EP0860682A1 - Device for the optical marking of the trajectory of missiles propelled by thrusters - Google Patents

Device for the optical marking of the trajectory of missiles propelled by thrusters Download PDF

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Publication number
EP0860682A1
EP0860682A1 EP97204141A EP97204141A EP0860682A1 EP 0860682 A1 EP0860682 A1 EP 0860682A1 EP 97204141 A EP97204141 A EP 97204141A EP 97204141 A EP97204141 A EP 97204141A EP 0860682 A1 EP0860682 A1 EP 0860682A1
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EP
European Patent Office
Prior art keywords
smoke
engine
hollow cylinder
rocket
missile
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.)
Granted
Application number
EP97204141A
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German (de)
French (fr)
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EP0860682B1 (en
Inventor
Josef Bissig
Rolf Oechslin
Walter Rauber
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RUAG Munition
Original Assignee
Schweizerische Eidgenossenschaft Vertreten Durch Die Sm Schweizerische Munitionsunternehmung Der Gruppe fur Ruestungsdienste
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Publication of EP0860682A1 publication Critical patent/EP0860682A1/en
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Publication of EP0860682B1 publication Critical patent/EP0860682B1/en
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    • 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

Definitions

  • the invention relates to a device for generating an optical marking of the trajectory one by one Accelerated missile engine, especially a rocket, which device is assigned to the engine, and the emerging gas jet and / or the outflowing air visible smoke and / or vapor particles are added.
  • the trajectory of rockets or aircraft is known to measure and record optical target tracking devices.
  • Avoidance maneuvers can also be practiced by pilots, if you launch practice rockets early and safely can recognize.
  • system security of the entire missile may through this additional unit, even under extreme operating conditions, not be endangered.
  • This object is achieved by attaching a nozzle to the nozzle Engine a smoke and / or steam unit connected which is activated by the gas jet of the engine, or is ignited.
  • a heat-sensitive film according to claim has proven itself 2 melted by the hot exhaust gases from the engine and / or is ignited and the penetration of the gases into the Allows smoking unit.
  • a diffuser surface according to claim 3 is advantageous because it is streamlined and also a coaxial smoke distribution favored.
  • the band mentioned in claim 6 facilitates the assembly of the Cones and is also aerodynamic.
  • a convex design is also flow-favorable the inlet, cf. Claim 7. She also heads the hot ones Gases of the engine towards the heat sensitive foil and accelerates their ignition.
  • a smoke set according to claim 8 is favorable.
  • the pyrotechnic mixture according to claim 9 has proven to be proven optimal.
  • 1, 1 is the outer ring of a hollow cylinder referred to, inside which there is a sieve tube 2, which has a plurality of cylindrical bores 5.
  • a sieve tube 2 which has a plurality of cylindrical bores 5.
  • the Outer ring 1 and the sieve tube 2 are in a known manner firmly connected by rivets 3.
  • the outer ring 1 there is a filling opening 4 which the filling of a smoke set in the between parts 1 and 2 formed cavity, the combustion chamber 6, is used.
  • the combustion chamber 6, in which smoke is generated, has a conical diffuser surface 7 on the rear.
  • the smoke unit according to FIG. 1 is in the housing 16 of a practice rocket R inserted.
  • the outer ring 1 in Inside of the housing 16, is with an adapter flange 10 a notoriously known thruster 12 of an engine 11 mechanically connected.
  • the engine 11 is a solids booster.
  • the rear part 15 is analogous to a conventional missile educated.
  • the diffuser surface 7 has a larger opening angle on as the conical part of the nozzle bore 7 'in one Thruster 12.
  • the holes 5 are through a easily inflammable film 8 covered.
  • the operation of the device is extremely simple and thus of the highest operational reliability: Will the rocket engine 11 ignited in the usual way, hot gases are produced, which meet the film 8 via the nozzle bore 7 ' and light it. At the same time it is in the combustion chamber 6 smoke set located 9 ignited; the flue gases are with of the outflowing air and are, in the present Fall over the entire trajectory of the practice rocket R available and form a corresponding tail that the trajectory the missile R indicates.
  • Stinger surface-to-air missile In the previously described and tested embodiment is a Stinger surface-to-air missile (see brochure 01-710A, undated, the BC BRUNSWICK CORPORATION, Defense Division, 3333 Harbor Boulevard., Costa Mesa, CA 92626 USA: STINGER Weapon System Training STLS, or STINGER Launch Simulator STLS).
  • This missile has a start engine, which the rocket to a minimum necessary for launch Accelerated speed of 30 m / s. After leaving of the launch tube is the thrust phase of the starting engine ended, therefore no flue gases are produced.
  • This practice rocket R has no cruise engine.
  • the smoke set 9 used is based on a pyrotechnic Mixture of 22% zinc oxide, 18% polyvinyl chloride, a reaction mixture from 22% zinc diamine chloride, 36% ammonium perchlorate and 2% collodion wool E220.
  • the powder smoke set is in the usual way using a vibrator when filling in the Combustion chamber 6 compressed.
  • the outer ring 1 and the sieve tube 2 are made of commercially available Chrome / nickel steel manufactured.
  • the rivets 3, Fig.1, are out an aluminum alloy and one not shown here Covering the filling opening 4 from a commercially available Aluminum foil with a conductive surface (Scotch tape # 1170, according to MIL-A-46050; Trademark of the 3M company Minnesota, USA).
  • the heat sensitive film 8 is a also commercially available aluminum tape (COROPLAST # 919, aluminum-steamed; Permapack AG, CH-9401 Rorschach).
  • This sieve tube 2 is designed in one piece and has in its cylindrical tubular part bores 5, which are identical are with those according to Fig. 1.
  • the screen tube 2 according to FIG. 3 each has an external thread 17 and in its diffuser surface 7 also bores 18, which are here but run axially.
  • Embodiment 5 is the preferred one Embodiment shown as a whole.
  • the adapter flange 10 After lining the cylindrical jacket of the sieve tube 2 by means of the heat-sensitive film 8, the adapter flange 10 with its end face 10 'by four fastening screws 3 'on the thrust nozzle 12 of the rocket motor 11, see. Fig. 2 screwed. These screws 3 'find one annular recess 22 place.
  • the outer ring 1 is from the left side pushed over the sieve tube 2 and on whose external thread 17, screwed to the rear. Here lies the flange portion 1 'of the outer ring 1 close to the flange portion 2 'of the sieve tube 2.
  • FIG. 4 The more precise design of the annular band 19 with its The locking pin 20 cast onto the band is shown in FIG. 4 refer to.
  • Polyurethane has proven itself as a material for this, which is in a die casting process ("spraying") easily manufactured in one piece.
  • the outer ring 1 and the sieve tube 2 here made of a high-strength aluminum alloy (Trademark Perunal 215 from Alusuisse AG, Switzerland; Material according to DIN 3.4365; Description USA: 7075 - T6).
  • This Aluminum alloy results in comparison to that previously described Variant a weight saving and can be more economical produce.
  • modified compared to FIG. 2 is based on the form fit of the No smoking unit, so that this is optional - are inserted and screwed into the practice rocket R. can.
  • Tracking missile launches makes it easier for ground personnel the necessary practice of the shooting manipulations. In pilots can also practice evasive maneuvers, when they see the missile’s trajectory from their perspective can. In an emergency, i.e. if a missile with war ammunition is shot down, the pilot already suffices the rocket engine or its booster produced smoke around you Shot not only to recognize, but also about him and him initiate evasive maneuvers to save the aircraft; is the flight dynamics of a conventional ground / air rocket very limited for technical reasons.
  • the subject of the invention is not based on that Limited embodiment, it can be in analog Adapt it to other engines, afterburner and the like.

