WO2002048639A1 - Towed body for representing an airborne target - Google Patents

Towed body for representing an airborne target Download PDF

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Publication number
WO2002048639A1
WO2002048639A1 PCT/DE2001/004585 DE0104585W WO0248639A1 WO 2002048639 A1 WO2002048639 A1 WO 2002048639A1 DE 0104585 W DE0104585 W DE 0104585W WO 0248639 A1 WO0248639 A1 WO 0248639A1
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WO
WIPO (PCT)
Prior art keywords
infrared
flare
towed body
flares
tow body
Prior art date
Application number
PCT/DE2001/004585
Other languages
German (de)
French (fr)
Inventor
Rolf Kapp
Peter Weimer
Original Assignee
Dornier 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 Dornier Gmbh filed Critical Dornier Gmbh
Priority to EP01995580A priority Critical patent/EP1348102A1/en
Priority to US10/203,451 priority patent/US20040020396A1/en
Publication of WO2002048639A1 publication Critical patent/WO2002048639A1/en

Links

Classifications

    • 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
    • F42B4/00—Fireworks, i.e. pyrotechnic devices for amusement, display, illumination or signal purposes
    • F42B4/26—Flares; Torches

Definitions

  • the invention relates to a towed body for displaying flight targets according to the preamble of patent claim 1.
  • infrared flares also called infrared tracking flares
  • IR flares are available in a wide range of effects on the market and can be firmly attached to the rear area of the towed body.
  • the target imaging means (towed body) is usually lost with each use.
  • a towed body is disclosed in DE 198 14 936 C1, in which the infrared flares are not permanently installed at the rear of the towed body, but can be deployed by the towed body and by means of a detachable tow rope during the Burning time of the infrared flare can be pulled by the towed body.
  • a height control for a towed body is known from DE 26 13 953 B2, wherein several identical, synchronously adjustable resistance bodies, which are distributed over the circumference of the towed body, are provided.
  • the object of the invention is to provide the lightest possible, effective, geometrically small, high-temperature-resistant stabilization device for the IR tracking flare with simultaneous channeling of the flow surrounding the flare burnup.
  • the IR flair has a ring wing at the rear. This advantageously consists of the thinnest, high-temperature-resistant steel sheet.
  • the suspension of the ring wing is realized in the form of two bent molded parts, wherein individual surfaces of the bent molded part are simultaneously designed and effective as additional tail units.
  • the entire stabilization unit consists of only three components, which enables inexpensive series production.
  • the above-mentioned special requirements regarding burn-off during towed operations can be fully met.
  • the IR flare designed in accordance with the invention shows, in particular, optimal burn-off behavior in the aerodynamic dead water behind the stabilizing cone. Further advantages of the invention result from the following exemplary embodiments, which are explained in more detail with reference to figures. 1 shows the execution of an IR flare according to the invention in two different ways
  • FIG. 2 shows the execution of a stabilization unit from the ring wing and its
  • FIG. 3 shows the execution of a further stabilization unit from the ring wing and its suspension in two different representations.
  • the IR flare 3 shows an embodiment of the IR flare according to the invention in a view from the front (left) and a sectional drawing (right), the section plane running through the longitudinal axis of the cylindrical IR flare 3.
  • the IR flare 3 has an annular wing 1 according to the invention, which is arranged concentrically to the longitudinal axis of the IR flare 3.
  • the ring wing 1 is made of thin (e.g. 0.5 mm), high temperature resistant steel sheet.
  • the suspension of the ring wing 1 is realized by means of two identical bent molded parts 2 (FIG. 2) which are welded to the ring wing, preferably laser-welded (position 20) and to which the IR flare 3 is fastened by means of a clamp 5. Partial surfaces of the bent molded parts 2 are designed and effective as additional tail units (fins 10) (in the sectional drawings on the right in FIGS. 1, 2 and 3, the fins 10 are rotated into the plane of the illustration).
  • a bent molded part 2 as a suspension of the ring wing thus comprises three surfaces: two fins 10 and an intermediate piece which follows the cylindrical contour of the IR flare 3.
  • the fins At their lower edge, the fins have cutouts 8 for the ejection and ignition unit (not shown) of the IR flare 3.
  • the ejection and ignition unit (not shown) of the IR flare 3.
  • Fig. 3 shows a further embodiment of the stabilization unit from ring wing and ring wing suspension in two different representations.
  • optional measures for increasing the resistance are shown here. provides the optimization of towing and burning behavior.
  • a transverse web 31 can be present on the rear edge of the ring wing (right illustration, top), which is produced in the embodiment shown in that the rear edge is flanged inwards or outwards.

