EP2216619A2 - Flight abort device for a missile - Google Patents
Flight abort device for a missile Download PDFInfo
- Publication number
- EP2216619A2 EP2216619A2 EP10001071A EP10001071A EP2216619A2 EP 2216619 A2 EP2216619 A2 EP 2216619A2 EP 10001071 A EP10001071 A EP 10001071A EP 10001071 A EP10001071 A EP 10001071A EP 2216619 A2 EP2216619 A2 EP 2216619A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- flight
- missile
- active element
- transmission
- control surfaces
- 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.)
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Images
Classifications
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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
- F42B10/60—Steering arrangements
- F42B10/62—Steering by movement of flight surfaces
- F42B10/64—Steering by movement of flight surfaces of fins
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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
- F42B10/48—Range-reducing, destabilising or braking arrangements, e.g. impact-braking arrangements; Fall-retarding means, e.g. balloons, rockets for braking or fall-retarding
Definitions
- the present invention relates to a flight abatement device for a missile with aerodynamic control surfaces for controlling the missile according to the preamble of claim 1. Furthermore, the invention relates to a method for stopping the flight of a FugMechs with aerodynamic control surfaces.
- this required flight abatement systems must completely or at least largely with regard to signal transmission, control and actuation can work independently. Only the power supply can be used in common, if buffering can be realized by switchable energy storage. In order to achieve a very low failure rate, it may be necessary to provide redundancy for a flight abort system. The same also applies to a telemetry system for condition monitoring of the flight cancellation system. If regular self-tests of all subsystems are required, it is also necessary to design the flight cancellation system reversibly.
- a pyrotechnic cutting cord can also parts of the missile, for example, rudder, wing or gear parts cut. Again, the same disadvantages apply, which have already been mentioned above in connection with the other pyrotechnic process.
- a transverse thrust or counter thrust can be generated which deflects the missile from its predetermined path.
- Such devices are currently mainly used in rescue capsules and landers in space technology application.
- a disadvantage of this concept is the requirement of an additional Fuel supply, which must be structurally implemented according to the environmental requirements, for example with regard to the storage of missiles, in the missile.
- an additional engine or the provision of an impulse charge increases the technical and design effort and the mass of the missile.
- the additional engine must be able to be turned off and re-ignited as desired to ensure reversibility for self-tests.
- Impulse charges must be provided in sufficient numbers on the missile to deflect the missile from its current trajectory in a preselected direction.
- Such a method for canceling a flight is feasible for cruise missiles with turbo jet engine or liquid engine, provided that the remaining distance to the target and the area of the security areas in which the missile can be deliberately crashed, are sufficiently large.
- This method is not suitable for missiles with solid propulsion engines, which however are used very frequently especially in military unmanned missiles. Also, this procedure of shutting down the engine is irreversible if the engine is not re-ignited.
- This method is also used in aircraft to shorten the braking distance when landing.
- it is only limitedly suitable for unmanned military missiles with non-disconnectable solid propulsion engine because the parachute brake generally does not withstand the high exhaust temperatures behind the missile.
- a considerable space requirement in the missile is required for the provision of a brake parachute or parachute and the mass of the shield and trigger system increases the total mass of the missile significantly.
- the complexity of a release system for parachute or brake parachute is due to the required high number of components in contradiction to the feasibility of a flight cancellation system with minimal risk of failure.
- this solution is irreversible and therefore no self-test accessible.
- Object of the present invention is therefore to provide a flight abatement device for a missile with aerodynamic control surfaces according to the preamble of claim 1, which works autonomously and reliably with minimized number of components and can be reliably used over several maintenance intervals of the missile.
- a method for canceling the flight of a missile which deflects the missile quickly and reliably from its planned trajectory.
- the object directed to the flight abatement device is achieved by the flight abort device having the features of patent claim 1.
- the control surfaces can be operated independently of the drive device in the event of a flight abort and are brought into a deflecting the missile from the previous trajectory position.
- the flight abatement device according to the invention can act on different control surfaces of the missile, for example on the wings, on rudders or on the front fuselage part of the missile intended duck wings (so-called canards).
- canards duck wings
- the active element of at least one transmission element of the transmission is formed, which is variable in at least one of its kinematic dimensions, said variability is preferably a length variability of serving as the active element gear member.
- the flight abatement device thus comprises a transmission element or a plurality of transmission elements, which are designed to be variably (for example variable in length) with regard to their kinematic dimensions.
- a transmission element or a plurality of transmission elements which are designed to be variably (for example variable in length) with regard to their kinematic dimensions.
- gear members designed as an active element they can be integrated in the transmission in parallel or in series.
- the triggering device has at least one energy store, preferably an elastic element, which is preferably formed by a spring.
- the energy store preferably an elastic element, which is preferably formed by a spring.
- a simple and reliable construction of the energy storage device is the provision of a prestressed and preferably frictionless spring.
- the triggering device has at least one releasable locking device for the elastic element.
- the locking device which locks the active element in the normal operating state of the missile, is unlocked upon activation of the flight abatement device, whereupon the elastic element suddenly relaxes and thereby the acting of the active element control surfaces in a predetermined position, preferably a defined stop position brings, so that the Missile is deflected abruptly and reliably from its previous attitude.
- a triggering device may have a plurality of independently operating locking devices.
- the triggering device is actuated by a control unit to move the active element from a standby position to a release position.
- This control unit which can also be present redundantly, can be activated, for example, by the on-board computer of the missile if the on-board computer itself can make a decision for a flight abort.
- the control unit can also be controlled via radio or telemetry from outside the missile independently of the on-board computer of the missile.
- a reset device which returns a triggered active element from the release position to the ready position.
- This reset device can be actuated by means of mechanical force applied externally or else be formed, for example, by a specially provided operating routine of the drive device for the control surfaces. By means of the reset device, it is possible to return an active element triggered, for example, after a self-test has been performed, back to the ready position.
