EP1674818A1 - Missile - Google Patents

Missile Download PDF

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Publication number
EP1674818A1
EP1674818A1 EP05027434A EP05027434A EP1674818A1 EP 1674818 A1 EP1674818 A1 EP 1674818A1 EP 05027434 A EP05027434 A EP 05027434A EP 05027434 A EP05027434 A EP 05027434A EP 1674818 A1 EP1674818 A1 EP 1674818A1
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EP
European Patent Office
Prior art keywords
hlm
missile
steering
pulses
target
Prior art date
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Granted
Application number
EP05027434A
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German (de)
French (fr)
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EP1674818B1 (en
Inventor
Peter Gleich
Erich Waxweiler
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
LFK Lenkflugkoerpersysteme GmbH
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LFK Lenkflugkoerpersysteme GmbH
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Application filed by LFK Lenkflugkoerpersysteme GmbH filed Critical LFK Lenkflugkoerpersysteme GmbH
Publication of EP1674818A1 publication Critical patent/EP1674818A1/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41H—ARMOUR; ARMOURED TURRETS; ARMOURED OR ARMED VEHICLES; MEANS OF ATTACK OR DEFENCE, e.g. CAMOUFLAGE, IN GENERAL
    • F41H13/00—Means of attack or defence not otherwise provided for
    • F41H13/0043—Directed energy weapons, i.e. devices that direct a beam of high energy content toward a target for incapacitating or destroying the target
    • F41H13/0068—Directed energy weapons, i.e. devices that direct a beam of high energy content toward a target for incapacitating or destroying the target the high-energy beam being of microwave type, e.g. for causing a heating effect in the target
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
    • F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
    • F42B12/36—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information

Definitions

  • the invention relates to a missile according to the preamble of the claim.
  • missiles There are numerous embodiments of missiles for a variety of applications known. In modern conflict scenarios increasingly attack missions of so-called. "Cheap drones" are described, which are equipped with chemical or biological weapons, z. For example, future out-of-range missions could pose an immense potential threat to troops.
  • HLM high-power microwave
  • the missile can serially combat multiple attack drones by disrupting or destroying their electronic components and forcing them to crash or crash.
  • the HLM missile After being instructed by external sensor systems (eg ground / airborne radars), the HLM missile navigates autonomously to a target expectation area, which by higher-level sensor / fire control systems from the target position and Target speed was calculated. During its flight there, the target heading of the missile is updated externally at regular intervals.
  • external sensor systems eg ground / airborne radars
  • the on-board sensor takes over the search for the target and guides the missile closer to the target by means of a prescribed steering law.
  • a defined approach geometry must be maintained, which allows a directed to the target radiation of the HLM pulses by means of rigidly installed FK antennas.
  • the control of the missile is carried out by aerodynamic bow or stern rudder, the control concept corresponds to the classic "bank to turn" principle of single wing aircraft.
  • the two variants are shown in FIGS. 1a and 1b or 2a and 2b.
  • the autopilot converts the steering commands in the marching phase and in the final steering phase into the corresponding control commands in a known manner.
  • Superordinate ground or airborne sensors detect approaching drones, their position, heading and speed are measured and forwarded to an appropriate launch facility for HLM missiles.
  • the selected HLM missile is programmed with a first estimate of the target expectation space (target and missile position at the meeting).
  • the missile is launched by solids discharge booster or by catapult, the jet engine runs high, the starting booster is dropped and the missile heads for the roughly calculated target expectation space.
  • the use of a start booster is not necessary, if in principle should be started with the help of a catapult.
  • the target expectation space is permanently updated by the external target measurement the missile will be informed by data link the resulting course corrections.
  • the on-board end-phase sensor takes over the FK steering, as described above.
  • the FK is trained on the next target u.s.w ..
  • the FK autonomously enters the march back to the predetermined or data link commanded landing.
  • the missile can be launched after a general function check, the installation of a new booster and after refueling to another mission.
  • the missile can be used in addition to the focus task of drone hunting for other missions in which the destruction / destruction of relatively little shielded electronic components is intended.

