EP2354756A2 - Missile head and method for separating a cowling from the body of a missile - Google Patents
Missile head and method for separating a cowling from the body of a missile Download PDFInfo
- Publication number
- EP2354756A2 EP2354756A2 EP11000642A EP11000642A EP2354756A2 EP 2354756 A2 EP2354756 A2 EP 2354756A2 EP 11000642 A EP11000642 A EP 11000642A EP 11000642 A EP11000642 A EP 11000642A EP 2354756 A2 EP2354756 A2 EP 2354756A2
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- European Patent Office
- Prior art keywords
- nose
- missile
- parts
- rear part
- hood
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- 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.)
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
- F42B15/36—Means for interconnecting rocket-motor and body section; Multi-stage connectors; Disconnecting means
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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
Definitions
- the invention relates to a missile head with a hood forming its tip, which in its entirety is detachable from the fuselage during a flight and which comprises a rear part connected to the fuselage and a front tip which can be separated from the rear part, and with a Separator for separating the rear part of the fuselage and the nose from the rear part during the flight.
- Guided missiles have in their front area a seeker head with a tracking system, with which they can follow a target by means of optical means. Inner parts of the seeker head are typically protected by an outwardly arched window, the dome, through which radiation from a target can reach the optics of the seeker head. At the start and during the flight of the missile, the dome is exposed to mechanical and thermal stresses. To protect the dome from external influences, such as particle impact or heat, it is covered before, during and possibly even in an early flight phase after take-off in which the tracking system is not active, the dome is covered by a dome forming the tip of the missile.
- Such a hood usually obstructs the view of the sensitive tracking system and thus can only be used in a particular flight phase in which the missile is not guided through the target tracking system to the destination. Before the missile is to be guided through the target tracking system to the target, the hood must be dropped, so that an unimpeded target detection is possible.
- Such a throw-off hood is for example from the DE 102 40 040 A1 known.
- the hood is separated into a rear part and a nose arranged in front of it, which is thrown off first.
- a forwardly directed opening forms in the rear part, into which the flying wind presses in and thus generates a high back pressure in the rear part.
- the rear part is divided in two parts, which are pushed apart by the dynamic pressure and released from the hull. The dome is thereby free and the viewfinder system can guide the missile to its destination.
- a missile head of the type mentioned in which the nose is inventively divided into at least two parts and the separator is prepared for separating the nose in these two parts during the flight.
- the invention is based on the consideration that a separation of the front nose forward, ie in the direction of flight, a high mechanical force needs to reliably separate the nose from the rear of the hood.
- the separator must be strong and thus made large, so that the hood is made large.
- the force can be kept smaller for separating the nose, so that the separator dimensioned smaller and the hood can thus be made small-building.
- the missile head may include attachment means for attaching the hood to a body of the missile and the hood itself, which conveniently covers, in particular completely covers, a dome which is located under the hood and which forms the foremost part of the missile after the hood is dropped.
- the missile head may include a target tracking system for controlling the missile.
- Target have.
- the hood expediently forms the outer surface of the missile head, at least in its front region. It includes at least the front nose and. the rear part, wherein both the rear part and the nose can be divided into further, each forming an outer surface of the missile forming parts.
- the nose is in this case at least predominantly, expediently arranged completely in front of the rear part, possibly up to the Fastener and an overlap area.
- the fuselage of the missile can be formed by all other elements of the missile.
- the separability of the nose from the rear part and / or the rear part from the fuselage of the missile can be realized by a fastening means provided for fastening the parts together and for separating the parts from each other by a predetermined process.
- This predetermined process may include a predetermined force introduction into at least two parts of the hood and a separation of the parts from each other at at least one predetermined location of the fastening means, for example at a predetermined breaking point.
- the separator may include means for introducing a predetermined force into, for example, two parts of the hood to separate them.
- the separation of the nose from the rear part and / or the rear part of the fuselage can be done directly by the introduction of force or indirectly by a follow-up process, such as the occurrence of back pressure.
- the separating device is designed so that first the nose is separated from the rear part and then the rear part of the fuselage of the missile.
- the separation of the two parts of the nose by the separator can be done by the separator introduces a force in each of these two parts, for example, by a pyrotechnic charge, by which the two parts are pressed apart. This can be done a complete or partial solution of these two parts of the rear part.
- the hood with separated nose has a forward facing opening.
- back pressure can form in the rear part, which carries out the separation of the rear part of the hull, or at least facilitated.
- the separating device is expediently designed for separating the nose from the rear part, whereby an opening in the rear part is formed in flight, which causes back pressure in the rear part.
- the invention is particularly advantageous applicable to a missile with wings that cause a span of the missile, which is at least twice as large as the caliber of the missile.
- the two parts of the nose are repulsible from each other laterally to the direction of flight, expediently in opposite directions.
- the two parts of the nose are expediently formed by a longitudinal division of the nose, whereby a repelling is facilitated laterally to the direction of flight.
- the longitudinal direction is parallel to the direction of flight of the missile.
- the two parts of the nose can be directly adjacent to each other via a parting line, the two ends open in a parting line between the nose and the rear part.
- these mouths are exactly opposite each other.
- the nose and the rear part are both longitudinally divided by joints, wherein the parting line of the nose and the parting line of the rear part offset from each other open in a parting line between the nose and rear part. This allows the nose to hold the back easily and stably.
- the two parts of the nose are asymmetrical in their outer surface. After the separation of the nose in these two parts, a staggering of these parts can be achieved in the air flow, so that a return to the direction of the missile and thus damage to the missile by one of the parts is unlikely.
- the asymmetry may be related to a central axis of the missile. It can e.g. the outer surface of one part may be larger than the outer surface of the other part. Also conceivable is an asymmetrical parting line between the two front parts.
- An advantageous unstable flying behavior of the two front parts can be achieved if the tip of the nose is formed at least 5 mm behind the foremost point of only one of the two parts of the nose.
- a further advantageous embodiment of the invention provides that the missile head has in particular a flexible connecting means, via which one of the two parts of the nose, while still after a separation from rear part of this removed, remains connected to the rear part.
- the separating energy introduced by the separating means or otherwise into the removing front part may be introduced into the rear part via the connecting means, so that it is separated from the hull by the separating energy or the separating energy at least supports a separation.
- the flexibility of the connecting means can be realized by a bendability by at least 180 °, wherein the connecting means is expediently a rope, in particular a steel cable.
- the missile head comprises a connecting means over which one of the two parts of the nose tears after separation from the rear part at least part of the rear part to the outside.
- a separation of the rear part of the hull can be effected or at least facilitated.
- the dynamic pressure and the connecting means cooperate in a separation of the rear part of the fuselage, for example by pulling the rear part together laterally away from the fuselage.
