EP1870663B1 - Airborne target - Google Patents

Airborne target Download PDF

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Publication number
EP1870663B1
EP1870663B1 EP07011644A EP07011644A EP1870663B1 EP 1870663 B1 EP1870663 B1 EP 1870663B1 EP 07011644 A EP07011644 A EP 07011644A EP 07011644 A EP07011644 A EP 07011644A EP 1870663 B1 EP1870663 B1 EP 1870663B1
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Prior art keywords
axis
airborne target
heating wire
target according
winding
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German (de)
French (fr)
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EP1870663A2 (en
EP1870663A3 (en
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Bernt Dr. Obkircher
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Airbus Defence and Space GmbH
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EADS Deutschland GmbH
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41J—TARGETS; TARGET RANGES; BULLET CATCHERS
    • F41J2/00—Reflecting targets, e.g. radar-reflector targets; Active targets transmitting electromagnetic or acoustic waves
    • F41J2/02—Active targets transmitting infrared radiation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41J—TARGETS; TARGET RANGES; BULLET CATCHERS
    • F41J9/00—Moving targets, i.e. moving when fired at
    • F41J9/08—Airborne targets, e.g. drones, kites, balloons
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41J—TARGETS; TARGET RANGES; BULLET CATCHERS
    • F41J9/00—Moving targets, i.e. moving when fired at
    • F41J9/08—Airborne targets, e.g. drones, kites, balloons
    • F41J9/10—Airborne targets, e.g. drones, kites, balloons towed
    • 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
    • F42B12/38—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 of tracer type
    • F42B12/382—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 of tracer type emitting an electromagnetic radiation, e.g. laser beam or infrared emission

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Electromagnetism (AREA)
  • Physics & Mathematics (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Optics & Photonics (AREA)
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  • Radar, Positioning & Navigation (AREA)
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Abstract

The target has an electrically operated heating wire (1) for generating infrared radiation. The wire is rolled up in windings (Wa, We) around an axis (Z), where the windings run along the axis. A surface that is surrounded by the winding (Wa) is larger than a surface surrounded by the winding (We). The axis is aligned parallel to a longitudinal axis of the airborne target. The heating wire is attached on a carrier body e.g. heat insulator, that is coated with a conductive layer. An infrared dome made of zinc sulfide, zinc selenide or magnesium fluoride is provided behind the heating wire.

Description

Die Erfindung betrifft ein Fluggerät zur IR-Flugzieldarstellung nach dem Oberbegriff des Patentanspruchs 1. Ein solches Gerät ist aus der EP 0 911 601 bekannt.The invention relates to an aircraft for IR-target aircraft according to the preamble of claim 1. Such a device is known from EP 0 911 601 known.

Zum Zwecke der Übung für Boden/Luft- oder Luft/Luft-Waffensysteme mit Infrarot(IR)-Lenkung werden unbemannte Fluggeräte als Flugziele verwendet. Diese Fluggeräte können Schleppflugkörper oder Drohnen sein. Sie sollen möglichst nicht nur die kinetischen Eigenschaften der echten Ziele (z. B. Kampfflugzeuge) simulieren, sondern auch die gleiche Infrarot-(lR)-Abstrahlung aufweisen.For the purpose of ground / air or air / air weapon systems with infrared (IR) steering, unmanned aerial vehicles will be used as destinations. These aircraft may be tow plows or drones. As much as possible, they should not only simulate the kinetic properties of the real targets (eg fighter jets), but also have the same infrared (IR) radiation.

Aus DE 40 24 263 C1 sind selbstgetriebene Flugkörper mit pyrotechnisch betriebenen Glühladungen bekannt. Die IR-Abstrahlung wird im Wesentlichen dadurch erzielt, dass die Glühladung eine am Heck des Flugkörpers angeordnete dünne Metallplatte aufheizt.Out DE 40 24 263 C1 Self-propelled missiles are known with pyrotechnically operated incandescent charges. The IR radiation is essentially achieved by the fact that the glow charge heats up a thin metal plate arranged at the rear of the missile.