Abstract

In a device for optically tracing the trajectory of a powered flying body, especially a rocket, by mixing visible smoke and/or vapour particles with the emitted gas jet and/or passing air, a smoke and/or vapour unit is connected to the rocket nozzle and is activated or ignited by the rocket exhaust. Preferably, the smoke unit is in the form of a hollow cylinder (1, 2) containing a pyrotechnic mixture (9) of 22% zinc oxide, 18% polyvinyl chloride, a reaction mixture of 22% y chloride, 36% ammonium perchlorate and 2% collodion cotton.

Description

Die Erfindung bezieht sich auf eine Vorrichtung zur Erzeugung einer optischen Markierung der Flugbahn eines durch ein Triebwerk beschleunigten Flugkörpers, insbesondere einer Rakete, welche Vorrichtung dem Triebwerk zugeordnet ist, und die dem austretenden Gasstrahl und/oder der abströmenden Luft sichtbare Rauch- und/oder Dampfpartikel beimengt.The invention relates to a device for generating an optical marking of the trajectory one by one Accelerated missile engine, especially a rocket, which device is assigned to the engine, and the emerging gas jet and / or the outflowing air visible smoke and / or vapor particles are added.

Es ist bekannt die Flugbahn von Raketen oder Flugzeugen mit optischen Zielfolgegeräten zu vermessen und aufzuzeichnen.The trajectory of rockets or aircraft is known to measure and record optical target tracking devices.

Im Zusammenhang mit der Ausbildung von Personal zur Bedienung von Boden/Luft-Raketen, Boden/Boden-Raketen und Luft/Boden-Raketen ist es jedoch hilfreich, wenn die Flugbahn der Rakete, zumindest in ihrem Startbereich, optisch sichtbar ist.In connection with the training of operating personnel of surface-to-air missiles, surface-to-surface missiles and air-to-surface missiles it’s helpful if the missile’s trajectory, at least in their start area, is visually visible.