- the connecting means pulls a front portion of the rear part more away from the center axis of the missile than a rear portion.
- the outward direction here is a direction away from a central axis of the missile, in particular perpendicularly away from the central axis.
- the connecting means does not have to transfer the energy in one shot, but a time span is available for this purpose.
- the connecting means is expediently made elastic. The elasticity can be achieved when the connecting means in its taut condition is made to elongate at least 3 mm, in particular 5 mm, until tearing.
- connection means has an extension means for materially extending the connection means by at least 3 mm beyond a tight connection. This also allows a period for transferring separation energy to be achieved.
- a material extension can be understood here that material is added to extend the connecting means between its two attachment points, for example, more rope.
- the material extension can be achieved by a rope loop with a braking device that For example, when removing from the front to the rear part and tightening of the connecting means engages.
- the invention is also directed to a method of separating a hood from a missile body during a flight of the missile, wherein a forward nose of the hood is removed from a rearward portion of the hood.
- the removal of the hood by the flying wind can create a dynamic pressure which releases two parts of the rear part from the fuselage.
- the nose according to the invention comprises two parts which are pushed apart by a separator and thereby detach from the rear part and then the rear part of the trunk dissolves. A complete separation of the nose from the rear part can be achieved with relatively little effort.
- the rear part is split longitudinally, so that dynamic pressure can press the two rear parts apart laterally and thereby detach from the fuselage.
- a chain reaction of the separation of the hood from the fuselage of the missile can be achieved.
- the two parts of the nose are pressed apart and then the rear part, in particular the two parts of the rear part is pressed apart.
- the hood can be reliably separated from the hull with a small force and the shape of the rear parts, which are particularly larger than the two parts of the nose, can be kept so that they are not driven back on a cushion of air to the missile and damage these, especially its wings.
- each of the parts of the nose pulls a part of the rear part laterally away from a missile axis.
- Fig. 1 shows a schematic representation of a missile 2 with a wing 6-bearing fuselage 4 and a hood 8, which forms the tip of the missile 2.
- the hood 8 consists of a front nose 10 and a rear part 12 and protects a fully arranged under the hood 8 Dom 14. A discharge of the hood 8 is controlled by a control unit 16.
- the head of the missile 2 is in Fig. 2 shown in a perspective view.
- the hood 8 is attached to the fuselage 4 of the missile 2 by fastening means 18, for example screws.
- the hood 8 is four in each case a portion of the outer surface 20 of the missile 2 forming parts 22, 24, 26, 28 formed in Fig. 5 are shown separated from each other.
- the two front parts 22, 24 of the hood 8 form the nose 10 of the hood 8, and the two rear parts 26, 28 form the rear part 12 of the hood. 8
- a separator 30 is visible, with which the front parts 22, 24 of the nose 10 are pressed apart during the flight of the missile 2, and the four parts fourteenth - 20 holds the hood 8 in front of it.
- the separating device 30 comprises two nested tubes 32, 34 and an inserted into the inner tube 32 pyrotechnic propellant 36. This is connected via cables directly or indirectly to the control unit 16 in the fuselage 4 of the missile 2, so that the pyrotechnic propellant 36 by means of a Control signal from the control unit 16 can be ignited.
- the two front parts 22, 24 of the nose 10 are held together tightly by the separator 30, for example by the two tubes 32, 34 frictionally engaged by a mutual interference fit connected to each other.
- the nose 10 encloses the front portion of the rear part 12, as seen from Fig. 3 can be seen, so that the two parts 26, 28 are also firmly held together by the firmly connected parts 22, 24 of the nose 10.
- the nose 10 and the rear part 12 positively connected to each other via a tongue and groove connection, so that a solution of the nose 10 from the rear part 12 without a separation of the nose 10 in the two spaced-apart parts 22, 24 as in Fig. 3 is impossible. Due to the tongue and groove connection also slipping of the nose 10 is prevented to the front and away from the rear part 12.
- a connecting means 44, 46 the parts 22, 24 of the nose 10 are each still connected to the part 26 or 28 lying behind them in the attached state, so that the two front parts 22, 24 are freely movable relative to the rear parts 26, 28, but only up to a fixed distance of the part 22 from the part 26 and the part 24 from the part 28.
- the two connecting means 44, 46 are each designed as a wire rope, the ends of each at one of the parts 22, 24 and 26, 28 are attached. If the two front parts 22, 24 have reached the distance from the rear parts 26, 28 predetermined by the connecting means 44, 46, then the connecting means 44, 46 are tightened and those by the pyrotechnic propellant.
- the separation energy of the separating device 30 is in this case dimensioned so that only the two front parts 22, 24 and then the two rear parts 26, 28 are separated even at a dormant or slow-flying missile 2 of the trunk 4, for example by das.Befest Trentsstoff 18th break with a predetermined breaking point, for example in a fastening screw.
- the two connecting means 44, 46 are each carried out somewhat elastically, so that the separation energy to be transmitted does not have to be transmitted in a moment of tightening of the connecting means 44, 46, but a period of time is available, during which the connecting means 44, 46 mm by about 5mm before breaking.
- the separation energy of the separator 30 and the strength of the connecting means 44, 46 are such that the connecting means 44, 46 rupture after transfer of separation energy to the rear portions 26, 28, so that the portion 22 is completely detached from the portion 26 and the portion 24 separated from part 28.
- the effect of the elastic elongation can be enhanced or replaced by a material extension of the connecting means 44, 46. This is achieved by an unillustrated loop in both wire ropes, which is pulled over a braking means when the ropes are taut and the parts 22, 24, 26, 28 further apart.
- an opening 48 is formed in the rear part 12, which is directed forward.
- the flying wind presses and causes a back pressure in the interior of the rear part 12, which pushes the two parts 26, 28 apart.
- the dynamic pressure is sufficient to release the parts 26, 28 from the fuselage 4.
- the separation is still supported by the parts 22, 24 via the connecting means 44, 46. If the missile 2 still flies slowly when the separating device 30 is triggered, the separating energy of the separating device 30 is sufficient to release the rear parts 26, 28 from the fuselage 4 as well.
- the two part 22, 24 of the nose 10 are asymmetrical to each other.
- the tip 50 and the full area of the outer surface 20 of the missile 2 and the hood 8 is formed to 5 cm behind the top 50 only by the part 24.
- the foremost part of the part 22 thus only reaches 5 cm to the top 50 zoom.
- a staggering flight behavior of the two parts 22, 24 is achieved, which prevents them from being guided again by the flying wind to the missile 2 and damaging it.
- the two parts 26, 28 are symmetrical to each other, but also behave staggering by the missing tip in the air flow, so that they are not performed again to the missile 2 and damage it.