Bekannt sind Schleppflugkörper und Zieldrohnen, die die gewünschte IR-Abstrahlung mit so genannten Tracking-Flares erzeugen. Diese haben den Nachteil, dass sie im Visuellen sichtbar sind und eine Rauchfahne hinter sich her ziehen. Darüber hinaus ist die spektrale Charakteristik dieser Flares nicht an die Strahlung der echten Ziele angepaßt. Außerdem sorgen Ungleichmäßigkeiten im Abbrand der Flares für unerwünschte Track-Probleme im IR-Suchkopf.Known are Schleppflug body and target drones that produce the desired IR radiation with so-called tracking flares. These have the disadvantage that they are visible in the visual and pull a trail of smoke behind them. In addition, the spectral characteristics of these flares are not matched to the radiation of the real targets. In addition, irregularities in the erosion of the flares cause unwanted track problems in the IR seeker head.

Aus EP 0 876 579 B1 und WO 00/29804 sind Flugziele bekannt, bei welchen heiße Gase aus einem mitgeführten Brenner in die Nase der Flugziele geleitet werden. Dort werden die Teile der Nase aufgeheizt und dienen als Infrarotstrahler. Nachteilig ist hier neben dem aufwendigen Brenneraufbau und der komplizierten Zuluft- und Abgasführung zur Sicherstellung einer stabilen Verbrennung, dass die Nase vom Fahrtwind von außen stark gekühlt wird, so dass zur Erzielung einer ausreichenden IR-Abstrahlung sehr hohe Heizleistungen notwendig sind.Out EP 0 876 579 B1 and WO 00/29804 Flight destinations are known in which hot gases are passed from a entrained burner in the nose of the destinations. There the parts of the nose are heated up and serve as infrared radiators. The disadvantage here, in addition to the complex burner design and the complicated Zuluft- and exhaust system to ensure stable combustion that the nose is strongly cooled by the wind from the outside, so that very high heat outputs are necessary to achieve a sufficient IR radiation.

Aus DE 102 10 433 C1 ist ein Flugziel bekannt, bei welchem eine Fluggasturbine in Flugrichtung vor der Nase des Flugziels angeordnet ist. Die sich im Abgasstrahl der Fluggasturbine befindliche Nase des Flugziels dient als Infrarotstrahler. Ein Nachteil dieser Anordnung ist die schlechte Aerodynamik des Flugziels.Out DE 102 10 433 C1 is a destination known in which an aircraft gas turbine is arranged in the direction of flight in front of the nose of the destination. The nose of the target located in the exhaust gas jet of the aircraft gas turbine serves as an infrared radiator. A disadvantage of this arrangement is the poor aerodynamics of the destination.

Aus EP 0 911 601 B1 ist ein Flugziel bekannt, bei welchem in der Nase ein elektrisch betriebener Heizdraht auf einer flachen Radiatorplatte angeordnet ist. Ein Nachteil dieser Anordnung ist, dass eine IR-Abstrahlung nur in Flugrichtung möglich ist. Eine IR-Abstrahlung seitlich zur Flugrichtung ist nur mit großem baulichen Aufwand möglich.Out EP 0 911 601 B1 is a destination known in which an electrically operated heating wire is arranged on a flat radiator plate in the nose. A disadvantage of this arrangement is that an IR radiation is possible only in the direction of flight. An IR radiation laterally to the direction of flight is possible only with great structural complexity.

Es ist Aufgabe der Erfindung, ein gattungsgemäßes Flugziel anzugeben, mit welchem eine räumliche IR-Abstrahlung in Flugrichtung und seitlich zur Flugrichtung ohne großen baulichen Aufwand möglich ist.It is an object of the invention to provide a generic destination, with which a spatial IR radiation in the direction of flight and laterally to the direction of flight is possible without great structural complexity.

Diese Aufgabe löst das Flugziel mit den Merkmalen gemäß Patentanspruch 1. Weitere vorteilhafte Ausgestaltungen der Erfindung sind Gegenstand von Unteransprüchen.This object is achieved by the destination with the features according to claim 1. Further advantageous embodiments of the invention are the subject of dependent claims.