- a particularly suitable embodiment of the flight demolition device according to the invention is characterized in that the active element is formed by a telescopically extendable handlebar.
- This handlebar may for example be tubular and receive the elastic element in its interior.
- the telescopically extendable handlebar is preferably biased by the elastic element in the direction of the extended position and is held by a locking device in the collapsed standby position, wherein the locking device is part of the triggering device.
- a plurality of independently operable locking devices can be provided.
- the individual components of the flight abatement device according to the invention can continue to be integrated into a telemetry system for the missile to increase the reliability so that the functionality of the individual components can be monitored telemetrically from the outside.
- a flight abort device according to the invention downstream of any existing locking system or unlocking system for the control surfaces, ie between the locking system and the unlocking system and the control surface is integrated.
- a completely self-sufficient functioning of the flight abatement device is achieved independently of a possibly made locking the acted upon by the action mechanism control surface and independent of the set by the drive means for the control surface state.
- At least one of the control surfaces is brought into a deflected position in order to deflect the missile from its intended trajectory.
- the control surfaces are brought abruptly in a deflected position.
- Fig. 1 shows a schematic representation of an inventive flight demolition device.
- a control surface 1 is mechanically connected via a transmission 2 with a drive device 3.
- the control surface 1 is pivotally mounted about an axis 10.
- a pivot lever 12 is further attached, which is fixedly connected at its one end to the control surface 1 and which is pivotally connected at its other, free end to a first end of a gear member 20 of the transmission 2 via a first joint 22.
- the rod-like gear member 20 is pivotally mounted at its second end with a second hinge 24 to a drive sleeve 30 of the drive means 3.
- the drive sleeve 30 is provided with a through hole having an internal thread which is in threaded engagement with an external thread of a drive spindle 32 of the drive device 3.
- the drive spindle 32 is connected to the drive shaft of a drive motor 34 of the drive device 3.
- the drive motor 34 actuates the drive spindle 32 in a desired direction of rotation about the axis 33 of the drive spindle 32.
- the angle of attack of the control surface 1 and thus the aerodynamic steering behavior of the control surface 1 can thus be influenced by selective actuation of the drive motor 34.
- the gear member 20 and thus the active element 4 is designed as a telescopically extendable handlebar 40, which is designed for the transmission of tensile and compressive forces.
- the handlebar 40 has a first, outer telescopic tube 42 and a second, inner telescopic tube 44.
- the inner telescopic tube 44 is axially displaceably mounted by means of an annular bearing 43 in the outer telescopic tube 42, as particularly well in Fig. 2 can be seen.
- an elastic element 5 formed by a coiled compression spring 50 is received as an energy store 5.
- the compression spring 50 is supported at its first end on the first joint 22 receiving the head end 21 of the gear member 20 from.
- the second end of the compression spring 50 is supported against a second end 24 receiving and connected to the outer telescopic tube 42 foot 23 of the gear member 20 from.
- the compression spring 50 is thus anxious to expand the telescopically extendable handlebar 40, the means push out the inner telescopic tube 44 from the outer telescopic tube 42.
- a releasable locking device 60 is provided, which is mounted in the region of the open end of the outer telescopic tube 42 on the outer telescopic tube 42 and part of a triggering device 6 for the active element 4.
- the locking device 60 has a radially displaceable slide as a locking device 64, the radially inner end in the in Fig. 1 shown ready position of the active element 4 with an annular latching projection 62 which is provided on the outer circumference of the inner telescopic tube in the vicinity of the head end 21.
- the annular detent projection 62 and the locking device 64 thus hold the telescopically extendable handlebar 40 in the ready position.
- a control unit 66 is provided to actuate the triggering device 6.
- Fig. 1 shows the flight abatement device according to the invention in the standby position
- Fig. 2 shows Fig. 2 the flight demolition device in the release position.
- the locking device 60 of the locking device 60 is moved from its locked with the annular locking projection 62 position on a command from the control unit 66 radially outward, as indicated by the arrow E in Fig. 2 is symbolized.
- the radially inner end of the locking device 64 gets out of engagement with the annular latching projection 62 and thus releases the inner telescopic tube 44.
- the inner telescopic tube 44 is abruptly moved from the outer telescopic tube 42 in the expansion position of the telescopically extendable handlebar 40.
- This sudden expansion of the handlebar 40 causes the control surface 1 also abruptly about its axis 10 in an extreme position ( Fig. 2 ) pivots, in which the pivot lever 12 comes against a missile-fixed stop 14 to the plant.
- This extreme deflection of the control surface 1 in turn causes that acting on the control surface 1 aerodynamic forces abruptly deflect the missile from the previous trajectory.
- the facing ends of the locking device 64 and the annular latching projection 62 are wedge-shaped, so that the locking device when the telescopically extendable handlebar 40 from the in Fig. 2 shown expansion position is compressed again over the annular locking projection 62 and then move back in Fig. 1 shown latched position can take.
- the drive means 3 the outer telescopic tube 42 under compression of the compression spring 50 so far move against the pivot lever 12 supported on the stop 14 inner telescopic tube 44 that this penetrates into the outer telescopic tube 42 to the locking of the locking device 64 with the locking projection 62 ,
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- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
Description
Die vorliegende Erfindung betrifft eine Flugabbruchvorrichtung für einen Flugkörper mit aerodynamischen Steuerflächen zur Steuerung des Flugkörpers gemäß dem Oberbegriff des Patentanspruchs 1. Weiterhin betrifft die Erfindung ein Verfahren zum Abbruch des Fluges eines Fugkörpers mit aerodynamischen Steuerflächen.The present invention relates to a flight abatement device for a missile with aerodynamic control surfaces for controlling the missile according to the preamble of claim 1. Furthermore, the invention relates to a method for stopping the flight of a Fugkörpers with aerodynamic control surfaces.
