EP1870663B1 - Flugziel - Google Patents

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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
Authority
EP
European Patent Office
Prior art keywords
axis
airborne target
heating wire
target according
winding
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.)
Active
Application number
EP07011644A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP1870663A3 (de
EP1870663A2 (de
Inventor
Bernt Dr. Obkircher
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.)
Airbus Defence and Space GmbH
Original Assignee
EADS Deutschland GmbH
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by EADS Deutschland GmbH filed Critical EADS Deutschland GmbH
Publication of EP1870663A2 publication Critical patent/EP1870663A2/de
Publication of EP1870663A3 publication Critical patent/EP1870663A3/de
Application granted granted Critical
Publication of EP1870663B1 publication Critical patent/EP1870663B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • 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

Definitions

  • 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.
  • unmanned aerial vehicles 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.
  • IR infrared
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • the diameter is the diagonal of the square.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • the largest possible length of the wound heating wire is achieved, whereby an effective IR radiation is ensured.
  • Fig. 2 shows a schematic representation of a section along the longitudinal axis of a flight destination according to the invention.
  • 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.
  • the carrier body 7 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.
  • 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.
  • 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.
  • 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.
  • 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 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.
  • 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.
  • the destination 4 comprises means which can transmit the current temperature of the heating element 1 to a ground station.
  • the heating element 1 is electrically operated according to the invention, wherein the power is supplied by entrained generators or batteries.
  • the support body 7 is suitably made of a heat-insulating material having a high temperature resistance, e.g. Ceramics.
  • 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.
  • 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.
  • the heating element 1 can in Fig. 2
  • 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.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Electromagnetism (AREA)
  • Optics & Photonics (AREA)
  • Remote Sensing (AREA)
  • Health & Medical Sciences (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Toxicology (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Resistance Heating (AREA)
  • Medicines That Contain Protein Lipid Enzymes And Other Medicines (AREA)
  • Transition And Organic Metals Composition Catalysts For Addition Polymerization (AREA)
  • Glass Compositions (AREA)
  • Seal Device For Vehicle (AREA)
EP07011644A 2006-06-22 2007-06-14 Flugziel Active EP1870663B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102006028596A DE102006028596A1 (de) 2006-06-22 2006-06-22 Flugziel

Publications (3)

Publication Number Publication Date
EP1870663A2 EP1870663A2 (de) 2007-12-26
EP1870663A3 EP1870663A3 (de) 2008-05-28
EP1870663B1 true EP1870663B1 (de) 2009-07-29

Family

ID=38477287

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07011644A Active EP1870663B1 (de) 2006-06-22 2007-06-14 Flugziel

Country Status (4)

Country Link
EP (1) EP1870663B1 (es)
AT (1) ATE438073T1 (es)
DE (2) DE102006028596A1 (es)
ES (1) ES2328638T3 (es)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN115493459B (zh) * 2022-11-21 2023-05-23 电光(北京)装备技术有限公司 一种红外目标模拟外挂吊舱装置

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3086202A (en) * 1956-10-22 1963-04-16 Del Mar Eng Lab Infrared emitting tow target
JPH02126100A (ja) * 1988-11-07 1990-05-15 Mitsubishi Electric Corp 標的
JP2865207B2 (ja) * 1989-02-18 1999-03-08 松下電工株式会社 毛髪乾燥器
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 (fr) 1998-11-13 2001-02-09 Pascal Doe Cible a rayonnements infrarouges autopropulsee par reaction
DE10210433C1 (de) * 2002-03-09 2003-08-14 Dornier Gmbh Fluggerät zur IR-Flugzieldarstellung

Also Published As

Publication number Publication date
EP1870663A3 (de) 2008-05-28
ES2328638T3 (es) 2009-11-16
EP1870663A2 (de) 2007-12-26
DE502007001164D1 (de) 2009-09-10
DE102006028596A1 (de) 2007-12-27
ATE438073T1 (de) 2009-08-15

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