Abstract

The space vehicle with an airframe, transmission, fuel tank, aerodynamic lift and control surfaces, navigation-, control-, and steering electronics, energy supply device, and communications device for data exchange with a command center. The vehicle includes high power microwave generator for production of HLM-pulses, directional aerial, end phase sensor for steering on local aim region, HLM shield for electronic unit, and parachute/umbrella/rescue system.

Description

Die Erfindung betrifft einen Flugkörper nach dem Oberbegriff des Patentanspruchs.The invention relates to a missile according to the preamble of the claim.

Es sind zahlreiche Ausführungsformen von Flugkörpern für die unterschiedlichsten Anwendungen bekannt. In modernen Konfliktszenarien werden zunehmend Angriffsmissionen von sog. "Billigdrohnen" beschrieben, die mit chemischen oder biologischen Kampfmitteln bestückt, z. B. in zukünftigen Outof- Area Einsätzen eine immense potenzielle Gefahr für die Truppen darstellen können.There are numerous embodiments of missiles for a variety of applications known. In modern conflict scenarios increasingly attack missions of so-called. "Cheap drones" are described, which are equipped with chemical or biological weapons, z. For example, future out-of-range missions could pose an immense potential threat to troops.

Es gibt Systemansätze zur Bekämpfung dieser Drohnen, die jedoch schwerpunktmäßig auf eine Zerstörung der Angreifer in der Endphase des Angriffs abzielen und somit in der Reichweite sehr beschränkt sind. Als Beispiele seien Maschinenkanonen mit spezieller Splittermunition, Hochenergielaser usw. genannt. Um jedoch etwaige Massenangriffe oder räumlich-zeitlich gestaffelte Angriffe sinnvoll abwehren zu können, ist für das Abwehrsystem eine gewisse Stand-off-Fähigkeit zu fordern. Diese könnte durch die Bekämpfung der Angriffsdrohnen mittels einer oder mehrerer Drohnenjagd-Flugkörper schon in größeren Entfernungen sichergestellt werden.There are system approaches to combat these drones, but they focus on destroying attackers in the final stages of the attack and are therefore very limited in range. Examples include machine guns with special splinter ammunition, high-energy lasers, etc. However, in order to effectively ward off any mass attacks or spatially-temporal staggered attacks, a certain stand-off capability has to be demanded of the defense system. This could be ensured by fighting the attack drones by means of one or more drone-hunting missiles even at greater distances.

Es ist das Ziel der Erfindung, einen Flugkörper zu schaffen, der eine effiziente und kostengünstige Bekämpfungsmöglichkeit für mehrere Drohnen bietet. Dies wird durch die Merkmale nach dem kennzeichnenden Teil des Patentanspruchs erreicht.It is the object of the invention to provide a missile that provides an efficient and cost-effective way to control multiple drones. This is achieved by the features according to the characterizing part of the patent claim.

Wichtige Merkmale des erfindungsgemäßen Jagdflugkörpers sind dabei sowohl das mehrfach nutzbare HLM (= Hochleistungs-Mikrowellen)-Wirksystem, das ohne Selbstzerstörung des Flugkörpers eingesetzt werden kann, als auch die Wiederverwendbarkeit des Flugkörpers selbst, der für mehrere Missionen einsetzbar ist. Mit dem HLM-Wirksystem kann der Flugkörper seriell mehrere Angriffsdrohnen durch Störung bzw. Zerstörung von deren Elekronikkomponenten wirksam bekämpfen und sie zum Absturz oder Missionsabbruch zwingen.Important features of the hunting missile according to the invention are both the reusable HLM (= high-power microwave) -Wirksystem that can be used without self-destruction of the missile, as well as the reusability of the missile itself, which can be used for multiple missions. With the HLM action system, the missile can serially combat multiple attack drones by disrupting or destroying their electronic components and forcing them to crash or crash.