Insbesondere bei der Missionsplanung für den Einsatz von unbemannten Flugkörpern, beispielsweise Marschflugkörpern, mit selbsttätiger Zielaufschaltung und Zielverfolgung stellt sich die Frage nach der Möglichkeit eines Missionsabbruchs. Durch eine solche Maßnahme des Missionsabbruchs wären mögliche Kollateralschäden, wie sie beispielsweise nach fehlerhafter Zielaufschaltung auftreten, vermeidbar, da die Mission während des Fluges abgebrochen werden kann. Auch ein Ausfall oder ein Versagen von Komponenten oder Subsystemen des Flugkörpers kann nach dessen Start zu ähnlich sicherheitskritischen Situationen führen, die einer Abbruchmöglichkeit bedürfen.In particular, in the mission planning for the use of unmanned missiles, such as cruise missiles, with automatic target injection and target tracking raises the question of the possibility of a mission abort. Such a measure of the mission termination would avoid possible collateral damage, as occurs, for example, after incorrect targeting, since the mission can be aborted during the flight. Even a failure or failure of components or subsystems of the missile may lead after its launch to similar safety-critical situations that require a termination option.
Über die sehr hohen Anforderungen an die Zuverlässigkeit aller funktionswichtigen Flugkörpersubsysteme hinaus besteht ebenfalls die Notwendigkeit, durch einen externen Eingriff zu beliebigen Zeitpunkten während der Mission ein schnelles und sicheres Abweichen des Flugkörpers von der momentan vorgegebenen Flugbahn bis hin zu einem kontrollierten Absturz innerhalb eines definierten Gebietes, des sogenannten äußeren Sicherheitsbereichs, zu ermöglichen.In addition to the very high demands placed on the reliability of all mission-critical missile subsystems, there is also a need for a quick and safe deviation of the missile from the currently given trajectory to a controlled crash within a defined area by external intervention at any time during the mission. the so-called outer security area.
Dazu erforderliche Flugabbruchsysteme müssen gegenüber allen funktionswichtigen Systemen an Bord des Flugkörpers bezüglich Signalübertragung, Steuerung und Betätigung völlig oder zumindest weitgehend autark arbeiten können. Lediglich die Energieversorgung ist gemeinsam nutzbar, wenn eine Pufferung durch zuschaltbare Energiespeicher realisierbar ist. Um eine sehr geringe Ausfallrate zu erzielen, kann es erforderlich sein, Redundanz für ein Flugabbruchsystem vorzusehen. Gleiches gilt auch bezüglich eines Telemetriesystems zur Zustandsüberwachung des Flugabbruchsystems. Sind regelmäßige Selbsttests aller Subsysteme gefordert, so ist es zudem erforderlich, das Flugabbruchsystem reversibel auszugestalten.Compared with all functionally important systems on board the missile, this required flight abatement systems must completely or at least largely with regard to signal transmission, control and actuation can work independently. Only the power supply can be used in common, if buffering can be realized by switchable energy storage. In order to achieve a very low failure rate, it may be necessary to provide redundancy for a flight abort system. The same also applies to a telemetry system for condition monitoring of the flight cancellation system. If regular self-tests of all subsystems are required, it is also necessary to design the flight cancellation system reversibly.
Bisher bekannte und auch eingesetzte Lösungen zur Herbeiführung eines Flugabbruchs erfüllen die vorgenannten Anforderungen nicht oder nur zum Teil. Derzeit sind folgende Konzepte für den Flugabbruch eines unbemannten Flugkörpers bekannt:Previously known and also used solutions to bring about a flight crash meet the above requirements not or only partially. Currently, the following concepts for the flight abort of an unmanned missile are known:
Hier erfolgt durch einen extremen Ruder- oder Flügelausschlag eine gezielte Herbeiführung eines instabilen Flugzustands. Dabei wird vorausgesetzt, dass das Stellsystem für das Ruder beziehungsweise den Flügel intakt ist; bei Ausfall des Stellsystems versagt auch dieses Flugabbruchsystem. Zudem muss der Stellbereich der Kinematik des Stellsystems auf den extremen Ruderbeziehungsweise Flügelausschlag ausgelegt werden.Here, by an extreme rudder or wing rash a purposeful bringing about an unstable state of flight. It is assumed that the control system for the rudder or the wing is intact; failure of the control system also fails this flight cancellation system. In addition, the adjustment range of the kinematics of the control system must be designed for the extreme rudder relationship or sash.
Dieses Konzept des Abtrennens von Rudern oder Flügeln vom Flugkörper ist nur pyrotechnisch sinnvoll realisierbar. Pyrotechnische Aktoren und Auslöser besitzen jedoch nur eine begrenzte Lagerfähigkeit und eine je nach Umgebungsbedingungen eingeschränkte Zuverlässigkeit. Weiterhin ist dieses Konzept des Flugabbruchs nur bei Flugkörpern einsetzbar, die sich nach dem Abtrennvorgang instabil verhalten. Auch ist dieses Konzept nicht für einen Selbsttest geeignet, da das Abtrennen von Rudern oder Flügeln ein irreversibler Vorgang ist.This concept of separating the rudders or wings from the missile is only feasible pyrotechnically useful. However, pyrotechnic actuators and actuators have limited shelf life and limited reliability depending on environmental conditions. Furthermore, this concept of flight termination can only be used with missiles that behave unstably after the separation process. Also, this concept is not for one Self-test suitable because the separation of rudders or wings is an irreversible process.