Abstract

The invention relates to a towed body for representing an airborne target. The towed body comprises infrared flares (3) situated at the rear thereof, whereby the infrared flares can be ejected from the towed body and are towed during the burning duration of the infrared flare by the towed body by means of a towing cable that can unreel. According to the invention, the infrared flares (3) have an annular wing (1) situated at the rear.

Description

Schleppkörper zur FlugzieldarstellungTow body for flight target display
Die Erfindung betrifft einen Schleppkörper zur Flugzieldarstellung nach dem Oberbegriff des Patentanspruchs 1.The invention relates to a towed body for displaying flight targets according to the preamble of patent claim 1.
In der bemannten Flugzieldarstellung werden seit längerer Zeit Schleppkörper mit Infrarotbrennern (Infrarot-Flares, auch Infrarot-Tracking-Flares genannt) ausgerüstet und für Training und Beschuss mit Lenkwaffen eingesetzt, welche mit IR-Suchköpfen bestückt sind. Diese IR-Flares sind in einem breiten Wirkungsspektrum auf dem Markt erhältlich und können fest am Heckbereich des Schleppkörpers befestigt sein.In the manned flight target display, towed bodies have been equipped with infrared burners (infrared flares, also called infrared tracking flares) for a long time and used for training and shelling with guided missiles equipped with IR seekers. These IR flares are available in a wide range of effects on the market and can be firmly attached to the rear area of the towed body.
Da die Trefferwahrscheinlichkeit der Lenkwaffen sehr hoch ist, geht in der Regel bei jedem Einsatz das Zieldarstellungsmittel (Schleppkörper) verloren.Since the missile's probability of being hit is very high, the target imaging means (towed body) is usually lost with each use.
Um die Wiederverwendbarkeit des Schleppkörpers sicherzustellen, ist in der DE 198 14 936 C1 ein Schleppkörper offenbart, bei dem die Infrarot-Flares nicht fest am Heck des Schleppkörpers installiert sind, sondern von dem Schleppkörper ausge- bracht werden können und mittels eines abspulbaren Schleppseils während der Brenndauer des Infrarot-Flares vom Schleppkörper gezogen werden.In order to ensure the reusability of the towed body, a towed body is disclosed in DE 198 14 936 C1, in which the infrared flares are not permanently installed at the rear of the towed body, but can be deployed by the towed body and by means of a detachable tow rope during the Burning time of the infrared flare can be pulled by the towed body.
Die sichere Ausbringung und Stabilisierung des üblicherweise zylindrischen IR- Trackingflares kann nur mit Hilfe zusätzlicher Anbringung von stabilisierenden Elementen am geschleppten Flare realisiert werden. Ohne diese Maßnahmen treten vollkommen instabile Flugzustände der Trackingflares auf, so dass eine sichere Auffassung durch die Waffensysteme nicht gewährleistet werden kann. Eine spezielle Problematik beim Einsatz von stabilisierenden Zusatzelementen an einem brennenden IR-Trackingflare stellt die starke Gaserzeugung sowie die Notwendigkeit eines sauberen Abbrands im sogenannten aerodynamischen Totwasser dar.The safe delivery and stabilization of the usually cylindrical IR tracking flare can only be achieved with the additional attachment of stabilizing elements to the towed flare. Without these measures, completely unstable flight conditions of the tracking flares occur, so that a safe view cannot be guaranteed by the weapon systems. A particular problem when using stabilizing additional elements on a burning IR tracking flare is the strong gas generation and the need for clean combustion in the so-called aerodynamic dead water.
Von der Anmelderin durchgeführte Flugversuche mit einem dem Stand der Technik entsprechenden, am Heck des IR-Trackingflares angebrachten Stabilisierungskonus zeigten sich hier insbesondere während des Abbrandes des Flares stark instabile Flugzustände (Fassrollen etc.). Die durchgeführten Untersuchungen und Auswertungen zeigten, dass durch den Abbrand des IR-Trackingflares der für die Stabilisierung notwendige Unterdruck hinter dem Heckkonus neutralisiert wird. Dadurch ergab sich das beobachtete instabile Schleppverhalten.Flight tests carried out by the applicant with a state-of-the-art stabilizing cone attached to the rear of the IR tracking flare Here, particularly unstable flight conditions (barrel rolls etc.) were shown, especially during the burning of the flares. The investigations and evaluations carried out showed that the burning of the IR tracking flare neutralizes the negative pressure behind the rear cone, which is necessary for stabilization. This resulted in the observed unstable towing behavior.