Erfindungsgemäß ist der Heizdraht in mehreren Windungen W um eine Achse Z aufgewickelt ist, wobei die Wicklung entlang der Achse Z verläuft und die von der ersten Windung W_a eingeschlossene Fläche größer als die von der letzten Windung W_e eingeschlossene Fläche ist. Dadurch wird gewährleistet, dass eine IR-Abstrahlung in einen großen Raumwinkel möglich ist. Außerdem wird der bauliche Aufwand bei optimaler Raumausnutzung gering gehalten.According to the invention, the heating wire is wound in several turns W about an axis Z, wherein the winding runs along the axis Z and the area enclosed by the first turn W_a is greater than the area enclosed by the last turn W_e. This ensures that an IR radiation in a large solid angle is possible. In addition, the structural complexity is kept low with optimal space utilization.

Unter einer von einer Windung eingeschlossenen Fläche wird dabei die Fläche verstanden, welche die jeweilige Windung in einer Projektionsfläche senkrecht zur Achse Z einschließt.In this context, a surface enclosed by a turn is understood to mean the surface which encloses the respective turn in a projection surface perpendicular to the axis Z.

Der erfindungsgemäße Heizdraht bildet somit eine in Richtung der Achse Z gezogene Wicklung. Das Wickelgebilde weist zumindest Abstrahlflächen senkrecht und parallel zur Achse Z auf. Das Wickelgebilde kann aber auch weitere Abstrahlflächen in anderen Raumrichtungen als senkrecht oder parallel zur Achse Z aufweisen.
Die Abstrahlfläche in z.B. Flugrichtung ist definiert durch die Projektion des Wickelgebildes auf eine Ebene senkrecht zur Achse Z, wenn die Achse Z parallel zur Flugachse des Flugziels ausgerichtet ist. Die Abstrahlfläche seitlich zur Flugrichtung ist für den gleichen Fall entsprechend definiert durch eine Projektion auf eine Ebene senkrecht zur Achse Z.The heating wire according to the invention thus forms a drawn in the direction of the axis Z winding. The winding structure has at least radiating surfaces perpendicular and parallel to the axis Z. But the winding structure can also have other radiating surfaces in other spatial directions than perpendicular or parallel to the axis Z.
The emission surface in eg flight direction is defined by the projection of the winding structure on a plane perpendicular to the axis Z, when the axis Z is aligned parallel to the flight axis of the target. The emission surface laterally to the direction of flight is correspondingly defined for the same case by a projection onto a plane perpendicular to the axis Z.

Im einfachsten Fall ist der Heizdraht zu einer konischen Spirale gewickelt. Unter einer konischen Spirale, auch als kegelförmige Raumspirale bezeichnet, versteht man eine Überlagerungskurve von Spirale und Schraube. Eine Spirale ist dabei ein Gebilde in der Ebene, ähnlich den Rillen einer Schallplatte. Eine Schraube ist ein räumliches Gebilde entlang des Mantels eines Zylinders.In the simplest case, the heating wire is wound into a conical spiral. A conical spiral, also referred to as a conical space spiral, is understood to mean a superposition curve of spiral and screw. A spiral is a structure in the plane, similar to the grooves of a record. A screw is a spatial formation along the mantle of a cylinder.

Mit anderen Worten, der Heizdraht ist um die Achse Z gewickelt ist, wobei sich der Durchmesser D der einzelnen Windungen der Wicklung in Längsrichtung der Achse verjüngt. Die Wicklung um die Achse Z erfolgt zweckmäßig symmetrisch. Unter dem Durchmesser D wird hierbei der mittlere Durchmesser der jeweiligen Windung verstanden. Bei einer quadratischen Wicklung, d.h. die Windung bildet die Umrandung eines Quadrats ist der Durchmesser die Diagonale des Quadrats.In other words, the heating wire is wound around the axis Z, wherein the diameter D of the individual turns of the winding tapers in the longitudinal direction of the axis. The winding about the axis Z is expediently symmetrical. The diameter D is understood to mean the average diameter of the respective turn. For a square winding, i. the winding forms the border of a square, the diameter is the diagonal of the square.