Ebenfalls können von Piloten Ausweichmanöver geübt werden, wenn Sie den Start von Übungsraketen frühzeitig und sicher erkennen können.Avoidance maneuvers can also be practiced by pilots, if you launch practice rockets early and safely can recognize.

Es ist daher Aufgabe der vorliegenden Erfindung eine Vorrichtung zu schaffen, welche als Einheit einem Triebwerk zugeordnet werden kann und die die Schubleistung des Motors nicht oder nur unmerklich beeinträchtigt und keinen Einfluss auf das Steuerungsverhalten des Flugkörpers hat.It is therefore an object of the present invention to provide a device to create which as a unit assigned to an engine and the engine's thrust cannot or only slightly affected and does not affect has the control behavior of the missile.

Zudem darf die Systemsicherheit des gesamten Flugkörpers durch diese zusätzliche Einheit, auch bei extremen Betriebsbedingungen, nicht gefährdet werden.In addition, the system security of the entire missile may through this additional unit, even under extreme operating conditions, not be endangered.

Diese Aufgabe wird dadurch gelöst, dass an die Düse eines Triebwerks eine Rauch- und/oder Dampfeinheit angeschlossen wird, welche durch den Gasstrahl des Triebwerks aktiviert, bzw. gezündet wird.This object is achieved by attaching a nozzle to the nozzle Engine a smoke and / or steam unit connected which is activated by the gas jet of the engine, or is ignited.

In nachfolgend abhängigen Ansprüchen sind vorteilhafte Weiterbildungen des Erfindungsgegenstands beschrieben.Advantageous further developments are in the dependent claims below described the subject of the invention.

Bewährt hat sich eine hitzeempfindliche Folie nach Anspruch 2, die durch die heissen Abgase des Triebwerks geschmolzen und/oder gezündet wird und das Eindringen der Gase in die Raucheinheit ermöglicht.A heat-sensitive film according to claim has proven itself 2 melted by the hot exhaust gases from the engine and / or is ignited and the penetration of the gases into the Allows smoking unit.

Vorteilhaft ist eine Diffusor-Fläche nach Anspruch 3, da sie strömungsgünstig ist und auch eine koaxiale Rauchverteilung begünstigt.A diffuser surface according to claim 3 is advantageous because it is streamlined and also a coaxial smoke distribution favored.

Durch den Einbezug von Bohrungen in die Diffusor-Fläche, Anspruch 4, können Überdrucke in der Raucheinheit abgebaut werden und Funktionsstörungen, insbesondere bei höheren Temperaturen verhindert werden.By including holes in the diffuser surface, claim 4, overpressures can be reduced in the smoke unit and malfunctions, especially at higher temperatures be prevented.

Günstig sind Verschlusszapfen nach Anspruch 5, welche in einfachster Weise Überdrucke abbauen können, in dem sie aus den Bohrungen geschoben werden.Favorable are locking pins according to claim 5, which in simplest Can reduce overpressures by removing them from the Holes are pushed.

Das in Anspruch 6 erwähnte Band erleichtert die Montage der Zapfen und ist zudem strömungsgünstig.The band mentioned in claim 6 facilitates the assembly of the Cones and is also aerodynamic.

Ebenfalls strömungsgünstig ist eine bombierte Ausgestaltung des Einlasses, vgl. Anspruch 7. Sie leitet zudem die heissen Gase des Triebwerks in Richtung hitzeempfindliche Folie und beschleunigt deren Entzünden.A convex design is also flow-favorable the inlet, cf. Claim 7. She also heads the hot ones Gases of the engine towards the heat sensitive foil and accelerates their ignition.

Günstig ist ein Rauchsatz gemäss Anspruch 8.A smoke set according to claim 8 is favorable.

Die pyrotechnische Mischung gemäss Anspruch 9 hat sich als optimal erwiesen. The pyrotechnic mixture according to claim 9 has proven to be proven optimal.

Alternativ lässt sich die Konstruktion einer Raucheinheit auch auf eine Dampfeinheit übertragen, wobei die Druckerzeugung in den wasserführenden Leitungen leicht durch den Staudruck der Rakete erzeugbar ist und die Initiierung der Dampfbildung durch das Abschmelzen und/oder -brennen der Verschlussstücke oder Sicherungen, Anspruch 10, erfolgt.Alternatively, the construction of a smoke unit also transferred to a steam unit, whereby the pressure generation in the water-carrying pipes easily due to the dynamic pressure the rocket can be generated and the initiation of vapor formation by melting and / or burning the closure pieces or fuses, claim 10.

Anhand von praktischen Ausführungsbeispielen wird nachfolgend der Erfindungsgegenstand näher dargestellt.Based on practical examples, the following the subject of the invention shown in more detail.