- the two part 22, 24 of the nose 10 are connected to each other via a parting line 52 or separated or adjacent to each other. It provides the longitudinal separation of the two parts 22, 24, with its two ends (only the end 54 is in Fig. 2 shown) open to each other lying exactly opposite in a further parting line 56 which separates the nose 10 from the rear part 12 and which forms the tongue and groove connection.
- the two rear parts 26, 28 are via two joints (of which only one parting line 58 in Fig. 2 is shown), wherein each of the parting lines 58 open at the same location in the parting line 56, as the parting line 52. In the in Fig. 1 this embodiment is not the case.
- the parting lines 58 open between the rear parts 26, 28 offset from the parting line 52 in the parting line 56. This creates a stable composite of the four parts 22, 24, 26, 28th
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- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
Description
Die Erfindung betrifft einen Flugkörperkopf mit einer seine Spitze bildenden Haube, die in ihrer Gesamtheit während eines Flugs vom Rumpf ablösbar ist, und die einen mit dem Rumpf verbundenen hinteren Teil und eine vom hinteren Teil abtrennbare vordere, die Spitze bildende Nase umfasst, und mit einer Trenneinrichtung zum Trennen des hinteren Teils vom Rumpf und der Nase vom hinteren Teil während des Flugs.The invention relates to a missile head with a hood forming its tip, which in its entirety is detachable from the fuselage during a flight and which comprises a rear part connected to the fuselage and a front tip which can be separated from the rear part, and with a Separator for separating the rear part of the fuselage and the nose from the rear part during the flight.
Lenkflugkörper weisen in ihrem vorderen Bereich einen Suchkopf mit einem Zielverfolgungssystem auf, mit dem sie mit Hilfe optischer Mittel ein Ziel verfolgen können. Innere Teile des Suchkopfs sind in der Regel durch ein nach außen gewölbtes Fenster, den Dom, geschützt, durch das Strahlung von einem Ziel auf die Optik des Suchkopfs gelangen kann. Beim Start und während des Flugs des Flugkörpers ist der Dom mechanischen und thermischen Belastungen ausgesetzt. Zum Schutz des Doms vor äußeren Einflüssen, wie Teilchenschlag oder Hitze, ist dieser vor, während und gegebenenfalls noch in einer frühen Flugphase nach dem Start, in der das Zielverfolgungssystem nicht aktiv ist, ist der Dom mit einer die Spitze des Lenkflugkörpers bildenden Haube abgedeckt.Guided missiles have in their front area a seeker head with a tracking system, with which they can follow a target by means of optical means. Inner parts of the seeker head are typically protected by an outwardly arched window, the dome, through which radiation from a target can reach the optics of the seeker head. At the start and during the flight of the missile, the dome is exposed to mechanical and thermal stresses. To protect the dome from external influences, such as particle impact or heat, it is covered before, during and possibly even in an early flight phase after take-off in which the tracking system is not active, the dome is covered by a dome forming the tip of the missile.
Eine solche Haube behindert in aller Regel die Sicht des empfindlichen Zielverfolgungssystems und kann daher nur in einer bestimmten Flugphase eingesetzt werden, in der der Lenkflugkörper nicht durch das Zielverfolgungssystem zum Ziel geführt wird. Bevor der Flugkörper durch das Zielverfolgungssystem zum Ziel geführt werden soll, muss die Haube abgeworfen werden, damit eine ungehinderte Zielerfassung möglich ist.Such a hood usually obstructs the view of the sensitive tracking system and thus can only be used in a particular flight phase in which the missile is not guided through the target tracking system to the destination. Before the missile is to be guided through the target tracking system to the target, the hood must be dropped, so that an unimpeded target detection is possible.
Eine solche abwerfbare Haube ist beispielsweise aus der
Es ist eine Aufgabe der vorliegenden Erfindung, einen Flugkörperkopf mit einer seine Spitze bildenden Haube anzugeben, bei dem die Haube mit einfachen Mitteln und zuverlässig vom Rumpf getrennt werden kann.It is an object of the present invention to provide a missile head with a hood forming its tip, in which the hood can be easily and reliably separated from the hull.
Diese Aufgabe wird durch einen Flugkörperkopf der eingangs genannten Art gelöst, bei dem die Nase erfindungsgemäß in zumindest zwei Teile aufgeteilt ist und die Trenneinrichtung zum Auftrennen der Nase in diese beiden Teile während des Flugs vorbereitet ist.This object is achieved by a missile head of the type mentioned, in which the nose is inventively divided into at least two parts and the separator is prepared for separating the nose in these two parts during the flight.
Die Erfindung geht hierbei von der Überlegung aus, dass ein Abtrennen der vorderen Nase nach vorne, also in Flugrichtung, eine hohe mechanische Kraft braucht, um die Nase zuverlässig vom hinteren Teil der Haube abzutrennen. Hierdurch muss die Trenneinrichtung kräftig und somit groß ausgeführt sein, sodass auch die Haube groß ausgeführt ist. Durch die Erfindung kann die Kraft zum Abtrennen der Nase geringer gehalten bleiben, sodass die Trenneinrichtung kleiner dimensioniert und die Haube somit klein bauend ausgeführt werden kann.The invention is based on the consideration that a separation of the front nose forward, ie in the direction of flight, a high mechanical force needs to reliably separate the nose from the rear of the hood. As a result, the separator must be strong and thus made large, so that the hood is made large. By the invention, the force can be kept smaller for separating the nose, so that the separator dimensioned smaller and the hood can thus be made small-building.
Der Flugkörperkopf kann Befestigungsmittel zum Befestigen der Haube an einem Rumpfteil des Flugkörpers und die Haube an sich umfassen, die zweckmäßigerweise einen Dom abdeckt, insbesondere vollständig abdeckt, der unter der Haube angeordnet ist und der nach dem Abwurf der Haube den vordersten Teil des Flugkörpers bildet. Der Flugkörperkopf kann ein Zielverfolgungssystem zum Steuern des Flugkörpers in ein. Ziel aufweisen. Die Haube bildet zweckmäßigerweise die Außenfläche des Flugkörperkopfs, zumindest in seinem vorderen Bereich. Sie umfasst zumindest die vordere Nase und. den hinteren Teil, wobei sowohl der hintere Teil als auch die Nase in weitere, jeweils eine Außenfläche des Flugkörpers bildende Teile unterteilt sein können. Die Nase ist hierbei in Flugrichtung zumindest überwiegend, zweckmäßigerweise vollständig vor dem hinteren Teil angeordnet, ggf. bis auf die Befestigungsmittel und einen Überlappbereich. Der Rumpf des Flugkörpers kann von allen übrigen Elementen des Flugkörpers gebildet werden.The missile head may include attachment means for attaching the hood to a body of the missile and the hood itself, which conveniently covers, in particular completely covers, a dome which is located under the hood and which forms the foremost part of the missile after the hood is dropped. The missile head may include a target tracking system for controlling the missile. Target have. The hood expediently forms the outer surface of the missile head, at least in its front region. It includes at least the front nose and. the rear part, wherein both the rear part and the nose can be divided into further, each forming an outer surface of the missile forming parts. The nose is in this case at least predominantly, expediently arranged completely in front of the rear part, possibly up to the Fastener and an overlap area. The fuselage of the missile can be formed by all other elements of the missile.