Mit der Erfindung ist somit eine IR-Abstrahlung nicht nur in Flugrichtung des Flugziels, sondern auch seitlich dazu möglich.With the invention, therefore, an IR radiation not only in the direction of flight of the target, but also laterally possible.

Die Erfindung sowie weitere vorteilhafte Ausführungen der Erfindung werden im Folgenden anhand von Figuren näher erläutert. Es zeigen:

Fig. 1
einen erfindungsgemäßen Heizdraht,
Fig. 2
einen senkrechten Schnitt entlang der Längsachse eines erfindungsgemäßen Flugziels.
The invention and further advantageous embodiments of the invention are explained in more detail below with reference to figures. Show it:
Fig. 1
a heating wire according to the invention,
Fig. 2
a vertical section along the longitudinal axis of a flight destination according to the invention.

Fig. 1 zeigt beispielhaft einen erfindungsgemäßen Heizdraht in Form einer Heizspirale. Der Heizdraht 1 weist ein erstes Ende 2 und ein zweites Ende 3 auf. Das erste Ende 2 verläuft dabei parallel zur Symmetrieachse Z.
In diesem Beispiel beschreibt der Heizdraht 1 die Form einer Heizspirale, wobei sich das eine Ende 2 näher an der Achse Z befindet als das andere Ende 3. Die erste Windung W_e umrandet dabei eine größere Fläche als die letzte Windung W_e der Wicklung. Fig. 1 shows an example of a heating wire according to the invention in the form of a heating coil. The heating wire 1 has a first end 2 and a second end 3. The first end 2 runs parallel to the axis of symmetry Z.
In this example, the heating wire 1 describes the shape of a heating coil, wherein the one end 2 is closer to the axis Z than the other end 3. The first turn W_e surrounds a larger area than the last turn W_e the winding.

Zweckmäßig besteht der Heizdraht 1 aus einem Element. Es ist aber auch möglich, dass der Heizdraht 1 aus mehreren Elementen aufgebaut ist. Im Weiteren wird der Heizdraht auch als Heizelement bezeichnet.Suitably, the heating wire 1 consists of an element. But it is also possible that the heating wire 1 is composed of several elements. In addition, the heating wire is also referred to as a heating element.

Der Heizdraht 1 besteht aus einem temperaturbeständigen Material, z.B. Nickelchrom. Es sind aber auch andere Materialzusammensetzungen möglich, deren Temperaturbeständigkeit bei bis zu 750°C liegt.The heating wire 1 is made of a temperature resistant material, e.g. Nickel chrome. However, other material compositions are possible whose temperature resistance is up to 750 ° C.

Die Ganghöhe der einzelnen Wicklungen ist zweckmäßig gering, z.B. kleiner als der Durchmesser des Heizdrahtes, um ein gute Überdeckung des Trägerkörpers zu erreichen. Dadurch wird eine möglichst große Länge des gewickelten Heizdrahtes erreicht, wodurch eine effektive IR-Abstrahlung gewährleistet wird.The pitch of the individual windings is expediently low, e.g. smaller than the diameter of the heating wire, in order to achieve a good coverage of the carrier body. As a result, the largest possible length of the wound heating wire is achieved, whereby an effective IR radiation is ensured.

Fig. 2 zeigt in einer schematischen Darstellung einen Schnitt entlang der Längsachse eines erfindungsgemäßen Flugziels. Insbesondere ist in Fig. 2 der Bug des Flugziels dargestellt. Das Heizelement 1 ist innerhalb des Flugziels 4 angeordnet, wobei das Flugziel 4 im Wesentlichen vom Rumpf 6 und dem IR-Dom 5 begrenzt ist. Das Heizelement 1 ist zweckmäßig in Flugrichtung (Pfeilrichtung) gesehen hinter dem IR-Dom 5 angeordnet. Fig. 2 shows a schematic representation of a section along the longitudinal axis of a flight destination according to the invention. In particular, in Fig. 2 the bug of the destination shown. The heating element 1 is arranged within the destination 4, wherein the destination 4 is essentially bounded by the fuselage 6 and the IR dome 5. The heating element 1 is expediently arranged in the direction of flight (arrow direction) behind the IR dome 5.