Es zeigen:

Fig. 1
eine funktionsfähige Raucheinheit in Schnittdarstellung, ohne Füllung und innere Abdeckung,
Fig. 2
die Raucheinheit Fig. 1 eingebaut in eine Übungsrakete in betriebsbereitem Zustand,
Fig. 3
ein einstückiges Siebrohr einer weiterentwickelten Raucheinheit, einer Variante zu Fig. 1, mit axialen Bohrungen in deren Diffusor-Fläche,
Fig. 4
ein Band mit Verschlusspfropfen zum verschliessen von Bohrungen in der Diffusor-Fläche des Sieb-Rohrs Fig. 3 und
Fig. 5
eine Schnittdarstellung einer Raucheinheit mit den Bestandteilen nach Fig. 3 und Fig. 4.
Show it:
Fig. 1
a functional smoke unit in sectional view, without filling and inner cover,
Fig. 2
1 installed in a training rocket in the operational state,
Fig. 3
a one-piece screen pipe of a further developed smoke unit, a variant of Fig. 1, with axial holes in its diffuser surface,
Fig. 4
a tape with a plug for closing bores in the diffuser surface of the sieve tube Fig. 3 and
Fig. 5
3 shows a sectional illustration of a smoking unit with the components according to FIGS. 3 and 4.

In sämtlichen Figuren sind gleiche Funktionsteile mit gleichen Bezugsziffern versehen.In all figures, the same functional parts are the same Provide reference numbers.

Gemäss Fig. 1 ist mit 1 der Aussenring eines Hohlzylinders bezeichnet, in dessen Inneren befindet sich ein Sieb-Rohr 2, welches eine Vielzahl zylindrischer Bohrungen 5 aufweist. Der Aussenring 1 und das Sieb-Rohr 2 sind in bekannter Weise durch Nieten 3 miteinander fest verbunden. 1, 1 is the outer ring of a hollow cylinder referred to, inside which there is a sieve tube 2, which has a plurality of cylindrical bores 5. Of the Outer ring 1 and the sieve tube 2 are in a known manner firmly connected by rivets 3.

Im Aussenring 1 befindet sich eine Einfüllöffnung 4, welche dem Einfüllen eines Rauchsatzes in den zwischen den Teilen 1 und 2 gebildeten Hohlraum, die Brennkammer 6, dient.In the outer ring 1 there is a filling opening 4 which the filling of a smoke set in the between parts 1 and 2 formed cavity, the combustion chamber 6, is used.

Die Brennkammer 6, in welcher eine Rauchbildung erfolgt, besitzt heckseitig eine kegelförmige Diffusor-Fläche 7.The combustion chamber 6, in which smoke is generated, has a conical diffuser surface 7 on the rear.

Gemäss Fig. 2 ist die Raucheinheit nach Fig. 1 in das Gehäuse 16 einer Übungsrakete R eingeschoben. Der Aussenring 1, im Innern des Gehäuses 16, ist über einen Adapter-Flansch 10 mit einer notorisch bekannten Schubdüse 12 eines Triebwerks 11 mechanisch verbunden. Beim Triebwerk 11 handelt es sich um einen Feststoff-Booster.According to FIG. 2, the smoke unit according to FIG. 1 is in the housing 16 of a practice rocket R inserted. The outer ring 1, in Inside of the housing 16, is with an adapter flange 10 a notoriously known thruster 12 of an engine 11 mechanically connected. The engine 11 is a solids booster.

In Abschussrichtung f ist ein länglicher Frontkörper 13 (Eject Bar) mit einer Spitze 14 vorgesehen, welcher in Bezug auf seine Masse und Trägheitsmomente die Eigenschaften einer realen Lenkwaffe aufweist.In the firing direction f there is an elongated front body 13 (Eject Bar) provided with a tip 14, which in relation on its mass and moments of inertia the properties of a has real missile.

Heckseitig ist das Endteil 15 analog einer üblichen Lenkwaffe ausgebildet.The rear part 15 is analogous to a conventional missile educated.

In der Brennkammer 6, gebildet aus dem Aussenring 1 und dem Sieb-Rohr 2, befindet sich ein an sich bekannter Rauchsatz 9.In the combustion chamber 6, formed from the outer ring 1 and the Sieve tube 2, there is a smoke set 9 known per se.

Die Diffusor-Fläche 7 weist einen grösseren Öffnungswinkel auf als der kegelförmige Teil der Düsenbohrung 7' in einer Schubdüse 12.The diffuser surface 7 has a larger opening angle on as the conical part of the nozzle bore 7 'in one Thruster 12.

Im Innern der Raucheinheit sind die Bohrungen 5 durch eine leicht entflammbare Folie 8 abgedeckt.Inside the smoke unit, the holes 5 are through a easily inflammable film 8 covered.