Die Abtrennbarkeit der Nase vom hinteren Teil und/oder des hinteren Teils vom Rumpf des Flugkörpers kann durch ein Befestigungsmittel realisiert werden, das zum Befestigen der Teile aneinander vorgesehen ist und zum Trennen der Teile voneinander durch einen vorbestimmten Prozess. Dieser vorbestimmte Prozess kann eine vorbestimmte Krafteinleitung in zumindest zwei Teile der Haube umfassen und eine Trennung der Teile voneinander an zumindest einer vorbestimmten Stelle des Befestigungsmittels, beispielsweise an einer Sollbruchstelle.The separability of the nose from the rear part and / or the rear part from the fuselage of the missile can be realized by a fastening means provided for fastening the parts together and for separating the parts from each other by a predetermined process. This predetermined process may include a predetermined force introduction into at least two parts of the hood and a separation of the parts from each other at at least one predetermined location of the fastening means, for example at a predetermined breaking point.
Die Trenneinrichtung kann ein Mittel umfassen zum Einleiten einer vorbestimmten Kraft in beispielsweise zwei Teile der Haube, um diese voneinander zu trennen. Das Trennen der Nase vom hinteren Teil und/oder des hinteren Teils vom Rumpf kann unmittelbar durch die Krafteinleitung oder mittelbar durch einen Folgeprozess, beispielsweise das Auftreten von Staudruck, erfolgen. Zweckmäßigerweise ist die Trenneinrichtung so ausgeführt, dass zuerst die Nase vom hinteren Teil abgetrennt wird und dann der hintere Teil vom Rumpf des Flugkörpers. Das Auftrennen der beiden Teile der Nase durch die Trenneinrichtung kann erfolgen, indem die Trenneinrichtung eine Kraft in jeden diese beiden Teile einleitet, beispielsweise durch eine pyrotechnische Ladung, durch die die beiden Teile auseinandergedrückt werden. Hierdurch kann eine vollständige oder teilweise Lösung dieser beiden Teile vom hinteren Teil erfolgen.The separator may include means for introducing a predetermined force into, for example, two parts of the hood to separate them. The separation of the nose from the rear part and / or the rear part of the fuselage can be done directly by the introduction of force or indirectly by a follow-up process, such as the occurrence of back pressure. Conveniently, the separating device is designed so that first the nose is separated from the rear part and then the rear part of the fuselage of the missile. The separation of the two parts of the nose by the separator can be done by the separator introduces a force in each of these two parts, for example, by a pyrotechnic charge, by which the two parts are pressed apart. This can be done a complete or partial solution of these two parts of the rear part.
Zweckmäßigerweise hat die Haube bei abgetrennter Nase eine nach vorne weisende Öffnung. Hierdurch kann sich Staudruck im hinteren Teil bilden, der die Abtrennung des hinteren Teils vom Rumpf vollzieht oder zumindest erleichtert. Die Trenneinrichtung ist zweckmäßigerweise zum Trennen der Nase vom hinteren Teil ausgebildet, wodurch im Flug eine Öffnung im hinteren Teil gebildet wird, die Staudruck im hinteren Teil bewirkt.Conveniently, the hood with separated nose has a forward facing opening. As a result, back pressure can form in the rear part, which carries out the separation of the rear part of the hull, or at least facilitated. The separating device is expediently designed for separating the nose from the rear part, whereby an opening in the rear part is formed in flight, which causes back pressure in the rear part.
Die Erfindung ist besonders vorteilhaft anwendbar bei einem Flugkörper mit Flügeln, die eine Spannweite des Flugkörpers bewirken, die zumindest doppelt so groß ist wie das Kaliber des Flugkörpers. Durch die Hilfe des Staudrucks beim Abtrennen von Haubenteilen vom Rumpf können diese auch bei hoher Fluggeschwindigkeit weit genug vom Rumpf weggedrückt werden, sodass sie die Flügel des weiterfliegenden Flugkörpers nicht berühren und diese nicht beschädigen. Bei langsamer Fluggeschwindigkeit stellt zweckmäßigerweise die Trenneinrichtung genügend Trennenergie zur Verfügung, um sowohl die beiden Teile der Nase als auch den hinteren Teil weit genug von der Mittelachse des Flugkörpers zu entfernen.The invention is particularly advantageous applicable to a missile with wings that cause a span of the missile, which is at least twice as large as the caliber of the missile. With the help of the dynamic pressure when separating hood parts from the fuselage, they can be pushed far enough away from the fuselage even at high airspeed so that they do not touch the wings of the flying missile and do not damage them. At slower Airspeed conveniently provides the separator with sufficient separation energy to remove both the two portions of the nose and the rear portion far enough away from the central axis of the missile.
In einer vorteilhaften Ausführungsform der Erfindung sind die beiden Teile der Nase seitlich zur Flugrichtung voneinander abstoßbar, zweckmäßigerweise in entgegengesetzte Richtungen. Hierdurch können die beiden Teile mit relativ kleinem Kraftaufwand weit genug vom Flugkörper weg bewegt werden, ohne diesen im Weiterflug zu beschädigen. Die beiden Teile der Nase sind zweckmäßigerweise durch eine Längsteilung der Nase gebildet, wodurch ein Abstoßen seitlich zur Flugrichtung erleichtert wird. Die Längsrichtung ist hierbei parallel zur Flugrichtung des Flugkörpers.In an advantageous embodiment of the invention, the two parts of the nose are repulsible from each other laterally to the direction of flight, expediently in opposite directions. As a result, the two parts can be moved far enough away from the missile with relatively little effort, without damaging it in the onward flight. The two parts of the nose are expediently formed by a longitudinal division of the nose, whereby a repelling is facilitated laterally to the direction of flight. The longitudinal direction is parallel to the direction of flight of the missile.
Die beiden Teile der Nase können über eine Trennfuge unmittelbar zueinander benachbart sein, deren beide Enden in einer Trennfuge zwischen der Nase und dem hinteren Teil münden. Insbesondere liegen diese Mündungen einander genau gegenüber. Weiter vorteilhaft ist es, wenn die Nase und der hintere Teil beide über Trennfugen längsgeteilt sind, wobei die Trennfuge der Nase und der Trennfuge des hinteren Teils zueinander versetzt in einer Trennfuge zwischen Nase und hinteren Teil münden. Hierdurch kann die Nase den hinteren Teil einfach und stabil zusammenhalten.The two parts of the nose can be directly adjacent to each other via a parting line, the two ends open in a parting line between the nose and the rear part. In particular, these mouths are exactly opposite each other. It is also advantageous if the nose and the rear part are both longitudinally divided by joints, wherein the parting line of the nose and the parting line of the rear part offset from each other open in a parting line between the nose and rear part. This allows the nose to hold the back easily and stably.