Aus der DE 26 13 953 B2 ist eine Höhensteuerung für einen Schleppkörper bekannt, wobei mehrere gleiche, über den Umfang des Schleppkörpers verteilt angeordnete, synchron verstellbare Widerstandkörper vorgesehen sind.A height control for a towed body is known from DE 26 13 953 B2, wherein several identical, synchronously adjustable resistance bodies, which are distributed over the circumference of the towed body, are provided.
Aufgabe der Erfindung ist es, eine möglichst leichte, effektiven, geometrisch kleine, hochtemperaturfeste Stabilisierungseinrichtung für den IR-Trackingflare bei gleichzeitiger Kanalisierung der den Flareabbrand umgebenden Strömung zu schaffen.The object of the invention is to provide the lightest possible, effective, geometrically small, high-temperature-resistant stabilization device for the IR tracking flare with simultaneous channeling of the flow surrounding the flare burnup.
Diese Aufgabe wird mit dem Gegenstand des Patentanspruchs 1 gelöst. Vorteilhafte Ausführungen sind Gegenstand weiterer Ansprüche.This object is achieved with the subject matter of patent claim 1. Advantageous designs are the subject of further claims.
Erfindungsgemäß weist der IR-Flair am Heck einen Ringflügel auf. Dieser besteht vorteilhaft aus dünnstem, hochtemperaturfesten Stahlblech.According to the invention, the IR flair has a ring wing at the rear. This advantageously consists of the thinnest, high-temperature-resistant steel sheet.
Die Aufhängung des Ringflügels wird in Form von zwei Biegeformteilen realisiert, wobei einzelne Flächen des Biegeformteiles gleichzeitig als Zusatzleitwerke ausgebildet und wirksam sind.The suspension of the ring wing is realized in the form of two bent molded parts, wherein individual surfaces of the bent molded part are simultaneously designed and effective as additional tail units.
Somit besteht die gesamte Stabilisierungseinheit aus nur drei Bauteilen, wodurch eine kostengünstigen Serienfertigung ermöglicht wird.Thus, the entire stabilization unit consists of only three components, which enables inexpensive series production.
Mit der Erfindung wird eine sichere Ausbringung und Stabilisierung des IR- Trackingflares erreicht.With the invention, a safe deployment and stabilization of the IR tracking flare is achieved.
Den obengenannten speziellen Anforderungen bezüglich des Abbrandes während des geschleppten Einsatzes kann voll entsprochen werden. Der erfindungsgemäß ausgestaltete IR-Flare zeigt insbesondere ein optimales Abbrandverhalten in dem aerodynamischen Totwasser hinter dem Stabilisierungskonus. Weitere Vorteile der Erfindung ergeben sich aus den folgenden Ausführungsbeispielen, die unter Bezugnahme auf Figuren näher erläutert werden. Es zeigen: Fig. 1 die Ausführung eines erfindungsgemäßen IR-Flares in zwei verschiedenenThe above-mentioned special requirements regarding burn-off during towed operations can be fully met. The IR flare designed in accordance with the invention shows, in particular, optimal burn-off behavior in the aerodynamic dead water behind the stabilizing cone. Further advantages of the invention result from the following exemplary embodiments, which are explained in more detail with reference to figures. 1 shows the execution of an IR flare according to the invention in two different ways
Darstellungen; Fig. 2 die Ausführung einer Stabilisierungseinheit aus Ringflügel und dessenrepresentations; Fig. 2 shows the execution of a stabilization unit from the ring wing and its
Aufhängung in zwei verschiedenen Darstellungen; Fig. 3 die Ausführung einer weiteren Stabilisierungseinheit aus Ringflügel und dessen Aufhängung in zwei verschiedenen Darstellungen.Suspension in two different representations; Fig. 3 shows the execution of a further stabilization unit from the ring wing and its suspension in two different representations.