Die Funktionsweise der Vorrichtung ist von grösster Einfachheit und somit von höchster Betriebssicherheit: Wird der Raketenmotor 11 in üblicher Weise gezündet, entstehen Heiss-Gase, welche über die Düsenbohrung 7' auf die Folie 8 treffen und diese anzünden. Gleichzeitig wird der in der Brennkammer 6 befindliche Rauchsatz 9 gezündet; die Rauchgase werden mit der abströmenden Luft abtransportiert und sind, im vorliegenden Fall über die gesamte Fugbahn der Übungsrakete R vorhanden und bilden einen entsprechenden Schweif, der die Flugbahn der Rakete R anzeigt.The operation of the device is extremely simple and thus of the highest operational reliability: Will the rocket engine 11 ignited in the usual way, hot gases are produced, which meet the film 8 via the nozzle bore 7 ' and light it. At the same time it is in the combustion chamber 6 smoke set located 9 ignited; the flue gases are with of the outflowing air and are, in the present Fall over the entire trajectory of the practice rocket R available and form a corresponding tail that the trajectory the missile R indicates.

Im vorgängig beschriebenen und erprobten Ausführungsbeispiel handelt es sich um eine Boden/Luft-Rakete des Typs Stinger (siehe Prospekt 01-710A, undatiert, der BC BRUNSWICK CORPORATION, Defense Division, 3333 Harbor Blvd., Costa Mesa, CA 92626 USA: STINGER Weapon System Training STLS, bzw. STINGER Launch Simulator STLS). Diese Rakete bezitzt ein Starttriebwerk, welche die Rakete auf eine zum Abschuss nötige minimale Geschwindigkeit von 30 m/s beschleunigt. Nach dem Verlassen des Abschussrohrs ist die Schubphase des Starttriebwerks beendet, es werden demzufolge auch keine Rauchgase produziert. Diese Übungsrakete R besitzt kein Marschtriebwerk.In the previously described and tested embodiment is a Stinger surface-to-air missile (see brochure 01-710A, undated, the BC BRUNSWICK CORPORATION, Defense Division, 3333 Harbor Blvd., Costa Mesa, CA 92626 USA: STINGER Weapon System Training STLS, or STINGER Launch Simulator STLS). This missile has a start engine, which the rocket to a minimum necessary for launch Accelerated speed of 30 m / s. After leaving of the launch tube is the thrust phase of the starting engine ended, therefore no flue gases are produced. This practice rocket R has no cruise engine.

Der verwendete Rauchsatz 9 basiert auf einer pyrotechnischen Mischung aus 22% Zinkoxid, 18% Polyvinylchlorid, einer Reaktionsmischung aus 22% Zinkdiaminchlorid, 36% Ammoniumperchlorat und 2% Kollodiumwolle E220. Der pulverförmige Rauchsatz wird in üblicher Weise mittels Vibrator beim Einfüllen in die Brennkammer 6 verdichtet.The smoke set 9 used is based on a pyrotechnic Mixture of 22% zinc oxide, 18% polyvinyl chloride, a reaction mixture from 22% zinc diamine chloride, 36% ammonium perchlorate and 2% collodion wool E220. The powder smoke set is in the usual way using a vibrator when filling in the Combustion chamber 6 compressed.

Bewährt haben sich im Sieb-Rohr 2 auf der ganzen Zylinderfläche verteilte vierundzwanzig Bohrungen von je 5,8 mm Durchmesser.Have proven themselves in the sieve tube 2 on the entire cylinder surface distributed twenty four holes of 5.8 mm each Diameter.

Der Aussenring 1 und das Siebrohr 2 sind aus handelsüblichem Chrom/Nickel-Stahl hergestellt. Die Nieten 3, Fig.1, sind aus einer Aluminiumlegierung und eine hier nicht näher dargestellte Abdeckung der Einfüllöffnung 4 aus einer handelsüblichen Aluminiumfolie mit leitender Oberfläche (Scotch-Tape #1170, according to MIL-A-46050; Handelsmarke der Firma 3M Minnesota, USA). Die hitzeempfindliche Folie 8 ist ein ebenfalls handelsübliches Aluminiumband (COROPLAST #919, alubedampft; Firma Permapack AG, CH-9401 Rorschach).The outer ring 1 and the sieve tube 2 are made of commercially available Chrome / nickel steel manufactured. The rivets 3, Fig.1, are out an aluminum alloy and one not shown here Covering the filling opening 4 from a commercially available Aluminum foil with a conductive surface (Scotch tape # 1170, according to MIL-A-46050; Trademark of the 3M company Minnesota, USA). The heat sensitive film 8 is a also commercially available aluminum tape (COROPLAST # 919, aluminum-steamed; Permapack AG, CH-9401 Rorschach).