Einzelheiten der Erfindung ergeben sich aus der Beschreibung, in der anhand der Zeichnung zwei Ausführungsbeispiele erörtert werden. Es zeigen

  • Fig. 1a und 1b einen erfindungsgemäßen Flugkörper mit Hecksteuerung und
  • Fig. 2a und 2b einen erfindungsgemäßen Flugkörper mit Entensteuerung.
Details of the invention will become apparent from the description in which reference to the drawings, two embodiments are discussed. Show it
  • Fig. 1a and 1b a missile according to the invention with rear control and
  • 2a and 2b show a missile according to the invention with duck control.

Der HLM-Flugkörper gemäß der Erfindung besitzt einen flugzeugähnlichen Airframe, in den folgende Komponenten integriert sind:

  • Endphasensensor (z.B. IR) zur Lenkung des FK's im Zielnahbereich, zur Heranführung des Jagdflugkörpers an das Ziel
  • Hochleistungs-Mikrowellen-Generator zur Erzeugung von HLM-Impulsen
  • Richtantennen zur räumlich gerichteten Abgabe der HLM-Impulse
  • Navigations-, Lenk- und Regelelektonik, die elektromagnetisch entsprechend abgeschirmt werden muss, damit sie nicht durch die eigenen Impulse beeinträchtigt werden kann. Sie besteht aus den Subkomponenten IMU, GPS und Bordrechner.
  • Datenlink zur Kommunikation der Bodenanlage/Kommandozentrale mit dem Flugkörper
  • Turboluftstrahltriebwerk oder alternative Antriebssysteme (Propeller, Raketentriebwerk...) mit Treibstofftank
  • Fallschirm/Gleitschirm-Bergungssystem
  • Geeignete Auftriebsflächen und Aerodynamikruder
  • Elekromechanische Rudermaschinen zum Antrieb der Aerodynamikruder
  • Elektrische Energieversorgung für den HLM-Generator, die komplette Sensorik, sowie für die elektromechanischen Rudermaschinen
The HLM missile according to the invention has an aircraft-like airframe, in which the following components are integrated:
  • End phase sensor (eg IR) to steer the FK's in the Zielnahbereich, to bring the Jagdflugkörpers to the target
  • High power microwave generator for generating HLM pulses
  • Directional antennas for spatially directed delivery of HLM pulses
  • Navigation, steering and control electronics, which must be shielded electromagnetically accordingly, so that they can not be affected by their own impulses. It consists of the subcomponents IMU, GPS and on-board computer.
  • Data link for communication of the ground installation / command center with the missile
  • Turbo jet engine or alternative propulsion systems (propeller, rocket engine ...) with fuel tank
  • Parachute / paraglider recovery system
  • Suitable lifting surfaces and aerodynamic rudder
  • Elecromechanical rudders for driving the aerodynamic rudder
  • Electrical power supply for the HLM generator, the complete sensor system, as well as for the electromechanical steering machines

Nach Einweisung durch externe Sensorsysteme (z.B. boden/luftgestützte Radare) navigiert der HLM-Flugkörper autonom in einen Zielerwartungsbereich, welcher durch übergeordnete Sensor-/Feuerleitanlagen aus der Zielposition und Zielgeschwindigkeit errechnet wurde. Während seines Fluges dorthin wird der Soll-Kurs des Flugkörpers in regelmäßigen Zeitabständen von extern aktualisiert.After being instructed by external sensor systems (eg ground / airborne radars), the HLM missile navigates autonomously to a target expectation area, which by higher-level sensor / fire control systems from the target position and Target speed was calculated. During its flight there, the target heading of the missile is updated externally at regular intervals.

Im Zielnahbereich übernimmt der bordeigene Sensor die Zielsuche und führt den Flugkörper per vorgegebenem Lenkgesetz noch näher an das Ziel heran. Dabei muß eine definierte Annäherungsgeometrie eingehalten werden, die eine auf das Ziel gerichtete Abstrahlung der HLM-Impulse mittels der starr eingebauten FK-Antennen erlaubt.In the near-end area, the on-board sensor takes over the search for the target and guides the missile closer to the target by means of a prescribed steering law. In this case, a defined approach geometry must be maintained, which allows a directed to the target radiation of the HLM pulses by means of rigidly installed FK antennas.