Es kann ein Trägerkörper 7 vorhanden sein, auf welchem das Heizelement 1 befestigt ist. Der Trägerkörper 7 weist zweckmäßig eine dem Heizelement 1 ähnliche Form auf. Der Trägerkörper 7 kann z.B. die Form eines Kegels, eines Kegelstumpfes, einer Pyramide, eines Pyramidenstumpfes oder einer Kugelschale aufweisen. Selbstverständlich kann der Trägerkörper 7 auch eine Form eines Doppelkegels, eines Doppelkegelstumpfes, einer Doppelpyramide oder eines Doppelpyramidenstumpfes aufweisen, wobei sich jeweils die Grundflächen der Kegel, Kegelsümpfe, Pyramiden oder Pyramidenstümpfe berühren. Dadurch wird eine IR-Abstrahlung in einen großen Raumwinkelbereich gewährleistet. Bekannte IR-Strahler emittieren IR-Strahlung im Wesentlichen nur in Flugrichtung bzw. können nur mit einem erheblichen baulichen Aufwand einen größeren Raumwinkelbereich ausleuchten.
Selbstverständlich ist es aber jede andere Form eines Trägerkörpers 7 möglich, bei welcher sich der Trägerkörper 7 zumindest teilweise von einem großen Durchmesser zu einem kleinen Durchmesser hin verjüngt.There may be a carrier body 7, on which the heating element 1 is attached. The carrier body 7 expediently has a shape similar to the heating element 1. The carrier body 7 may, for example, have the shape of a cone, a truncated cone, a pyramid, a truncated pyramid or a spherical shell. Of course, the carrier body 7 may also have a shape of a double cone, a double truncated cone, a double pyramid or a Doppelpyramidenstumpfes, each touching the base surfaces of the cones, cone bottoms, pyramids or truncated pyramids. This ensures IR radiation in a large solid angle range. Known IR emitters emit IR radiation substantially only in the direction of flight or can only illuminate a larger solid angle range with a considerable structural complexity.
Of course, however, it is possible any other shape of a support body 7, in which the support body 7 tapers at least partially from a large diameter to a small diameter.

Der IR-Dom 5 besteht vorteilhaft aus einem infrarotdurchlässigen Material, insbesondere aus Zinksulfid, Zinkselenid oder Magnesiumfluorid. Das infrarotdurchlässige Material wird zweckmäßig so gewählt, dass die Transmission von IR-Strahlung im Wellenlängenbereich von 3-5 µm und/oder 8-12 µm maximal ist. Der IR-Dom 5 ist zweckmäßig sphärisch, d.h. als Kugelschale ausgeführt. Dadurch wird eine optimale Aerodynamik des Flugziels erreicht.The IR dome 5 is advantageously made of an infrared-transparent material, in particular of zinc sulfide, zinc selenide or magnesium fluoride. The infrared-transparent material is expediently chosen so that the transmission of IR radiation in the wavelength range of 3-5 microns and / or 8-12 microns is maximum. The IR dome 5 is desirably spherical, i. designed as a spherical shell. This achieves optimum aerodynamics of the destination.

Der Übergang 8 zwischen dem IR-Dom 5 und dem Rumpf 6 ist zweckmäßig stetig ausgeführt. Dadurch wird gewährleistet, dass im Flugbetrieb des Flugziels keine Verwirbelungen an der Kontaktstelle 8 zwischen IR-Dom 5 und Rumpf 6 entstehen, wodurch der Luftwiderstand des Flugziels beeinträchtigt werden würde.
Der Übergang 8 befindet sich dabei, in Flugrichtung gesehen, auf gleicher Höhe zur Grundfläche G des Trägerkörpers 7. Selbstverständlich kann sich der Übergang 8 auch in Flugrichtung gesehen hinter der Grundfläche G des Trägerkörpers 2 befinden.
Für den Fall, dass das Heizelement 1 freitragend ist, d.h. es ist kein Trägerkörper vorhanden, kann sich der Übergang 8 in Flugrichtung gesehen hinter dem Heizdraht 1 befinden.The transition 8 between the IR dome 5 and the hull 6 is suitably carried out steadily. This ensures that in the flight operation of the destination no turbulence at the contact point 8 between IR dome 5 and hull 6 arise, whereby the air resistance of the destination would be affected.
The transition 8 is located, seen in the direction of flight, at the same height to the base G of the support body 7. Of course, the transition 8 seen in the direction of flight can be located behind the base G of the support body 2.
In the event that the heating element 1 is cantilevered, that is, there is no carrier body present, the transition 8 seen in the direction of flight can be located behind the heating wire 1.