Weiter vorteilhaft ist es, wenn die beiden Teile der Nase in ihrer Außenfläche asymmetrisch zueinander sind. Nach dem Auftrennen der Nase in diese beiden Teile kann ein Torkeln dieser Teile im Luftstrom erreicht werden, sodass ein Zurückfliegen in Richtung zum Flugkörper und damit eine Beschädigung des Flugkörpers durch eines der Teile unwahrscheinlich ist. Die Asymmetrie kann auf eine Mittelachse des Flugkörpers bezogen sein. Es kann z.B. die Außenfläche des einen Teils größer als die Außenfläche des anderen Teils sein. Ebenfalls denkbar ist eine asymmetrische Trennfuge zwischen den beiden vorderen Teilen.It is also advantageous if the two parts of the nose are asymmetrical in their outer surface. After the separation of the nose in these two parts, a staggering of these parts can be achieved in the air flow, so that a return to the direction of the missile and thus damage to the missile by one of the parts is unlikely. The asymmetry may be related to a central axis of the missile. It can e.g. the outer surface of one part may be larger than the outer surface of the other part. Also conceivable is an asymmetrical parting line between the two front parts.
Ein vorteilhaftes instabiles Flugverhalten der beiden vorderen Teile kann erreicht werden, wenn die Spitze der Nase bis zumindest 5 mm hinter den vordersten Punkt von nur einem der beiden Teile der Nase gebildet ist.An advantageous unstable flying behavior of the two front parts can be achieved if the tip of the nose is formed at least 5 mm behind the foremost point of only one of the two parts of the nose.
Eine weitere vorteilhafte Ausführungsform der Erfindung sieht vor, dass der Flugkörperkopf ein insbesondere ein flexibles Verbindungsmittel aufweist, über das eines der beiden Teile der Nase, noch während es sich nach einer Abtrennung vom hinteren Teil von diesem entfernt, mit dem hinteren Teil verbunden bleibt. Die durch das Trennmittel oder auf andere Weise in das sich entfernende vordere Teil eingebrachte Trennenergie kann über das Verbindungsmittel in den hinteren Teil eingebracht werden, sodass dieses durch die Trennenergie vom Rumpf getrennt wird oder die Trennenergie eine Trennung zumindest unterstützt. Die Flexibilität des Verbindungsmittels kann durch einen Biegbarkeit um zumindest 180° Grad realisiert werden, wobei das Verbindungsmittel zweckmäßigerweise ein Seil ist, insbesondere ein Stahlseil.A further advantageous embodiment of the invention provides that the missile head has in particular a flexible connecting means, via which one of the two parts of the nose, while still after a separation from rear part of this removed, remains connected to the rear part. The separating energy introduced by the separating means or otherwise into the removing front part may be introduced into the rear part via the connecting means, so that it is separated from the hull by the separating energy or the separating energy at least supports a separation. The flexibility of the connecting means can be realized by a bendability by at least 180 °, wherein the connecting means is expediently a rope, in particular a steel cable.
Weiter ist es vorteilhaft, wenn der Flugkörperkopf ein Verbindungsmittel umfasst, über das eines der beiden Teile der Nase nach einer Abtrennung vom hinteren Teil zumindest einen Teil des hinteren Teils nach außen reißt. Hierdurch kann eine Abtrennung des hinteren Teils vom Rumpf bewirkt oder zumindest erleichtert werden. Vorteilhafterweise wirken der Staudruck und das Verbindungsmittel gemeinsam an einer Abtrennung des hinteren Teils am Rumpf mit, beispielweise indem sie den hinteren Teil gemeinsam seitlich vom Rumpf wegziehen. Vorteilhafterweise zieht das Verbindungsmittel einen vorderen Bereich des hinteren Teils mehr von der Mittelachse des Flugkörpers weg als einen hinteren Bereich. Die Richtung nach außen ist hierbei eine Richtung von einer Mittelachse des Flugkörpers weg, insbesondere senkrecht von der Mittelachse weg.Further, it is advantageous if the missile head comprises a connecting means over which one of the two parts of the nose tears after separation from the rear part at least part of the rear part to the outside. As a result, a separation of the rear part of the hull can be effected or at least facilitated. Advantageously, the dynamic pressure and the connecting means cooperate in a separation of the rear part of the fuselage, for example by pulling the rear part together laterally away from the fuselage. Advantageously, the connecting means pulls a front portion of the rear part more away from the center axis of the missile than a rear portion. The outward direction here is a direction away from a central axis of the missile, in particular perpendicularly away from the central axis.
Um Trennenergie von der Nase auf den hinteren Teil möglichst weitgehend übertragen zu können ist es vorteilhaft, wenn das Verbindungsmittel die Energie nicht in einem Schlag übertragen muss, sondern eine Zeitspanne hierfür zur Verfügung steht. Hierzu ist das Verbindungsmittel zweckmäßigerweise elastisch ausgeführt. Die Elastizität kann erreicht werden, wenn das Verbindungsmittel in seinem straffen Zustand zu einer Längung von zumindest 3 mm, insbesondere 5 mm, bis zu einem Reißen ausgeführt ist.In order to be able to transfer separating energy from the nose to the rear part as far as possible, it is advantageous if the connecting means does not have to transfer the energy in one shot, but a time span is available for this purpose. For this purpose, the connecting means is expediently made elastic. The elasticity can be achieved when the connecting means in its taut condition is made to elongate at least 3 mm, in particular 5 mm, until tearing.
Weiter vorteilhaft ist es, wenn das Verbindungsmittel ein Verlängerungsmittel zum materiellen Verlängern des Verbindungsmittels um zumindest 3 mm über eine straffe Verbindung hinaus aufweist. Auch hierdurch kann ein Zeitraum zum Übertragen von Trennenergie erreicht werden. Als materielle Verlängerung kann hierbei verstanden werden, dass Material zum Verlängern des Verbindungsmittels zwischen seinen beiden Befestigungspunkten beigegeben wird, beispielsweise mehr Seil. Die materielle Verlängerung kann durch eine Seilschlaufe mit einem Bremsmittel erreicht werden, die sich beispielsweise bei einem Entfernen vom vorderen zum hinteren Teil und einem Straffen des Verbindungsmittels zuzieht.It is further advantageous if the connection means has an extension means for materially extending the connection means by at least 3 mm beyond a tight connection. This also allows a period for transferring separation energy to be achieved. As a material extension can be understood here that material is added to extend the connecting means between its two attachment points, for example, more rope. The material extension can be achieved by a rope loop with a braking device that For example, when removing from the front to the rear part and tightening of the connecting means engages.