Auch diese Flugabbruchvariante ist nur pyrotechnisch realisierbar, wodurch auch die Nachteile bezüglich der Lagerfähigkeit und Zuverlässigkeit pyrotechnischer Erzeugnisse für diese Variante zutreffen. Zudem ist auch diese Vorgehensweise irreversibel.This flight abort variant is only pyrotechnic feasible, which also applies to the disadvantages in terms of shelf life and reliability pyrotechnic products for this variant. Moreover, this procedure is irreversible.
Mittels einer pyrotechnischen Schneidschnur lassen sich ebenfalls Teile des Flugkörpers, beispielsweise Ruder, Flügel oder Getriebeteile durchtrennen. Auch hier gelten die gleichen Nachteile, die vorstehend bereits in Verbindung mit den anderen pyrotechnischen Verfahren genannt worden sind.By means of a pyrotechnic cutting cord can also parts of the missile, for example, rudder, wing or gear parts cut. Again, the same disadvantages apply, which have already been mentioned above in connection with the other pyrotechnic process.
Der Einsatz von automatisierten Kabetschneidern zum Durchtrennen von elektrischen Kabeln führt einen Systemausfall durch die Unterbrechung von Kabeln beziehungsweise Kabelbäumen innerhalb des Flugkörpers herbei. Auch diese Methode ist nur bei Flugkörpern einsetzbar, die sich nach dem Durchtrennen von Kabeln instabil verhalten. Auch diese Variante ist irreversibel.The use of automated wire cutters to sever electrical cables causes a system failure by breaking cables or wiring harnesses within the missile. This method is only applicable to missiles that behave unstable after cutting through cables. This variant is also irreversible.
Durch das Vorsehen eines zusätzlichen Triebwerks oder einer Impulsladung kann ein Querschub oder ein Gegenschub erzeugt werden, der den Flugkörper aus seiner vorbestimmten Bahn auslenkt. Derartige Vorrichtungen finden derzeit vorwiegend in Rettungskapseln und Landefähren in der Raumfahrttechnik Anwendung. Nachteilig bei diesem Konzept ist das Erfordernis eines zusätzlichen Treibstoffvorrats, der konstruktiv entsprechend den Umweltanforderungen, beispielsweise bezüglich der Lagerung von Flugkörpern, in den Flugkörper implementiert werden muss. Außerdem erhöht ein zusätzliches Triebwerk beziehungsweise das Vorsehen einer Impulsladung den technisch-konstruktiven Aufwand und die Masse des Flugkörpers. Das zusätzliche Triebwerk muss beliebig abschaltbar und wieder zündbar sein, um eine Reversibilität für Selbsttests zu gewährleisten. Impulsladungen müssen in einer ausreichenden Anzahl am Flugkörper vorgesehen werden, um den Flugkörper in einer vorwählbaren Richtung aus seiner momentanen Flugbahn auslenken zu können.By providing an additional engine or an impulse charge, a transverse thrust or counter thrust can be generated which deflects the missile from its predetermined path. Such devices are currently mainly used in rescue capsules and landers in space technology application. A disadvantage of this concept is the requirement of an additional Fuel supply, which must be structurally implemented according to the environmental requirements, for example with regard to the storage of missiles, in the missile. In addition, an additional engine or the provision of an impulse charge increases the technical and design effort and the mass of the missile. The additional engine must be able to be turned off and re-ignited as desired to ensure reversibility for self-tests. Impulse charges must be provided in sufficient numbers on the missile to deflect the missile from its current trajectory in a preselected direction.
Ein derartiges Verfahren zum Abbruch eines Fluges ist für Marschflugkörper mit Turboluftstrahltriebwerk oder Flüssigkeitstriebwerk realisierbar, sofern die verbleibende Entfernung bis zum Ziel und die Fläche der Sicherheitsbereiche, in denen der Flugkörper gezielt zum Absturz gebracht werden kann, ausreichend groß sind. Nicht geeignet ist dieses Verfahren für Flugkörper mit Feststofftriebwerken, die jedoch gerade bei militärischen unbemannten Flugkörpern sehr häufig zum Einsatz kommen. Auch ist diese Vorgehensweise des Abschaltens des Triebwerks irreversibel, falls das Triebwerk nicht wieder zündbar ist.Such a method for canceling a flight is feasible for cruise missiles with turbo jet engine or liquid engine, provided that the remaining distance to the target and the area of the security areas in which the missile can be deliberately crashed, are sufficiently large. This method is not suitable for missiles with solid propulsion engines, which however are used very frequently especially in military unmanned missiles. Also, this procedure of shutting down the engine is irreversible if the engine is not re-ignited.
Dieses Verfahren ist allgemein aus Verkehrsflugzeugen zur Verkürzung des Bremswegs bei der Landung bekannt. Der technische Aufwand zur Realisierung einer Schubumkehr ist jedoch aufgrund der erforderlichen Anzahl von Komponenten äußerst hoch und steht im Widerspruch zur geforderten Realisierbarkeit mit geringst möglichem Ausfallrisiko des Flugabbruchsystems.This method is generally known from commercial aircraft for shortening the stopping distance when landing. However, the technical effort to realize a thrust reverser is extremely high due to the required number of components and is in contradiction to the required feasibility with the lowest possible risk of failure of the flight abort system.