Fig. 2 zeigt, dass das eine Ende 2 des Heizelements 1 parallel zur Symmetrieachse S des Trägerkörpers 7 geführt ist. Das andere Ende 3 ist am Rand des Trägerkörpers 7 geführt.
Zweckmäßig umfasst das Flugziel 4 ein System zur Temperaturregelung (nicht dargestellt). Das Regelungssystem kann dabei die Temperatur des Heizelements 1 kontinuierlich oder stufenweise verändern. Zweckmäßig erfolgt die Veränderung der Temperatur während des Fluges. Hierzu ist es möglich, dass das Flugziel 4 Mittel umfasst, welche die aktuelle Temperatur des Heizelements 1 an eine Bodenstation übermitteln können. Fig. 2 shows that the one end 2 of the heating element 1 is guided parallel to the axis of symmetry S of the carrier body 7. The other end 3 is guided on the edge of the carrier body 7.
Suitably, the destination 4 includes a system for temperature control (not shown). The control system can change the temperature of the heating element 1 continuously or stepwise. It is expedient to change the temperature during the flight. For this purpose, it is possible that the destination 4 comprises means which can transmit the current temperature of the heating element 1 to a ground station.

Das Heizelement 1 wird erfindungsgemäß elektrisch betrieben, wobei die Stromversorgung durch mitgeführte Generatoren oder Akkus erfolgt.The heating element 1 is electrically operated according to the invention, wherein the power is supplied by entrained generators or batteries.

Der Trägerkörper 7 ist zweckmäßig aus einem wärmeisolierenden Material mit einer hohen Temperaturbeständigkeit gefertigt, z.B. Keramik.The support body 7 is suitably made of a heat-insulating material having a high temperature resistance, e.g. Ceramics.

Das Heizelement 1 kann in einer ersten Ausführung direkt auf der Oberfläche des Trägerkörpers 7 aufgebracht sein, z.B. durch Löten, Schweißen oder Kleben. In einer zweiten Ausführungsform kann das Heizelement aber auch beabstandet an dem Trägerkörper angebracht sein, z.B. durch Abstandshalter (nicht dargestellt) zwischen der Oberfläche des Trägerkörpers und dem Heizelement.The heating element 1 may be applied in a first embodiment directly on the surface of the carrier body 7, e.g. by soldering, welding or gluing. In a second embodiment, however, the heating element may also be mounted at a distance from the carrier body, e.g. by spacers (not shown) between the surface of the carrier body and the heating element.

Der Trägerkörper 7 kann auf der Oberfläche in dem Bereich in welchem die Heizspirale 1 den Trägerkörper 7 bedeckt mit einer leitfähigen Schicht 9, z.B. eine Ag-Schicht beschichtet sein. Diese Schicht 9 reflektiert die von dem Heizelement 9 emittierte IR-Strahlung, wodurch die Ausbeute an in einen Raumwinkelbereich emittierter IR-Strahlung verbessert wird.The support body 7 may be provided on the surface in the area in which the heating coil 1 covers the support body 7 with a conductive layer 9, e.g. be coated on an Ag layer. This layer 9 reflects the IR radiation emitted by the heating element 9, whereby the yield of IR radiation emitted in a solid angle range is improved.