Die Erfindung ist außerdem gerichtet auf ein Verfahren zum Trennen einer Haube von einem Rumpf eines Flugkörpers während eines Flugs des Flugkörpers, bei dem eine vordere Nase der Haube von einem hinteren Teil der Haube entfernt wird. Im hinteren Teil kann sich durch das Entfernen der Haube durch den Flugwind ein Staudruck bilden, der zwei Teile des hinteren Teils vom Rumpf löst.The invention is also directed to a method of separating a hood from a missile body during a flight of the missile, wherein a forward nose of the hood is removed from a rearward portion of the hood. In the rear part, the removal of the hood by the flying wind can create a dynamic pressure which releases two parts of the rear part from the fuselage.
Es wird vorgeschlagen, dass die Nase erfindungsgemäß zwei Teile umfasst, die durch eine Trenneinrichtung auseinandergedrückt werden und sich hierdurch vom hinteren Teil lösen und sich danach der hintere Teil vom Rumpf löst. Eine vollständige Trennung der Nase vom hinteren Teil kann mit relativ geringem Kraftaufwand erreicht werden.It is proposed that the nose according to the invention comprises two parts which are pushed apart by a separator and thereby detach from the rear part and then the rear part of the trunk dissolves. A complete separation of the nose from the rear part can be achieved with relatively little effort.
Vorteilhafterweise ist der hintere Teil längsgeteilt, sodass Staudruck die beiden hinteren Teile seitlich auseinander drücken und hierdurch vom Rumpf lösen kann. Durch das insbesondere seitliche Auseinanderdrücken der beiden Teile der Nase kann eine Kettenreaktion der Trennung der Haube vom Rumpf des Flugkörpers erreicht werden. Zuerst werden die beiden Teile der Nase auseinandergedrückt und danach wird der hintere Teil, insbesondere die beiden Teile des hinteren Teils auseinandergedrückt. Mit dieser Kettenreaktion kann die Haube mit einem geringen Kraftaufwand zuverlässig vom Rumpf getrennt werden und die Form der hinteren Teile, die insbesondere größer sind als die beiden Teile der Nase, kann so gehalten werden, dass diese nicht auf einem Luftpolster gleitend zum Flugkörper zurückgetrieben werden und diesen, insbesondere dessen Flügel, beschädigen.Advantageously, the rear part is split longitudinally, so that dynamic pressure can press the two rear parts apart laterally and thereby detach from the fuselage. By the particular lateral separation of the two parts of the nose, a chain reaction of the separation of the hood from the fuselage of the missile can be achieved. First, the two parts of the nose are pressed apart and then the rear part, in particular the two parts of the rear part is pressed apart. With this chain reaction, the hood can be reliably separated from the hull with a small force and the shape of the rear parts, which are particularly larger than the two parts of the nose, can be kept so that they are not driven back on a cushion of air to the missile and damage these, especially its wings.
In einer vorteilhaften Ausführungsform des Verfahrens zieht jedes der Teile der Nase einen Teil des hinteren Teils seitlich von einer Flugkörperachse weg. Hierdurch kann auch bei einem langsamen Flug, bei dem beispielsweise nicht genug Staudruck zum Abtrennen des hinteren Teils vom. Rumpf entsteht, dieser vom Rumpf getrennt werden.In an advantageous embodiment of the method, each of the parts of the nose pulls a part of the rear part laterally away from a missile axis. As a result, even with a slow flight, in which, for example, not enough back pressure for separating the rear part of. Hull is created, this will be separated from the hull.
Ausführungsbeispiele der Erfindung werden in einer Zeichnung näher erläutert. Dabei zeigen:
- Fig. 1
- Einen Flugkörper mit einer während des Flugs ablösbaren Haube,
- Fig. 2
- den Flugkörperkopf des Flugkörpers,
- Fig. 3
- ein Schnitt durch die Haube,
- Fig. 4
- die Haube nach einem Abtrennen der Nase vom hinteren Teil der Haube und
- Fig. 5
- die vom Rumpf des Flugkörpers vollständig abgetrennte Haube.
- Fig. 1
- A missile with a detachable during the flight hood,
- Fig. 2
- the missile head of the missile,
- Fig. 3
- a cut through the hood,
- Fig. 4
- the hood after separating the nose from the back of the hood and
- Fig. 5
- the hood completely detached from the fuselage of the missile.
Der Kopf des Flugkörpers 2 ist in
In der in
Vor dem Flug, während der Startphase und während eines ersten Teils des Flugs des Flugkörper 2 werden die beiden vorderen Teile 22, 24 der Nase 10 durch die Trenneinrichtung 30 fest zusammengehalten, beispielsweise durch die beiden Rohre 32, 34, die durch einen gegenseitigen Presssitz reibschlüssig miteinander verbunden sind. Die Nase 10 umschließt den vorderen Bereich des hinteren Teils 12, wie aus
Nach dem Start des Flugkörpers 2 und während des Flugs in Flugrichtung 40, die parallel zu einer Mittelachse 42 des Flugkörpers 2 ist, wird zu einem vorgegebenen Zeitpunkt oder bei einem vorgegebenen Zustand des Flugkörpers 2 oder eines Teils daraus ein Signal von der Steuereinheit 16 an die Trenneinrichtung 30 gegeben. Hierdurch zündet der pyrotechnische Treibsatz 36, der die beiden vorderen Teile 22, 24 der Nase 10 auseinander sprengt, wie in
Über jeweils ein Verbindungsmittel 44, 46 sind die Teile 22, 24 der Nase 10 jeweils noch mit dem im befestigten Zustand hinter ihnen liegenden Teil 26 bzw. 28 verbunden, sodass die beiden vorderen Teile 22, 24 zwar frei beweglich gegenüber den hinteren Teilen 26, 28 sind, jedoch nur bis zu einer festgelegten Entfernung des Teils 22 vom Teil 26 und des Teils 24 vom Teil 28. Die beiden Verbindungsmittel 44, 46 sind jeweils als Drahtseil ausgeführt, dessen Enden jeweils an einem der Teile 22, 24 bzw. 26, 28 befestigt sind. Haben die beiden vorderen Teile 22, 24 die durch das Verbindungsmittel 44 bzw. 46 vorgegebene Entfernung von den hinteren Teilen 26, 28 erreicht, so werden die Verbindungsmittel 44, 46 gestrafft und die durch den pyrotechnischen Treibsatz. 36 auf die beiden vorderen Teile 22, 24 übertragene Trennenergie wird teilweise auf die hinteren Teile 26, 28 übertragen, da diese durch die sich entfernenden Teile 22, 24 über die Verbindungsmittel 44, 46 vorne auseinandergerissen werden. Dieser Zustand ist in