Auch dieses Verfahren wird bei Flugzeugen zur Verkürzung des Bremswegs bei der Landung eingesetzt. Es ist jedoch bei unbemannten militärischen Flugkörpern mit nicht abschaltbarem Feststofftriebwerk nur begrenzt geeignet, da der Bremsfallschirm im Allgemeinen nicht den hohen Abgastemperaturen hinter dem Flugkörper standhält. Des Weiteren ist für das Vorsehen eines Bremsfallschirms oder Fallschirms ein nicht unerheblicher Platzbedarf im Flugkörper erforderlich und die Masse von Schirm und Auslösesystem erhöht die Gesamtmasse des Flugkörpers deutlich. Auch die Komplexität eines Auslösesystems für Fallschirm oder Bremsfallschirm steht aufgrund der erforderlichen hohen Anzahl von Komponenten im Widerspruch zur Realisierbarkeit eines Flugabbruchsystems mit geringstem Ausfallrisiko. Zudem ist auch diese Lösung irreversibel und daher keinem Selbsttest zugänglich.This method is also used in aircraft to shorten the braking distance when landing. However, it is only limitedly suitable for unmanned military missiles with non-disconnectable solid propulsion engine because the parachute brake generally does not withstand the high exhaust temperatures behind the missile. Furthermore, a considerable space requirement in the missile is required for the provision of a brake parachute or parachute and the mass of the shield and trigger system increases the total mass of the missile significantly. The complexity of a release system for parachute or brake parachute is due to the required high number of components in contradiction to the feasibility of a flight cancellation system with minimal risk of failure. In addition, this solution is irreversible and therefore no self-test accessible.
Aufgabe der vorliegenden Erfindung ist es daher, eine Flugabbruchvorrichtung für einen Flugkörper mit aerodynamischen Steuerflächen gemäß dem Oberbegriff des Patentanspruchs 1 anzugeben, die bei minimierter Komponentenzahl autark und zuverlässig funktioniert und über mehrere Wartungsintervalle des Flugkörpers zuverlässig einsetzbar ist. Außerdem soll durch die Erfindung ein Verfahren zum Abbrechen des Fluges eines Flugkörpers angegeben werden, das den Flugkörper schnell und zuverlässig aus seiner geplanten Flugbahn ablenkt.Object of the present invention is therefore to provide a flight abatement device for a missile with aerodynamic control surfaces according to the preamble of claim 1, which works autonomously and reliably with minimized number of components and can be reliably used over several maintenance intervals of the missile. In addition to be specified by the invention, a method for canceling the flight of a missile, which deflects the missile quickly and reliably from its planned trajectory.
Die auf die Flugabbruchvorrichtung gerichtete Aufgabe wird gelöst durch die Flugabbruchvorrichtung mit den Merkmalen des Patentanspruchs 1.The object directed to the flight abatement device is achieved by the flight abort device having the features of patent claim 1.
Dazu ist bei einer Flugabbruchvorrichtung für einen Flugkörper mit aerodynamischen Steuerflächen zur Steuerung des Flugkörpers, wobei Steuerflächen von zumindest einer Antriebseinrichtung über zumindest ein Getriebe zur Verstellung antreibbar sind, zumindest ein von einer Auslösevorrichtung betätigbares Wirkelement vorgesehen, das in das Getriebe integriert ist.This is in a flight abatement device for a missile with aerodynamic control surfaces for controlling the missile, wherein control surfaces of at least one drive means via at least one transmission can be driven for adjustment, at least one of Tripping device operable active element provided, which is integrated in the transmission.
Unter dem Begriff "Getriebe" ist hier die gesamte kinematische Kette eines Antriebsstrangs von der Antriebseinrichtung bis zur betreffenden Steuerfläche zu verstehen.The term "gear" here is to be understood as the entire kinematic chain of a drive train from the drive device to the relevant control surface.
Durch das Vorsehen des in das Getriebe integrierten und von einer Auslösevorrichtung betätigbaren Wirkelements können die Steuerflächen unabhängig von der Antriebseinrichtung im Falle eines Flugabbruchs betätigt werden und so in eine den Flugkörper aus der bisherigen Flugbahn auslenkende Stellung gebracht werden. Die erfindungsgemäße Flugabbruchvorrichtung kann auf unterschiedliche Steuerflächen des Flugkörpers wirken, beispielsweise auf die Flügel, auf Ruder oder auf am vorderen Rumpfteil des Flugkörpers vorgesehene Entenflügel (sogenannte Canards). Zur Erzielung einer Redundanz können sowohl mehrere unabhängig voneinander arbeitende Auslösevorrichtungen für ein Wirkelement, als auch mehrere unabhängig voneinander arbeitende Wirkelemente für eine Steuerfläche vorgesehen sein.By providing the integrated into the transmission and operable by a triggering active element, the control surfaces can be operated independently of the drive device in the event of a flight abort and are brought into a deflecting the missile from the previous trajectory position. The flight abatement device according to the invention can act on different control surfaces of the missile, for example on the wings, on rudders or on the front fuselage part of the missile intended duck wings (so-called canards). To achieve redundancy, it is possible to provide a plurality of independently triggering devices for one active element as well as a plurality of independently operating active elements for a control surface.
Vorzugsweise ist das Wirkelement von zumindest einem Getriebeglied des Getriebes gebildet, das in zumindest einer seiner kinematischen Abmessungen veränderbar ist, wobei diese Veränderbarkeit bevorzugt eine Längenveränderbarkeit des als Wirkelement dienenden Getriebeglieds ist.Preferably, the active element of at least one transmission element of the transmission is formed, which is variable in at least one of its kinematic dimensions, said variability is preferably a length variability of serving as the active element gear member.
Die Flugabbruchvorrichtung umfasst somit ein Getriebeglied oder mehrere Getriebeglieder, das beziehungsweise die bezüglich ihrer kinematischen Abmessungen variabel (zum Beispiel längenveränderlich) ausgeführt sind. Beim Vorsehen von mehreren als Wirkelement ausgebildeten Getriebegliedern können diese parallel oder seriell in das Getriebe integriert sein.The flight abatement device thus comprises a transmission element or a plurality of transmission elements, which are designed to be variably (for example variable in length) with regard to their kinematic dimensions. When providing a plurality of gear members designed as an active element, they can be integrated in the transmission in parallel or in series.