Das Heizelement 1 kann in Fig. 2 auch selbstverständlich ohne den Trägerkörper 7 mit einem Fachmann bekannten Maßnahmen am Rumpf des Flugziels 4 befestigt sein. In diesem Fall kann das beispielhafte Heizelement in Fig. 2 auch um 180° gedreht angeordnet sein, d.h. die Windung W_e mit der kleineren Fläche liegt in Flugrichtung gesehen hinter der Windung W_a mit der größeren Fläche.The heating element 1 can in Fig. 2 Of course, without the support body 7 with a person skilled in the known measures on the fuselage of the target 4 to be attached. In this case, the exemplary heating element in Fig. 2 Also be rotated by 180 °, ie the winding W_e with the smaller area is seen in the direction of flight behind the winding W_a with the larger area.

Claims (9)

  1. Airborne target having an electrically operated heating wire (1) for production of infrared radiation,
    characterized in that
    the heating wire (1) is wound with a plurality of turns W about an axis Z, with the winding running along the axis Z and with the area enclosed by the first turn W_a being greater than the area enclosed by the last turn W_e.
  2. Airborne target according to Claim 1, characterized in that the axis Z is aligned parallel to the longitudinal axis S of the airborne target (4).
  3. Airborne target according to Claim 1 or 2, characterized in that the heating wire (1) is fitted to a mount body (7).
  4. Airborne target according to Claim 3, characterized in that the mount body (7) is in the form of a cone, a truncated cone, a pyramid, a truncated pyramid or a spherical shell.
  5. Airborne target according to one of the preceding Claims 1-4, characterized in that the mount body (7) is a heat insulator.
  6. Airborne target according to one of the preceding Claims 3-5, characterized in that the mount body (7) is coated with a conductive layer (9).
  7. Airborne target according to one of the preceding Claims 1-6, characterized in that the heating element (1) is fitted behind an IR dome (5) composed of zinc sulphide, zinc selenide or magnesium fluoride.
  8. Airborne target according to Claim 7, characterized in that the IR dome (5) is in the form of a spherical shell.
  9. Airborne target according to Claim 7 or 8, characterized in that the transition (8) between the fuselage of the airborne target (4) and the IR dome (5) is continuous.
EP07011644A 2006-06-22 2007-06-14 Airborne target Active EP1870663B1 (en)

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DE102006028596A DE102006028596A1 (en) 2006-06-22 2006-06-22 destination

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EP1870663A2 EP1870663A2 (en) 2007-12-26
EP1870663A3 EP1870663A3 (en) 2008-05-28
EP1870663B1 true EP1870663B1 (en) 2009-07-29

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EP07011644A Active EP1870663B1 (en) 2006-06-22 2007-06-14 Airborne target

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CN115493459B (en) * 2022-11-21 2023-05-23 电光(北京)装备技术有限公司 Infrared target simulation externally hung nacelle device

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US3086202A (en) * 1956-10-22 1963-04-16 Del Mar Eng Lab Infrared emitting tow target
JPH02126100A (en) * 1988-11-07 1990-05-15 Mitsubishi Electric Corp Target
JP2865207B2 (en) * 1989-02-18 1999-03-08 松下電工株式会社 Hair dryer
DE4024263C1 (en) * 1990-07-31 1991-08-22 Messerschmitt-Boelkow-Blohm Gmbh, 8012 Ottobrunn, De IR heat radiator for location of self-propelled projectile - is positioned on tail of missile and has rotationally mounted shutter or shield in front of thermal radiator
GB9601207D0 (en) * 1996-01-22 1996-03-20 Target Technology Ltd Aerial target system
GB9722259D0 (en) 1997-10-22 1997-12-17 Global Target Systems Lltd Aerial target system
FR2785981B1 (en) 1998-11-13 2001-02-09 Pascal Doe SELF-PROPELLED REACTION INFRARED RADIATION TARGET
DE10210433C1 (en) * 2002-03-09 2003-08-14 Dornier Gmbh Unmanned airborne target, for ground-to-air or air-to-air weapons system uses IR radiator positioned in exhaust gas stream of heat generating unit

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DE102006028596A1 (en) 2007-12-27
EP1870663A2 (en) 2007-12-26
ATE438073T1 (en) 2009-08-15
EP1870663A3 (en) 2008-05-28
ES2328638T3 (en) 2009-11-16
DE502007001164D1 (en) 2009-09-10

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