Um eine zumindest weitgehende Übertragung der Trennenergie von dem vorderen Teil 22 auf das hintere Teil 26 und vom vorderen Teil 24 auf das hintere Teil 28 zu gewährleisten, sind die beiden Verbindungsmittel 44, 46 jeweils ein Stück weit elastisch ausgeführt, sodass die zu übertragende Trennenergie nicht in einem Moment des Straffwerdens der Verbindungsmittel 44, 46 übertragen werden muss, sondern eine Zeitspanne zur Verfügung steht, während der sich die Verbindungsmittel 44, 46 um etwa 5 mm jeweils längen bevor sie reißen. Die Trennenergie der Trenneinrichtung 30 und die Stärke der Verbindungsmittel 44, 46 sind so bemessen, dass die Verbindungsmittel 44, 46 nach einem Übertrag von Trennenergie auf die hinteren Teile 26, 28 zerreißen, sodass das Teil 22 vollständig vom Teil 26 und das Teil 24 vollständig vom Teil 28 getrennt ist. Der Effekt der elastischen Längung kann durch eine materielle Verlängerung der Verbindungsmittel 44, 46 verstärkt oder ersetzt werden. Diese wird durch eine nicht dargestellte Schlaufe in beiden Drahtseilen erreicht, die über ein Bremsmittel zugezogen wird wenn die Seile straff sind und sich die Teile 22, 24, 26, 28 weiter voneinander entfernen.To at least substantial transfer of the separation energy from the
Durch das Abtrennen der Nase 10 vom hinteren Teil 12, wie in
Die beiden Teil 22, 24 der Nase 10 sind asymmetrisch zueinander. Die Spitze 50 und der vollständige Bereich der Außenfläche 20 des Flugkörpers 2 bzw. der Haube 8 wird bis 5 cm hinter die Spitze 50 nur durch das Teil 24 gebildet. Der vorderste Teil des Teils 22 reicht also nur bis 5 cm zur Spitze 50 heran. Durch diese Asymmetrie wird ein torkelndes Flugverhalten der beiden Teile 22, 24 erreicht, das verhindert, dass sie durch den Flugwind wieder zu dem Flugkörper 2 hin geführt werden und diesen beschädigen. Die beiden Teile 26, 28 sind zwar symmetrisch zueinander ausgeführt, verhalten sich jedoch durch die fehlende Spitze ebenfalls torkelnd im Luftstrom, so dass auch sie nicht wieder zu dem Flugkörper 2 hin geführt werden und diesen beschädigen.The two
Die beiden Teil 22, 24 der Nase 10 sind über eine Trennfuge 52 miteinander verbunden bzw. voneinander getrennt oder zueinander benachbart. Sie schafft die Längstrennung der beiden Teile 22, 24, wobei ihre beiden Enden (nur das Ende 54 ist in
- 22
- Flugkörpermissile
- 44
- Rumpfhull
- 66
- Flügelwing
- 88th
- HaubeHood
- 1010
- Nasenose
- 1212
- hinterer Teilback part
- 1414
- Domcathedral
- 1616
- Steuereinheitcontrol unit
- 1818
- Befestigungsmittelfastener
- 2020
- Außenflächeouter surface
- 2222
- Teilpart
- 2424
- Teilpart
- 2626
- Teilpart
- 2828
- Teilpart
- 3030
- Trenneinrichtungseparator
- 3232
- Rohrpipe
- 3434
- Rohrpipe
- 3636
- Treibsatzpropellant
- 3838
- Steuereinheitcontrol unit
- 4040
- Flugrichtungflight direction
- 4242
- Mittelachsecentral axis
- 4444
- Verbindungsmittelconnecting means
- 4646
- Verbindungsmittelconnecting means
- 4848
- Öffnungopening
- 5050
- Spitzetop
- 5252
- Trennfugeparting line
- 5454
- EndeThe End
- 5656
- Trennfugeparting line
- 5858
- Trennfugeparting line
Claims (10)
dass die Nase (10) in zumindest zwei Teile (22, 24) aufgeteilt ist und die Trenneinrichtung (30) zum Auftrennen der Nase (10) in diese beiden Teile (22, 24) während des Flugs vorbereitet ist.A missile head having a hood (8) forming its tip (50) which is detachable in its entirety during flight from the fuselage (4) of the missile (2), and the rear part (12) and the fuselage (4) a nose (10) forming the tip (50) separable from the rear part (12), and having a separator (30) for separating the rear part (12) from the body and the nose (10) from the rear part (12 ) during the flight, characterized
in that the nose (10) is divided into at least two parts (22, 24) and the separating device (30) is prepared for separating the nose (10) into these two parts (22, 24) during the flight.
dadurch gekennzeichnet,
dass die beiden Teile (22, 24) der Nase (10) seitlich zur Flugrichtung (40) voneinander abstoßbar sind.Missile head according to claim 1,
characterized,
in that the two parts (22, 24) of the nose (10) can be repulsed from one another laterally relative to the direction of flight (40).
dadurch gekennzeichnet,
dass die beiden Teile (22, 24) der Nase (10) in ihrer Außenfläche (20) asymmetrisch zueinander sind.Missile head according to claim 1 or 2,
characterized,
in that the two parts (22, 24) of the nose (10) are asymmetrical in their outer surface (20).
dadurch gekennzeichnet,
dass die Spitze (50) der Nase (10) bis zumindest 5 mm hinter den vordersten Punkt von nur einem der beiden Teile (24) der Nase (10) gebildet ist.Missile head according to one of the preceding claims,
characterized,
in that the tip (50) of the nose (10) is formed at least 5 mm behind the foremost point of only one of the two parts (24) of the nose (10).
durch ein Verbindungsmittel (44, 46), über das eines der beiden Teile (22, 24) der Nase (10), noch während es sich nach einer Abtrennung vom hinteren Teil (12) von diesem entfernt, mit dem hinteren Teil (12) verbunden bleibt.Missile head according to one of the preceding claims, characterized
by a connecting means (44, 46), via which one of the two parts (22, 24) of the nose (10), while still being separated from the rear part (12), is connected to the rear part (12). remains connected.
durch ein Verbindungsmittel (44, 46), über das eines der beiden Teile (22, 24) der Nase (10) nach einer Abtrennung vom hinteren Teil (12) zumindest einen Teil (26, 28) des hinteren Teils (12) nach außen reißt.Missile head according to one of the preceding claims, characterized
by a connecting means (44, 46), via the one of the two parts (22, 24) of the nose (10) after a separation from the rear part (12) at least a portion (26, 28) of the rear part (12) to the outside tears.
