfolgt z.B. aufgrund der Signale eines zielsuchenden Sensors, wobei die Spitze des Flugkörpers dann mit Hilfe der Aktuatoren so verschwenkt wird, daß sie auf das anzufliegende Ziel weist. Nach dem Verschwenken der Spitze wird das übrige Granatengehäuse nachgezogen, bis die Mittelachse der Spitze und der Granate wieder zusammenfallen.From WO A-82/03453 a missile is known which contains an active control, which consists in that the missile tip is articulated to the missile housing and can be pivoted with the aid of actuators in the form of cylinder-piston units. This pivoting takes place e.g. on the basis of the signals from a target-searching sensor, the tip of the missile then being pivoted with the aid of the actuators in such a way that it points to the target to be targeted. After swiveling the tip, the remaining grenade housing is retightened until the center axis of the tip and the grenade coincide again.

Dieses aktive System könnte zwar auch eine automatische Kompensation von auf den Flugkörper wirkenden Querkräften ermöglichen, jedoch wären hierzu zusätzliche Sensoren notwendig. Die durch die aktive Steuerung des Flugkörpers bereits notwendig komplizierte Konstruktion würde daher noch aufwendiger.Although this active system could also automatically compensate transverse forces acting on the missile, additional sensors would be necessary for this. The complicated construction already necessary due to the active control of the missile would therefore be even more complex.

Der Erfindung liegt die Aufgabe zugrunde, eine konstruktiv einfache aerodynamische Stabilisiervorrichtung für einen Flugkörper anzugeben, mit der einer Pendelung des Flugkörpers entgegen gewirkt wird.The invention has for its object to provide a structurally simple aerodynamic stabilizing device for a missile, with which a pendulum of the missile is counteracted.

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 Anströmrichtung und erzeugt somit keine wesentlichen Momente um die Flugkörperachse. Hierdurch wird der Flugkörper stabilisiert und in den Wind gezogen, wenn die übliche Druckverteilung 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. in the direction of flow and therefore does not generate any significant moments around the missile axis. This stabilizes the missile and pulls it into the wind when the usual pressure distribution behind the tip shell in connection with the center of gravity of the missile creates a stabilizing moment and when the disturbing torques on the tip shell - which are largely due to what is happening 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 la bis c zeigen jeweils einen Schnitt durch eine Granatenspitze mit einer Spitzenhülle die mit Hilfe eines Teleskopzylinders aus einer Ruheposition gemäß Figur 1 a über eine Zwischenposition gemäß Figur 1 b in die Wirkstellung gemäß Figur 1 c gebracht wird, in der sie zum Stabilisieren der Granate dient.Figures la 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 FIG. 1a through an intermediate position according to FIG. 1b into the active position according to FIG. 1c, in which it is used to stabilize the grenade serves.

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 zugeordnet 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. By Most extendable telescopic tube 9, a second extendable telescopic tube 12 is mounted.

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. Ober 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 through the channels 20 into the telescopic cylinder 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 1 b 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 1 b.

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 1 c 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.e. 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 come into contact on the inner and outer telescopic tube, 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. 1 c, 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 currents could be kept to a minimum. These disturbances are 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, in the position of the tip casing shown in FIG. 1c, flows parallel to the axis during the flight, 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. A fast-flying missile (1), more especially a shell flying at supersonic speed, with a device (4, 9), which can be extended during the flight of the missile (1), for stabilising the missile (1) and for reducing the oscillation thereof, characterised in that the missile (1) has a stabilisation device in the region of the nose of the missile a rotationally-symmetrical substantially conical tip casing (4) which, counterbalanced, is mounted so as to be freely swingable all round on a bearing point (23) situated on the longitudinal axis (3) of the missile.
2. A missile according to claim 1, characterised in that the tip casing is mounted at the front end (15) of a telescopic cylinder (7, 8, 9, 12) which can be extended in the direction of the longitudinal axis (3) of the missile and which is connected on its other side to the housing (2) of the missile.
3. A missile according to claim 2, characterised in that the telescopic cylinder (7, 81, 9, 12) has one telescopic tube (7, 8) which is securely connected to the housing (2) of the missile and two telescopic tubes (9, 12) which can be extended successively, in that the tip casing (4) during the extension of the telescopic tube (9) which slides in the fixed telescopic tube (7, 8) and which can be extended first is held in a form-locking manner on a front shoulder (17) of this telescopic tube (9), and in that the bearing point (23) for the tip casing (4) is provided at the front end (15) of the second telescopic tube (12) which can be run out subsequently along with release of the form-locking connection between the shoulder (17) and the tip casing (4).
4. A missile according to claim 2 or 3, characterised in that the telescopic cylinder (7, 8, 9, 12) is pneumatically actuable.
5. A missile according to claim 4, characterised in that a gas generator (18) is provided for the actuation of the telescopic cylinder (7, 8, 9, 12).
6. A missile according to claim 5, characterised in that the gas generator (18) additionally communicates with blow-out apertures (21) which are arranged between the telescopic cylinder and the inside wall of the tip casing (4) in a rotationally-symmetrical manner around the longitudinal axis (3) of the missile.
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

Publications (2)

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

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ID=6298446

Family Applications (1)

Application Number Title Priority Date Filing Date
EP87101159A Expired - Lifetime EP0249677B1 (en) 1986-04-11 1987-01-28 Fast-flying missile

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US (1) US4756492A (en)
EP (1) EP0249677B1 (en)
DE (1) DE3612175C1 (en)
NO (1) NO161463C (en)

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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

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Also Published As

Publication number Publication date
NO871505L (en) 1987-10-12
NO871505D0 (en) 1987-04-10
EP0249677A1 (en) 1987-12-23
DE3612175C1 (en) 1987-10-08
NO161463B (en) 1989-05-08
NO161463C (en) 1989-08-16
US4756492A (en) 1988-07-12

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