In einer bevorzugten Ausgestaltungsform der vorliegenden Erfindung weist die Auslösevorrichtung zumindest einen Energiespeicher, vorzugsweise ein elastisches Element auf, welches bevorzugt von einer Feder gebildet ist. Aus Gründen der Redundanz können mehrere unabhängig voneinander betätigbare Energiespeicher in einer Auslösevorrichtung vorgesehen sein. Eine einfache und zuverlässige Konstruktion des Energiespeichers ist das Vorsehen einer vorgespannten und vorzugsweise reibungslosen Feder.In a preferred embodiment of the present invention, the triggering device has at least one energy store, preferably an elastic element, which is preferably formed by a spring. For reasons of redundancy, a plurality of independently operable energy stores can be provided in a triggering device. A simple and reliable construction of the energy storage device is the provision of a prestressed and preferably frictionless spring.
Grundsätzlich können zur Erzielung einer größtmöglichen Redundanz gemeinsam auch unterschiedliche Energiespeicher und unterschiedlich konstruierte Auslösevorrichtungen vorgesehen sein, die unabhängig voneinander funktionsfähig sind. Wesentlich ist dabei, dass nach Betätigen der Auslösevorrichtung das Wirkelement dafür sorgt, dass die von ihm beaufschlagten Steuerflächen in eine für einen Flugabbruch geeignete Position ausgelenkt werden, unabhängig von der Position der Steuerflächen, die für den bisherigen Flug von der Antriebseinrichtung der Steuerflächen eingestellt worden war. Die Wirkung der Antriebseinrichtung der Steuerflächen auf die Steuerflächen wird somit von der Wirkung des Wirkelements auf die Steuerflächen dominant überlagert.Basically, to achieve the greatest possible redundancy, different energy stores and differently designed triggering devices can be provided together, which are independently functional. It is essential that after actuation of the triggering device, the active element ensures that the control surfaces acted upon by it are deflected into a suitable position for a flight termination, regardless of the position of the control surfaces, which had been set for the previous flight of the drive means of the control surfaces , The effect of the drive means of the control surfaces on the control surfaces is thus dominated by the effect of the active element on the control surfaces dominant.
Weiter bevorzugt ist es, wenn die Auslösevorrichtung zumindest eine lösbare Verriegelungsvorrichtung für das elastische Element aufweist.It is further preferred if the triggering device has at least one releasable locking device for the elastic element.
Die Verriegelungsvorrichtung, die im normalen Betriebszustand des Flugkörpers das Wirkelement arretiert, wird bei einer Aktivierung der Flugabbruchvorrichtung entriegelt, worauf sich das elastische Element schlagartig entspannt und dadurch die vom Wirkelement beaufschlagten Steuerflächen in eine vorbestimmte Position, vorzugsweise eine definierte Anschlagposition, bringt, so dass der Flugkörper aus seiner bisherigen Fluglage abrupt und zuverlässig ausgelenkt wird. Zur Erzielung einer Redundanz kann eine Auslösevorrichtung mehrere voneinander unabhängig arbeitende Verriegelungsvorrichtungen aufweisen.The locking device, which locks the active element in the normal operating state of the missile, is unlocked upon activation of the flight abatement device, whereupon the elastic element suddenly relaxes and thereby the acting of the active element control surfaces in a predetermined position, preferably a defined stop position brings, so that the Missile is deflected abruptly and reliably from its previous attitude. To achieve redundancy, a triggering device may have a plurality of independently operating locking devices.
Vorzugsweise ist die Auslösevorrichtung von einer Steuereinheit betätigbar, um das Wirkelement aus einer Bereitschaftsstellung in eine Auslösestellung zu bewegen. Diese Steuereinheit, die auch redundant vorhanden sein kann, kann beispielsweise vom Bordrechner des Flugkörpers angesteuert werden, wenn der Bordrechner selbst eine Entscheidung für einen Flugabbruch treffen kann. Die Steuereinheit kann aber auch über Funk oder Telemetrie von außerhalb des Flugkörpers unabhängig vom Bordrechner des Flugkörpers ansteuerbar sein.Preferably, the triggering device is actuated by a control unit to move the active element from a standby position to a release position. This control unit, which can also be present redundantly, can be activated, for example, by the on-board computer of the missile if the on-board computer itself can make a decision for a flight abort. The control unit can also be controlled via radio or telemetry from outside the missile independently of the on-board computer of the missile.
In einer besonderen bevorzugten Ausführungsform ist eine Rücksetzeinrichtung vorgesehen, die ein ausgelöstes Wirkelement aus der Auslösestellung in die Bereitschaftsstellung zurückführt.In a particular preferred embodiment, a reset device is provided which returns a triggered active element from the release position to the ready position.
Diese Rücksetzeinrichtung kann mittels mechanisch von außen aufgebrachter Kraft betätigt werden oder auch beispielsweise durch eine dafür speziell vorgesehene Betätigungsroutine der Antriebseinrichtung für die Steuerflächen gebildet sein. Mittels der Rücksetzeinrichtung ist es möglich, ein beispielsweise nach einem durchgeführten Selbsttest ausgelöstes Wirkelement wieder in die Bereitschaftsstellung zurückzuführen.This reset device can be actuated by means of mechanical force applied externally or else be formed, for example, by a specially provided operating routine of the drive device for the control surfaces. By means of the reset device, it is possible to return an active element triggered, for example, after a self-test has been performed, back to the ready position.
Eine besonders geeignete Ausführungsform der erfindungsgemäßen Flugabbruchvorrichtung zeichnet sich dadurch aus, dass das Wirkelement von einer teleskopartig ausfahrbaren Lenkerstange gebildet ist. Diese Lenkerstange kann beispielsweise rohrförmig ausgebildet sein und in ihrem Inneren das elastische Element aufnehmen.A particularly suitable embodiment of the flight demolition device according to the invention is characterized in that the active element is formed by a telescopically extendable handlebar. This handlebar may for example be tubular and receive the elastic element in its interior.