Fig. 1 zeigt eine Ausführung des erfindungsgemäßen IR-Flares in einer Ansicht von vorne (links), sowie eine Schnittzeichnung (rechts), wobei die Schnittebene durch die Längsachse des zylindrischen IR-Flares 3 verläuft. Der IR-Flare 3 weist an seinem Heck einen erfindungsgemäßen Ringflügel 1 auf, der konzentrisch zur Längsachse des IR-Flares 3 angeordnet ist. Der Ringflügel 1 ist aus dünnem (z.B. 0,5mm), hochtemperaturfesten Stahlblech hergestellt.1 shows an embodiment of the IR flare according to the invention in a view from the front (left) and a sectional drawing (right), the section plane running through the longitudinal axis of the cylindrical IR flare 3. At its rear, the IR flare 3 has an annular wing 1 according to the invention, which is arranged concentrically to the longitudinal axis of the IR flare 3. The ring wing 1 is made of thin (e.g. 0.5 mm), high temperature resistant steel sheet.
Die Aufhängung des Ringflügels 1 wird mittels zweier identischer Biegeformteile 2 (Fig. 2) realisiert, die am Ringflügel angeschweißt, bevorzugt lasergeschweißt sind (Position 20) und an dem IR-Flare 3 mittels einer Klammer 5 befestigt sind. Teilflächen der Biegeformteile 2 sind als Zusatzleitwerke (Fins 10) ausgebildet und wirksam (In den Schnittzeichnungen jeweils rechts in Fig. 1 , 2 und 3 sind die Fins 10 in die Darstellungsebene gedreht). Ein Biegeformteil 2 als Aufhängung des Ringflügles umfasst somit drei Flächen: zwei Fins 10 sowie ein Zwischenstück, das der zylindri- sehen Kontur des IR-Flares 3 folgt.The suspension of the ring wing 1 is realized by means of two identical bent molded parts 2 (FIG. 2) which are welded to the ring wing, preferably laser-welded (position 20) and to which the IR flare 3 is fastened by means of a clamp 5. Partial surfaces of the bent molded parts 2 are designed and effective as additional tail units (fins 10) (in the sectional drawings on the right in FIGS. 1, 2 and 3, the fins 10 are rotated into the plane of the illustration). A bent molded part 2 as a suspension of the ring wing thus comprises three surfaces: two fins 10 and an intermediate piece which follows the cylindrical contour of the IR flare 3.
Die Fins weisen an ihrem unteren Rand Freischnitte 8 für die (nicht dargestellte) Ausstoß- und Anzündeinheit des IR-Flares 3 auf. Durch diese Leitwerksfreischnitte sowie die relativ weit vorne liegende Anbindung des Ringflügels 1 mittels der Klammer 5 kann die notwendige Zugänglichkeit zu der pyrotechnischen Ausstoß - und Anzündeinheit gewährleistet werden.At their lower edge, the fins have cutouts 8 for the ejection and ignition unit (not shown) of the IR flare 3. By means of these tailplane free cuts and the relatively far forward connection of the ring wing 1 by means of the clamp 5, the necessary accessibility to the pyrotechnic ejection and ignition unit can be guaranteed.
Fig. 3 zeigt eine weitere Ausführung der Stabilisierungseinheit aus Ringflügel und Ringflügelaufhängung in zwei verschiedenen Darstellungen. Gegenüber der Ausführung nach Fig. 2 sind hier optionale Maßnahmen zur Widerstandserhöhung darge- stellt, die der Optimierung des Schlepp- und Abbrandverhaltens dienen. Dazu ist (rechte Darstellung, unten) an der Hinterkante des Ringflügels eine keilförmige Aufdickung 30 vorhanden. Alternativ kann an der Hinterkante des Ringflügels ein Quersteg 31 vorhanden sein (rechte Darstellung, oben), der in der gezeigten Ausführung dadurch hergestellt wird, dass die Hinterkante nach innen oder außen umgebördelt ist. Selbstverständlich ist in der Realität an demselben Ringflügel nur eine Art der Widerstandserhöhung vorhanden. Fig. 3 shows a further embodiment of the stabilization unit from ring wing and ring wing suspension in two different representations. Compared to the embodiment according to FIG. 2, optional measures for increasing the resistance are shown here. provides the optimization of towing and burning behavior. For this purpose (right illustration, below) there is a wedge-shaped thickening 30 on the rear edge of the ring wing. Alternatively, a transverse web 31 can be present on the rear edge of the ring wing (right illustration, top), which is produced in the embodiment shown in that the rear edge is flanged inwards or outwards. Of course, in reality there is only one type of resistance increase on the same ring wing.