Die Abstrahlung mehrerer Impulse geschieht dann in unmittelbarer Zielnähe, bei Restentfernungen von ca. kleiner 50 m.The emission of several impulses happens then in direct proximity to the target, with residual distances of approx. Less than 50 m.

Die Steuerung des Flugkörpers wird mittels aerodynamischer Bug - oder Heckruder durchgeführt, das Steuerungskonzept entspricht dem klassischen "Bank to Turn"-Prinzip von Ebenflügel-Fluggeräten. Die beiden Varianten sind in den Figuren 1a und 1 b bzw. 2a und 2b dargestellt.The control of the missile is carried out by aerodynamic bow or stern rudder, the control concept corresponds to the classic "bank to turn" principle of single wing aircraft. The two variants are shown in FIGS. 1a and 1b or 2a and 2b.

Der Autopilot setzt in bekannter Weise die Lenkkommandos in der Marschphase und in der Endlenkphase in die entsprechenden Steuerkommandos um.The autopilot converts the steering commands in the marching phase and in the final steering phase into the corresponding control commands in a known manner.

Durch übergeordnete boden- oder luftgestützte Sensoren werden anfliegende Drohnen entdeckt, deren Position, Kurs und Geschwindigkeit werden vermessen und an eine entsprechende Startanlage für HLM- Flugkörper weitergeleitet.Superordinate ground or airborne sensors detect approaching drones, their position, heading and speed are measured and forwarded to an appropriate launch facility for HLM missiles.

Vor dem Start wird dem ausgewählten HLM-Flugkörper eine erste Abschätzung des Zielerwartungsraums (Ziel- und Flugkörperposition beim Zusammentreffen) einprogrammiert.Before starting, the selected HLM missile is programmed with a first estimate of the target expectation space (target and missile position at the meeting).

Der Flugkörper wird per Feststoffabwurfbooster oder per Katapult gestartet, das Luftstrahltriebwerk läuft hoch, der Startbooster wird abgeworfen und der Flugkörper nimmt Kurs auf den grob berechneten Zielerwartungsraum. Die Verwendung eines Startboosters entfällt, wenn grundsätzlich mit Hilfe eines Katapults gestartet werden soll.The missile is launched by solids discharge booster or by catapult, the jet engine runs high, the starting booster is dropped and the missile heads for the roughly calculated target expectation space. The use of a start booster is not necessary, if in principle should be started with the help of a catapult.

Während seiner Annäherung an das ausgesuchte Ziel wird der Zielerwartungsraum durch die externe Zielvermessung permanent aktualisiert und dem Flugkörper werden per Datenlink die resultierenden Kurskorrekturen mitgeteilt.During its approach to the chosen destination, the target expectation space is permanently updated by the external target measurement the missile will be informed by data link the resulting course corrections.

Im Zielnahbereich übernimmt der bordeigene Endphasensensor die FK-Lenkung, wie oben bereits beschrieben.In the near-end area, the on-board end-phase sensor takes over the FK steering, as described above.

Nach der Bekämpfung des ersten Drohnenziels wird der FK auf das nächste Ziel eingewiesen u.s.w..After fighting the first drone target, the FK is trained on the next target u.s.w ..

Nach der Bekämpfung des letzten Ziels bzw. nach Erreichen der für den Rückmarsch benötigten Treibstoffrestmenge, bzw. nach Rückruf durch die Kommandozentrale tritt der FK autonom den Rückmarsch zum vorbestimmten oder per Datenlink kommandierten Landeort an.After fighting the last goal or after reaching the required fuel for the return march, or after recall by the command center, the FK autonomously enters the march back to the predetermined or data link commanded landing.

Über dem Landeort wird das Fallschirm/Gleitschirm-Bergungssystem ausgelöst und der FK kann geborgen werden.Over the landing site the parachute / paraglider recovery system is triggered and the FK can be salvaged.

Der Flugkörper kann nach einer allgemeinen Funktionsüberprüfung, dem Anbau eines neuen Startboosters sowie nach Auftanken zu einer weiteren Mission gestartet werden.The missile can be launched after a general function check, the installation of a new booster and after refueling to another mission.