Dabei ist die teleskopartig ausfahrbare Lenkerstange vorzugsweise vom elastischen Element in Richtung der ausgefahrenen Position vorgespannt und wird von einer Arretiereinrichtung in der zusammengeschobenen Bereitschaftsstellung gehalten, wobei die Arretiereinrichtung Bestandteil der Auslösevorrichtung ist. Aus Gründen der Redundanz können auch mehrere unabhängig voneinander betätigbare Arretiereinrichtungen vorgesehen sein.In this case, the telescopically extendable handlebar is preferably biased by the elastic element in the direction of the extended position and is held by a locking device in the collapsed standby position, wherein the locking device is part of the triggering device. For reasons of redundancy, a plurality of independently operable locking devices can be provided.
Die einzelnen Komponenten der erfindungsgemäßen Flugabbruchvorrichtung können zur Erhöhung der Zuverlässigkeit weiterhin in ein Telemetriesystem für den Flugkörper derart integriert werden, dass die Funktionsfähigkeit der einzelnen Komponenten telemetrisch von außen überwacht werden kann.The individual components of the flight abatement device according to the invention can continue to be integrated into a telemetry system for the missile to increase the reliability so that the functionality of the individual components can be monitored telemetrically from the outside.
Vorteilhaft ist es auch, wenn eine erfindungsgemäße Flugabbruchvorrichtung einem eventuell vorhandenen Verriegelungssystem beziehungsweise Entriegelungssystem für die Steuerflächen nachgeschaltet, also zwischen das Verriegelungssystem beziehungsweise das Entriegelungssystem und die Steuerfläche integriert ist. Dadurch wird eine völlig autarke Funktionsfähigkeit der Flugabbruchvorrichtung unabhängig von einer eventuell vorgenommenen Verriegelung der vom Wirkmechanismus beaufschlagten Steuerfläche und unabhängig von dem von der Antriebseinrichtung für die Steuerfläche eingestellten Zustand erzielt.It is also advantageous if a flight abort device according to the invention downstream of any existing locking system or unlocking system for the control surfaces, ie between the locking system and the unlocking system and the control surface is integrated. As a result, a completely self-sufficient functioning of the flight abatement device is achieved independently of a possibly made locking the acted upon by the action mechanism control surface and independent of the set by the drive means for the control surface state.
Die auf das Verfahren gerichtete Aufgabe wird gelöst durch ein Verfahren mit den Merkmalen des Patentanspruchs 11.The object directed to the method is achieved by a method having the features of patent claim 11.
Bei einem erfindungsgemäßen Verfahren zum Abbrechen des Flugs eines Flugkörpers mit aerodynamischen Steuerflächen wird zumindest eine der Steuerflächen in eine ausgelenkte Stellung gebracht, um den Flugkörper aus seiner vorgesehenen Flugbahn auszulenken. Vorzugsweise werden die Steuerflächen dabei schlagartig in eine ausgelenkte Stellung gebracht.In a method according to the invention for stopping the flight of a missile with aerodynamic control surfaces, at least one of the control surfaces is brought into a deflected position in order to deflect the missile from its intended trajectory. Preferably, the control surfaces are brought abruptly in a deflected position.
Bevorzugte Ausführungsbeispiele der Erfindung mit zusätzlichen Ausgestaltungsdetails und weiteren Vorteilen sind nachfolgend unter Bezugnahme auf die beigefügten Zeichnungen näher beschrieben und erläutert.Preferred embodiments of the invention with additional design details and other advantages are described and explained in more detail below with reference to the accompanying drawings.
Es zeigt:
- Fig. 1
- eine schematische Darstellung einer erfindungsgemäßen Flugabbruchvorrichtung in der Bereitschaftsstellung und
- Fig. 2
- die Flugabbruchvorrichtung aus
Fig. 1 in ihrer ausgelösten Stellung.
- Fig. 1
- a schematic representation of a flight abatement device according to the invention in the ready position and
- Fig. 2
- the flight crash device out
Fig. 1 in their triggered position.
Das stangenartige Getriebeglied 20 ist an seinem zweiten Ende mit einem zweiten Gelenk 24 an einer Antriebsmuffe 30 der Antriebseinrichtung 3 schwenkbar gelagert.The rod-like gear member 20 is pivotally mounted at its second end with a
Die Antriebsmuffe 30 ist mit einer Durchgangsbohrung versehen, die ein Innengewinde aufweist, welches mit einem Außengewinde einer Antriebsspindel 32 der Antriebseinrichtung 3 in Gewindeeingriff steht. Die Antriebsspindel 32 ist mit der Antriebswelle eines Antriebsmotors 34 der Antriebseinrichtung 3 verbunden.The
Im normalen Flugbetrieb betätigt der Antriebsmotor 34 die Antriebsspindel 32 in einer gewünschten Drehrichtung um die Achse 33 der Antriebsspindel 32. Je nach Drehrichtung der Antriebsspindel 32 wandert die Antriebsmuffe 30 und mit ihr das Getriebeglied 20 entlang der Achse 33 in Richtung zum Antriebsmotor 34 hin oder von diesem weg, wie durch den Doppelpfeil W in
Diese Axialbewegung der Antriebsmuffe 30 führt aufgrund der gelenkigen Kopplung des Getriebeglieds 20 mit der Antriebsmuffe 30 einerseits und dem Schwenkhebel 12 andererseits zu einer Schwenkbewegung der Steuerfläche 1 um die Achse 10. Diese Schwenkbewegung der Steuerfläche 1 ist durch die vier an der Steuerfläche 1 angreifenden Pfeile in
Der Anstellwinkel der Steuerfläche 1 und damit das aerodynamische Lenkverhalten der Steuerfläche 1 kann somit durch wahlweises Betätigen des Antriebsmotors 34 beeinflusst werden.The angle of attack of the control surface 1 and thus the aerodynamic steering behavior of the control surface 1 can thus be influenced by selective actuation of the
Nachstehend wird der Aufbau des Getriebeglieds 20, das ein Wirkelement 4 der erfindungsgemäßen Flugabbruchvorrichtung bildet, beschrieben.Hereinafter, the structure of the gear member 20, which forms an active element 4 of the flight demolition device according to the invention, will be described.