Bei der praktischen Erprobung der vorgängig beschriebenen ersten Variante einer Raucheinheit hat es sich gezeigt, dass bei Umgebungstemperaturen von über 50° C der Schubstrahl des Raketenmotors 11 den Aussenring 1 aufbläht und dadurch die Rakete R im Abschussrohr behindert oder dass diese sogar darin stecken bleibt.In the practical testing of the first described above Variant of a smoking unit, it has been shown that at ambient temperatures of over 50 ° C the thrust jet of the Rocket motor 11 inflates the outer ring 1 and thereby the Missile R in the launch tube hindered or even this gets stuck in it.

In einem bevorzugten Ausführungsbeispiel wurde daher der Erfindungsgegenstand weiterentwickelt, indem eine Ausgestaltung des Sieb-Rohrs 2 gemäss Fig. 3 vorgesehen wurde.In a preferred embodiment, therefore, the subject of the invention evolved by designing of the sieve tube 2 according to FIG. 3 was provided.

Dieses Sieb-Rohr 2 ist einstückig ausgestaltet und besitzt in seinem zylindrischen Rohrteil Bohrungen 5, welche identisch sind mit denjenigen gemäss Fig. 1. Zusätzlich weist das Sieb-Rohr 2 nach Fig. 3 je seitlich ein Aussengewinde 17 und in seiner Diffusor-Fläche 7 ebenfalls Bohrungen 18, die hier aber axial verlaufen.This sieve tube 2 is designed in one piece and has in its cylindrical tubular part bores 5, which are identical are with those according to Fig. 1. In addition, the screen tube 2 according to FIG. 3 each has an external thread 17 and in its diffuser surface 7 also bores 18, which are here but run axially.

Diese axialen Bohrungen 18 sind mittels eines ringförmigen Bands 19 mit Verschlusszapfen 20, Fig. 4 verschlossen.These axial bores 18 are annular Bands 19 closed with locking pins 20, Fig. 4.

In der Zusammenstellungszeichnung Fig. 5 ist das bevorzugte Ausführungsbeispiel als Ganzes dargestellt.5 is the preferred one Embodiment shown as a whole.

Nach der Auskleidung der zylindrischen Mantels des Sieb-Rohrs 2 mittels der hitzeempfindlichen Folie 8 wird der Adapterflansch 10 mit seiner Stirnfläche 10' durch vier Befestigungsschrauben 3' an der Schubdüse 12 des Raketenmotors 11, vgl. Fig. 2 verschraubt. Diese Schrauben 3' finden in einer ringförmigen Ausnehmung 22 platz. Der Aussenring 1 ist von der linken Seite her über das Sieb-Rohr 2 geschoben und an dessen Aussengewinde 17, heckseitig verschraubt. Dabei liegt die Flanschpartie 1' des Aussenrings 1 dicht an der Flanschpartie 2' des Sieb-Rohrs 2 an. After lining the cylindrical jacket of the sieve tube 2 by means of the heat-sensitive film 8, the adapter flange 10 with its end face 10 'by four fastening screws 3 'on the thrust nozzle 12 of the rocket motor 11, see. Fig. 2 screwed. These screws 3 'find one annular recess 22 place. The outer ring 1 is from the left side pushed over the sieve tube 2 and on whose external thread 17, screwed to the rear. Here lies the flange portion 1 'of the outer ring 1 close to the flange portion 2 'of the sieve tube 2.

Im Unterschied zu Fig. 1 bzw. Fig. 2 ist hier das Sieb-Rohr 2 strömungsgünstiger ausgestaltet, in dem es einen bombierten Einlass 21 aufweist, welcher die Treibgase des Raketenmotors verstärkt durch die Bohrungen 5 Richtung Folie 8 lenkt und deren Anzünden beschleunigt.In contrast to FIG. 1 or FIG. 2, here is the sieve tube 2 more aerodynamically designed, in which there is a convex Inlet 21, which contains the propellant gases of the rocket engine reinforced through the holes 5 directs film 8 and their lighting accelerated.

So dann werden die Verschlusszapfen 20 zusammen mit dem ringförmigen Band 19 von aussen in die Bohrungen 18 - in der Diffusor-Fläche 7 hineingedrückt. Das Band 19 wird mit einem handelsüblichen Silikonkleber mit dem Flansch 7 verklebt. Daraufhin wird der Rauchsatz 9, in Form von kleinen "Pellets" in den resultierenden Zwischenraum, die Brennkammer 6 eingefüllt, verdichtet und anschliessend die Einfüllöffnung 4 mit einem handelsüblichen Klebstreifen 4' verschlossen.So then the locking pin 20 together with the annular Band 19 from the outside into the holes 18 - in the diffuser surface 7 pushed in. The tape 19 is with a commercially available silicone adhesive glued to the flange 7. Thereupon the smoke set 9, in the form of small "pellets" in the resulting space, the combustion chamber 6 filled, compresses and then the filling opening 4 with a commercial adhesive tape 4 'closed.