Der Anbau eines neuen Startboosters entfällt für die Katapultstart-Version.The addition of a new start booster is not required for the catapult start version.

Der Flugkörper kann neben der Schwerpunktaufgabe der Drohnenjagd auch für andere Missionen eingesetzt werden, in denen die Störung/Zerstörung von relativ wenig abgeschirmten Elektronikbauteilen beabsichtigt wird.The missile can be used in addition to the focus task of drone hunting for other missions in which the destruction / destruction of relatively little shielded electronic components is intended.

Claims (1)

Flugkörper mit einem Rumpf (Airframe), einem Triebwerk, Treibstofftanks und aerodynamisch wirksamen Auftriebs und Steuerflächen, mit einer Navigations-, Lenk- und Regelelektronik, einer Energieversorgungseinrichtung und einer Kommunikationseinrichtung zum Datenaustausch mit einer Kommandozentrale, dadurch gekennzeichnet, dass er
einen Hochleistungs-Mikrowellengenerator zur Erzeugung von HLM-Impulsen,
eine Richtantenne zur räumlich gerichteten Abgabe der HLM-Impulse,
einen Endphasensensor zur Lenkung im Zielnahbereich,
eine Abschirmung für die elektronischen Einrichtungen gegen die erzeugten HLM-Impulse sowie
ein Fallschirm/Gleitschirm-Bergungssystem aufweist.Missile with a fuselage (airframe), an engine, fuel tanks and aerodynamically effective buoyancy and control surfaces, with a navigation, steering and control electronics, a power supply device and a communication device for data exchange with a command center, characterized in that
a high power microwave generator for generating HLM pulses,
a directional antenna for the spatially directed delivery of the HLM pulses,
an end-phase sensor for steering in the target area,
a shield for the electronic devices against the generated HLM pulses as well
a parachute / paraglider recovery system.
EP20050027434 2004-12-23 2005-12-15 Missile Revoked EP1674818B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE200410061979 DE102004061979B4 (en) 2004-12-23 2004-12-23 missile

Publications (2)

Publication Number Publication Date
EP1674818A1 true EP1674818A1 (en) 2006-06-28
EP1674818B1 EP1674818B1 (en) 2010-07-21

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ID=35840438

Family Applications (1)

Application Number Title Priority Date Filing Date
EP20050027434 Revoked EP1674818B1 (en) 2004-12-23 2005-12-15 Missile

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EP (1) EP1674818B1 (en)
DE (2) DE102004061979B4 (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2008147290A1 (en) * 2007-05-29 2008-12-04 Totalförsvarets Forskningsinstitut Warhead
WO2008147291A1 (en) * 2007-05-29 2008-12-04 Totalförsvarets Forskningsinstitut Warhead

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102007054382A1 (en) * 2007-11-14 2009-05-20 Diehl Bgt Defence Gmbh & Co. Kg Ammunition, with a self-destruction facility, carries a small explosive charge to fracture the casing on a remote command
DE102013006812B4 (en) * 2013-04-19 2015-01-15 Mbda Deutschland Gmbh Guided missile and active system, comprising the guided missile

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1568490A (en) * 1967-06-09 1969-05-23
US5192827A (en) * 1991-12-19 1993-03-09 The United States Of America As Represented By The Secretary Of The Army Microwave projectile

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10044867A1 (en) * 2000-09-12 2002-03-21 Rheinmetall W & M Gmbh Explosive-powered RF radiation source

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1568490A (en) * 1967-06-09 1969-05-23
US5192827A (en) * 1991-12-19 1993-03-09 The United States Of America As Represented By The Secretary Of The Army Microwave projectile

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2008147290A1 (en) * 2007-05-29 2008-12-04 Totalförsvarets Forskningsinstitut Warhead
WO2008147291A1 (en) * 2007-05-29 2008-12-04 Totalförsvarets Forskningsinstitut Warhead

Also Published As

Publication number Publication date
DE102004061979B4 (en) 2009-10-29
DE502005009943D1 (en) 2010-09-02
EP1674818B1 (en) 2010-07-21
DE102004061979A1 (en) 2006-07-06

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