Das Getriebeglied 20 und damit das Wirkelement 4 ist als teleskopartig ausfahrbare Lenkerstange 40 ausgestaltet, die zur Übertragung von Zug- und Druckkräften ausgelegt ist.The gear member 20 and thus the active element 4 is designed as a telescopically extendable handlebar 40, which is designed for the transmission of tensile and compressive forces.
Die Lenkerstange 40 weist ein erstes, äußeres Teleskoprohr 42 sowie ein zweites, inneres Teleskoprohr 44 auf. Das innere Teleskoprohr 44 ist mittels eines ringförmigen Lagers 43 im äußeren Teleskoprohr 42 axial verschiebbar gelagert, wie besonders gut in
Um diese Expansion der teleskopartig ausfahrbaren Lenkerstange 40 zu verhindern, ist eine lösbare Verriegelungsvorrichtung 60 vorgesehen, die im Bereich des offenen Endes des äußeren Teleskoprohrs 42 am äußeren Teleskoprohr 42 angebracht ist und Teil einer Auslösevorrichtung 6 für das Wirkelement 4 ist. Die Verriegelungsvorrichtung 60 weist einen radial verschiebbaren Schieber als Arretiereinrichtung 64 auf, dessen radial inneres Ende in der in
Während
Wie in den
Bezugszeichen in den Ansprüchen, der Beschreibung und den Zeichnungen dienen lediglich dem besseren Verständnis der Erfindung und sollen den Schutzumfang nicht einschränken.Reference signs in the claims, the description and the drawings are only for the better understanding of the invention and are not intended to limit the scope.
Es bezeichnen:
- 1
- Steuerfläche
- 2
- Getriebe
- 3
- Antriebseinrichtung
- 4
- Wirkelement
- 5
- Energiespeicher
- 6
- Auslösevorrichtung
- 10
- Achse
- 12
- Schwenkhebel
- 14
- Anschlag
- 20
- Getriebeglied
- 21
- Kopfende
- 22
- Gelenk
- 23
- Fußende
- 24
- Gelenk
- 30
- Antriebsmuffe
- 32
- Antriebsspindel
- 33
- Antriebsachse
- 34
- Antriebsmotor
- 40
- Lenkerstange
- 42
- äußeres Teleskoprohr
- 44
- inneres Teleskoprohr
- 50
- Druckfeder
- 60
- Verriegelungsvorrichtung
- 62
- Rastvorsprung
- 64
- Arretiereinrichtung
- 66
- Steuereinheit
- 1
- control surface
- 2
- transmission
- 3
- driving means
- 4
- active element
- 5
- energy storage
- 6
- triggering device
- 10
- axis
- 12
- pivoting lever
- 14
- attack
- 20
- transmission member
- 21
- head
- 22
- joint
- 23
- foot
- 24
- joint
- 30
- drive sleeve
- 32
- drive spindle
- 33
- drive axle
- 34
- drive motor
- 40
- handlebar
- 42
- outer telescopic tube
- 44
- inner telescopic tube
- 50
- compression spring
- 60
- locking device
- 62
- catch projection
- 64
- locking
- 66
- control unit
Claims (12)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE200910007731 DE102009007731A1 (en) | 2009-02-05 | 2009-02-05 | Flight crash device for a missile |
Publications (3)
Publication Number | Publication Date |
---|---|
EP2216619A2 true EP2216619A2 (en) | 2010-08-11 |
EP2216619A3 EP2216619A3 (en) | 2014-03-19 |
EP2216619B1 EP2216619B1 (en) | 2016-12-14 |
Family
ID=41785918
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP10001071.9A Active EP2216619B1 (en) | 2009-02-05 | 2010-02-03 | Flight abort device for a missile |
Country Status (2)
Country | Link |
---|---|
EP (1) | EP2216619B1 (en) |
DE (1) | DE102009007731A1 (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2024039423A1 (en) * | 2022-08-17 | 2024-02-22 | Raytheon Company | Sliding pin-yoke mechanism |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102020119446B4 (en) | 2020-05-18 | 2022-01-05 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Risk minimization device for the flight termination of a flight system, method for risk reduction in the flight termination of a flight system and flight system |
Family Cites Families (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3352513A (en) * | 1966-03-25 | 1967-11-14 | George W Baker | Helicopter rotor shaft and rotor blade severing means |
DE4135557C2 (en) * | 1991-10-29 | 1999-05-06 | Diehl Stiftung & Co | Rudder control device |
DE19635847C2 (en) * | 1996-09-04 | 1998-07-16 | Daimler Benz Aerospace Ag | Guided missile with ramjet drive |
-
2009
- 2009-02-05 DE DE200910007731 patent/DE102009007731A1/en not_active Withdrawn
-
2010
- 2010-02-03 EP EP10001071.9A patent/EP2216619B1/en active Active
Non-Patent Citations (1)
Title |
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None |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2024039423A1 (en) * | 2022-08-17 | 2024-02-22 | Raytheon Company | Sliding pin-yoke mechanism |
Also Published As
Publication number | Publication date |
---|---|
DE102009007731A1 (en) | 2010-08-19 |
EP2216619A3 (en) | 2014-03-19 |
EP2216619B1 (en) | 2016-12-14 |
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