Die genauere Ausgestaltung des ringförmigen Bands 19 mit seinen am Band angegossenen Verschlusszapfen 20 ist der Fig. 4 zu entnehmen. Als Material hat sich hierfür Polyurethan bewährt, das sich in einem Druckgiessverfahren ("Spritzen") leicht einstückig fabrizieren lässt.The more precise design of the annular band 19 with its The locking pin 20 cast onto the band is shown in FIG. 4 refer to. Polyurethane has proven itself as a material for this, which is in a die casting process ("spraying") easily manufactured in one piece.

Im Gegensatz zur ersten Variante sind der Aussenring 1 und das Siebrohr 2 hier aus einer hochfesten Aluminiumlegierung (Handelsmarke Perunal 215 der Firma Alusuisse AG, Schweiz; Werkstoff nach DIN 3.4365; Bezeichnung USA: 7075 - T6). Diese Aluminiumlegierung ergibt gegenüber der vorgängig beschriebenen Variante eine Gewichtsersparnis und lässt sich wirtschaflicher herstellen.In contrast to the first variant, the outer ring 1 and the sieve tube 2 here made of a high-strength aluminum alloy (Trademark Perunal 215 from Alusuisse AG, Switzerland; Material according to DIN 3.4365; Description USA: 7075 - T6). This Aluminum alloy results in comparison to that previously described Variant a weight saving and can be more economical produce.

In einer weiteren, gegenüber Fig. 2 geänderten Ausführungsform wird auf die dort dargestellte Formschlüssigkeit der Raucheinheit verzichtet, so dass diese nachträglich - optional - in die Übungsrakete R eingeschoben und verschraubt werden kann.In a further embodiment, modified compared to FIG. 2 is based on the form fit of the No smoking unit, so that this is optional - are inserted and screwed into the practice rocket R. can.

Das Verfolgen des Raketenabschusses erleichtert dem Bodenpersonal das notwendige Einüben der Abschussmanipulationen. In gleicher Weise können Piloten Ausweichmanöver trainieren, wenn sie die Flugbahn der Rakete aus ihrer Sicht beobachten können. Im Ernstfall, d.h. wenn eine Rakete mit Kriegsmunition abgeschossen wird, genügt dem Piloten bereits der durch den Raketenmotor oder dessen Booster erzeugte Rauch um einen Abschuss nicht nur zu erkennen, sondern auch um das ihn und das Flugzeug rettende Ausweichmanöver einzuleiten; ist doch die Flugdynamik einer konventionellen Boden/Luftrakete aus systemtechnischen Gründen sehr beschränkt.Tracking missile launches makes it easier for ground personnel the necessary practice of the shooting manipulations. In pilots can also practice evasive maneuvers, when they see the missile’s trajectory from their perspective can. In an emergency, i.e. if a missile with war ammunition is shot down, the pilot already suffices the rocket engine or its booster produced smoke around you Shot not only to recognize, but also about him and him initiate evasive maneuvers to save the aircraft; is the flight dynamics of a conventional ground / air rocket very limited for technical reasons.

Selbstverständlich ist der Erfindungsgegenstand nicht auf das Ausführungsbeispiel beschränkt, er lässt sich in analoger Weise auch an andere Triebwerke, Nachbrenner und dgl. adaptieren.Of course, the subject of the invention is not based on that Limited embodiment, it can be in analog Adapt it to other engines, afterburner and the like.

Anstelle der verwendeten pyrotechnischen Rauchsätze sind auch sogenannte Dampfgeneratoren denkbar, welche noch umweltfreundlicher als der an sich gefahrlos zu verwendende Rauchsatz 9 sind. Der bei der Dampfbildung ablaufende endotherme Prozess würde zudem der Kühlung der Brennkammer dienen und könnte somit die an sich bereits vorhandene Wiederverwendbarkeit des Systems erhöhen und würde insbesondere das Abschussrohr und die daran montierten Bauteile schonen.Instead of the pyrotechnic smoke kits used, too so-called steam generators conceivable, which are even more environmentally friendly than the smoke set that can be used safely 9 are. The endothermic that occurs during the formation of steam Process would also serve to cool the combustion chamber and could thus be the existing reusability of the system and in particular would increase the launch tube and protect the components mounted on it.

Bei Übungsraketen könnten auch, anstelle von Zielfolge-Elektronik und von Sprengladungen die notwendigen Wasserbehälter in den Raketenkörper integriert werden.Practice rockets could also, instead of target electronics and the necessary water containers from explosive charges be integrated into the missile body.

Es sind auch Kombinationen von pyrotechnischen Raucheinheiten und wassergespeisten Dampfeinheiten denkbar, die sequentiell und/oder parallel zuschaltbar sind.There are also combinations of pyrotechnic smoking units and water-powered steam units conceivable that are sequential and / or can be connected in parallel.