dadurch gekennzeichnet,
dass das Verbindungsmittel (44, 46) in seinem straffen Zustand zu einer Längung von zumindest 3 mm bis zu einem Reißen ausgeführt ist.Missile head according to claim 5 or 6,
characterized,
that the connecting means (44, 46) in its taut condition is made to elongate at least 3 mm until torn.
dadurch gekennzeichnet,
dass das Verbindungsmittel (44, 46) ein Verlängerungsmittel zum materiellen Verlängern des Verbindungsmittels (44, 46) um zumindest 3 mm über eine straffe Verbindung hinaus aufweistMissile head according to one of claims 5 to 7,
characterized,
in that the connecting means (44, 46) has an extension means for materially extending the connection means (44, 46) by at least 3 mm beyond a tight connection
dadurch gekennzeichnet,
dass die Nase (10) zwei Teile (22, 24) umfasst, die durch eine Trenneinrichtung (30) auseinander gedrückt werden und sich hierdurch vom hinteren Teil (12) und sich danach der hintere Teil (12) vom Rumpf (4) löst.A method for separating a hood (8) from a hull (4) of a missile (2) during flight of the missile (2), wherein a front nose (10) of the hood (8) from a rear portion (12) of the hood (8) is removed,
characterized,
in that the nose (10) comprises two parts (22, 24) which are pushed apart by a separating device (30) and thereby separate from the rear part (12) and then the rear part (12) from the hull (4).
dadurch gekennzeichnet,
dass jedes der Teile (22, 24) der Nase (10) ein Teil (26, 28) des hinteren Teils (12) seitlich von einer Flugkörperachse (42) weg zieht.Method according to claim 9,
characterized,
in that each of the parts (22, 24) of the nose (10) pulls a part (26, 28) of the rear part (12) laterally away from a missile axis (42).
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102010007064A DE102010007064B4 (en) | 2010-02-06 | 2010-02-06 | Missile head and method of separating a hood from a missile body |
Publications (3)
Publication Number | Publication Date |
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EP2354756A2 true EP2354756A2 (en) | 2011-08-10 |
EP2354756A3 EP2354756A3 (en) | 2014-10-22 |
EP2354756B1 EP2354756B1 (en) | 2015-10-07 |
Family
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Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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EP11000642.6A Not-in-force EP2354756B1 (en) | 2010-02-06 | 2011-01-27 | Missile head and method for separating a cowling from the body of a missile |
Country Status (4)
Country | Link |
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US (1) | US8505455B2 (en) |
EP (1) | EP2354756B1 (en) |
DE (1) | DE102010007064B4 (en) |
IL (1) | IL210979A0 (en) |
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CN111174647A (en) * | 2020-03-13 | 2020-05-19 | 北京星际荣耀空间科技有限公司 | Split type rotary throwing separation method of rocket fairing |
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US8093487B2 (en) * | 2008-01-31 | 2012-01-10 | The Penn State Research Foundation | Removable protective nose cover |
DE102014011035A1 (en) | 2014-07-23 | 2016-01-28 | Diehl Bgt Defence Gmbh & Co. Kg | Hull hood for a missile |
US9857154B2 (en) * | 2014-07-30 | 2018-01-02 | The United States Of America As Represented By The Secretary Of The Army | Steerable munitions projectile |
US10254094B1 (en) * | 2015-11-16 | 2019-04-09 | Northrop Grumman Systems Corporation | Aircraft shroud system |
RU2649202C1 (en) * | 2017-01-17 | 2018-03-30 | Акционерное общество "Конструкторское бюро приборостроения им. академика А.Г. Шипунова" | Method of destroying the nose cone of the controlled artillery shell and mines (options) |
US10030952B1 (en) * | 2017-03-30 | 2018-07-24 | The United States Of America As Represented By The Secretary Of The Army | Thermally deployable shroud for affordable precision guided projectile |
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WO2020218569A1 (en) * | 2019-04-26 | 2020-10-29 | 川崎重工業株式会社 | Nose fairing |
US11274907B2 (en) * | 2020-04-28 | 2022-03-15 | Raytheon Company | Shroud driven deployable flight surfaces and method |
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DE10240040A1 (en) | 2002-08-27 | 2004-03-11 | BODENSEEWERK GERäTETECHNIK GMBH | Guided missile with detachable protective cap |
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DE3936403A1 (en) * | 1989-11-02 | 1991-05-08 | Messerschmitt Boelkow Blohm | PROTECTIVE HOOD FOR A MISSILE |
JP3223171B2 (en) * | 1998-12-24 | 2001-10-29 | 宇宙開発事業団 | Division structure and division method of rocket fairing |
US7082878B2 (en) * | 2003-07-01 | 2006-08-01 | Raytheon Company | Missile with multiple nosecones |
US7401752B2 (en) * | 2004-09-14 | 2008-07-22 | The Boeing Company | Protective shield assembly for space optics and associated methods |
DE102005030090B4 (en) * | 2005-06-27 | 2007-03-22 | Diehl Bgt Defence Gmbh & Co. Kg | Throw-off hood and missile with detachable hood |
IL189089A0 (en) * | 2008-01-28 | 2008-08-07 | Rafael Advanced Defense Sys | Apparatus and method for splitting and removing a shroud from an airborne vehicle |
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2010
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2011
- 2011-01-27 EP EP11000642.6A patent/EP2354756B1/en not_active Not-in-force
- 2011-01-31 IL IL210979A patent/IL210979A0/en not_active IP Right Cessation
- 2011-02-07 US US13/021,879 patent/US8505455B2/en not_active Expired - Fee Related
Patent Citations (1)
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DE10240040A1 (en) | 2002-08-27 | 2004-03-11 | BODENSEEWERK GERäTETECHNIK GMBH | Guided missile with detachable protective cap |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
RU2492413C1 (en) * | 2012-03-05 | 2013-09-10 | Открытое акционерное общество "Корпорация "Тактическое ракетное вооружение" | Drop head fairing of aircraft (versions) |
CN111174647A (en) * | 2020-03-13 | 2020-05-19 | 北京星际荣耀空间科技有限公司 | Split type rotary throwing separation method of rocket fairing |
CN111174647B (en) * | 2020-03-13 | 2021-04-27 | 北京星际荣耀空间科技股份有限公司 | Split type rotary throwing separation method of rocket fairing |
Also Published As
Publication number | Publication date |
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DE102010007064B4 (en) | 2012-03-29 |
EP2354756A3 (en) | 2014-10-22 |
DE102010007064A1 (en) | 2011-08-11 |
US8505455B2 (en) | 2013-08-13 |
EP2354756B1 (en) | 2015-10-07 |
IL210979A0 (en) | 2011-06-30 |
US20110192308A1 (en) | 2011-08-11 |
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