Claims

Patentansprüche: claims:
1. Schleppkörper zur Flugzieldarstellung, mit an seinem Heck befindlichen Infrarot- Flares (3), wobei die Infrarot-Flares von dem Schleppkörper ausgebracht werden können und mittels eines abspulbaren Schleppseils während der Brenndauer des1. Tow body for flight target display, with infrared flares (3) located at its rear, the infrared flares being able to be deployed by the tow body and by means of a reelable tow rope during the burning time of the
Infrarot-Flares vom Schleppkörper gezogen werden, dadurch gekennzeichnet, dass die Infrarot-Flares (3) am Heck einen Ringflügel (1) aufweisen.Infrared flares are pulled from the tow body, characterized in that the infrared flares (3) have an annular wing (1) at the rear.
2. Schleppkörper nach Anspruch 1 , dadurch gekennzeichnet, dass die Aufhängung des Ringflügels (1) in Form zweier Biegeformteile (2) realisiert ist, wobei Teilflächen der Biegeformteile gleichzeitig als Zusatzleitwerke (10) ausgebildet und wirksam sind.2. Tow body according to claim 1, characterized in that the suspension of the ring wing (1) is realized in the form of two bent mold parts (2), partial surfaces of the bent mold parts being simultaneously designed and effective as additional tail units (10).
3. Schleppkörper nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass der Ringflügel (1) mittels einer Klammer (5) am Infrarot-Flare (3) befestigt ist.3. Tow body according to claim 1 or 2, characterized in that the ring wing (1) by means of a bracket (5) on the infrared flare (3) is attached.
4. Schleppkörper nach einem der vorangehenden Ansprüche, dadurch gekennzeichnet, dass am hinteren Rand des Rundflügels (1) eine keilförmige Aufdik- kung (30) oder ein Quersteg (31) vorhanden ist. 4. Tow body according to one of the preceding claims, characterized in that a wedge-shaped thickening (30) or a transverse web (31) is present at the rear edge of the round wing (1).
PCT/DE2001/004585 2000-12-12 2001-12-06 Towed body for representing an airborne target WO2002048639A1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP01995580A EP1348102A1 (en) 2000-12-12 2001-12-06 Towed body for representing an airborne target
US10/203,451 US20040020396A1 (en) 2000-12-12 2001-12-06 Towed body for representing a flying target

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10061772.7 2000-12-12
DE10061772A DE10061772C1 (en) 2000-12-12 2000-12-12 Towed body representing airborne target has IR flare provided with vane ring for flight stabilisation

Publications (1)

Publication Number Publication Date
WO2002048639A1 true WO2002048639A1 (en) 2002-06-20

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PCT/DE2001/004585 WO2002048639A1 (en) 2000-12-12 2001-12-06 Towed body for representing an airborne target

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US (1) US20040020396A1 (en)
EP (1) EP1348102A1 (en)
DE (1) DE10061772C1 (en)
WO (1) WO2002048639A1 (en)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2010099228A1 (en) 2009-02-24 2010-09-02 Blue Origin, Llc Bidirectional control surfaces for use with high speed vehicles, and associated systems and methods
CN102589360A (en) * 2012-04-06 2012-07-18 浏阳市余氏科技环保烟花厂 Character pattern directed aerial shell
CN103115529B (en) * 2013-03-13 2015-02-25 长沙职业技术学院 Three-dimensional directional launching device for display shell
US9487308B2 (en) * 2013-03-15 2016-11-08 Blue Origin, Llc Launch vehicles with ring-shaped external elements, and associated systems and methods
US10822122B2 (en) 2016-12-28 2020-11-03 Blue Origin, Llc Vertical landing systems for space vehicles and associated methods

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2613953A1 (en) * 1976-04-01 1977-10-13 Dornier Gmbh Aircraft simulation control system - manoeuvres towed target from neutral altitude position according to adjusted air resistance profile of target
GB2034267A (en) * 1978-11-18 1980-06-04 Dornier Gmbh Device for Towing by an Aircraft
US4607849A (en) * 1985-03-07 1986-08-26 Southwest Aerospace Corporation Jet exhaust simulator
EP0768508A2 (en) * 1995-10-13 1997-04-16 Gec-Marconi Limited Drag-producing aerodynamic device
EP0947799A1 (en) * 1998-04-03 1999-10-06 DORNIER GmbH Artificial towed target with IR-flare

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2613953A1 (en) * 1976-04-01 1977-10-13 Dornier Gmbh Aircraft simulation control system - manoeuvres towed target from neutral altitude position according to adjusted air resistance profile of target
GB2034267A (en) * 1978-11-18 1980-06-04 Dornier Gmbh Device for Towing by an Aircraft
US4607849A (en) * 1985-03-07 1986-08-26 Southwest Aerospace Corporation Jet exhaust simulator
EP0768508A2 (en) * 1995-10-13 1997-04-16 Gec-Marconi Limited Drag-producing aerodynamic device
EP0947799A1 (en) * 1998-04-03 1999-10-06 DORNIER GmbH Artificial towed target with IR-flare

Also Published As

Publication number Publication date
US20040020396A1 (en) 2004-02-05
EP1348102A1 (en) 2003-10-01
DE10061772C1 (en) 2002-05-08

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