Claims (10)

Vorrichtung zur Erzeugung einer optischen Markierung der Flugbahn eines durch ein Triebwerk beschleunigten Flugkörpers, insbesondere einer Rakete, welche Vorrichtung dem Triebwerk zugeordnet ist, und die dem austretenden Gasstrahl und/oder der abströmenden Luft sichtbare Rauch und/oder Dampfpartikel beimengt, dadurch gekennzeichnet, dass an die Düse eines Raketenmotors eine Rauch- und/oder Dampfeinheit angeschlossen ist, welche durch den Gasstrahl des Raketenmotors aktiviert, bzw. gezündet wird.Device for generating an optical marking of the Trajectory of a missile accelerated by an engine, especially a missile, which device is assigned to the engine, and the exiting Gas jet and / or smoke flowing out of the air flowing out and / or steam particles, characterized in that that on the nozzle of a rocket engine a smoke and / or Steam unit is connected, which by activated or ignited the gas jet of the rocket engine becomes. Vorrichtung nach Anspruch 2, dadurch gekennzeichnet, dass die Raucheinheit im wesentlichen aus einem Hohlzylinder (1;2) besteht, der im Inneren Bohrungen (5) aufweist, welche durch eine hitzeempfindliche Folie (8) abgedeckt sind.Device according to claim 2, characterized in that the smoke unit essentially consists of a hollow cylinder (1; 2), which has holes (5) in the interior, which is covered by a heat-sensitive film (8) are. Vorrichtung nach Anspruch 2, dadurch gekennzeichnet, dass im Inneren des Hohlzylinders (1;2) ein Siebrohr (2) vorgesehen ist, welches heckseitig eine Diffusor-Fläche (7) aufweist.Device according to claim 2, characterized in that inside the hollow cylinder (1; 2) a sieve tube (2) is provided, which has a diffuser surface at the rear (7). Vorrichtung nach Anspruch 3, dadurch gekennzeichnet, dass in der Diffusor-Fläche (7) axiale Bohrungen (18) vorhanden sind.Device according to claim 3, characterized in that axial bores (18) in the diffuser surface (7) available. Vorrichtung nach Anspruch 4, dadurch gekennzeichnet, dass die Bohrungen (18) durch Verschlusszapfen (20) dicht verschlossen sind.Device according to claim 4, characterized in that the bores (18) through locking pins (20) are tightly closed. Vorrichtung nach Anspruch 3, dadurch gekennzeichnet, dass die Bohrungen (18) durch Verschlusszapfen (20), welche an einem Band (19) angeordnet sind, dicht verschlossen sind. Device according to claim 3, characterized in that the bores (18) through locking pins (20), which are arranged on a band (19), tightly closed are. Vorrichtung nach Anspruch 2, dadurch gekennzeichnet, dass gegenüber der Düse (7') des Triebwerks ein bombierter Einlass (21) im Hohlzylinder (1; 2) angeordnet ist.Device according to claim 2, characterized in that compared to the nozzle (7 ') of the engine a convex Inlet (21) arranged in the hollow cylinder (1; 2) is. Vorrichtung nach einem der Ansprüche 2 bis 7, dadurch gekennzeichnet, dass der Hohlzylinder (1;2) eine pyrotechnische Mischung enthält.Device according to one of claims 2 to 7, characterized characterized in that the hollow cylinder (1; 2) is a pyrotechnic Mix contains. Vorrichtung nach Anspruch 8, dadurch gekennzeichnet, dass die pyrotechnische Mischung aus 22% Zinkoxid, 18% Polyvinylchlorid, einer Reaktionsmischung aus 22% Zinkdiaminchlorid, 36% Ammoniumperchlorat und 2% Kollodiumwolle besteht.Device according to claim 8, characterized in that the pyrotechnic mixture of 22% zinc oxide, 18% Polyvinyl chloride, a reaction mixture of 22% zinc diamine chloride, 36% ammonium perchlorate and 2% collodion wool consists. Vorrichtung nach Anspruch 1, dadurch gekennzeichnet, dass die Dampfeinheit aus mehreren, wasserführenden Rohrleitungen besteht, welche in einem Hohlzylinder münden und durch hitzeempfindliche Endstücke oder Sicherungen abgeschlossen und/oder gesichert sind.Device according to claim 1, characterized in that the steam unit consists of several, water-bearing Pipes exist which open into a hollow cylinder and by heat-sensitive end pieces or fuses completed and / or secured.
EP97204141A 1997-02-25 1997-12-30 Device for the optical marking of the trajectory of missiles propelled by thrusters Expired - Lifetime EP0860682B1 (en)

Applications Claiming Priority (2)

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US3830997P 1997-02-25 1997-02-25
US38309P 1997-02-25

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Also Published As

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DE59707152D1 (en) 2002-06-06
DK0860682T3 (en) 2002-07-29
ATE217077T1 (en) 2002-05-15
US5929369A (en) 1999-07-27
EP0860682B1 (en) 2002-05-02

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