EP0860682B1 - Vorrichtung für die optische Markierung der Flugbahn von durch Triebwerke beschleunigten Flugkörpern - Google Patents
Vorrichtung für die optische Markierung der Flugbahn von durch Triebwerke beschleunigten Flugkörpern Download PDFInfo
- Publication number
- EP0860682B1 EP0860682B1 EP97204141A EP97204141A EP0860682B1 EP 0860682 B1 EP0860682 B1 EP 0860682B1 EP 97204141 A EP97204141 A EP 97204141A EP 97204141 A EP97204141 A EP 97204141A EP 0860682 B1 EP0860682 B1 EP 0860682B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- assembly according
- hollow cylinder
- rocket
- smoke
- unit
- 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.)
- Expired - Lifetime
Links
Images
Classifications
-
- 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 according to the Preamble of claim 1.
- 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 they launch practice rockets early and safely can recognize.
- US-A-4 721 042 is a rocket with a lighting unit known, which is ignited after the launch of the rocket and gives off a visible trace of light during the flight.
- the Luminous unit is designed as a hollow cylinder between the outside of the housing of the drive nozzle and the inner wall of the rocket is arranged.
- the hollow cylinder is through special constructive measures in the area of Propulsion part of the rocket formed.
- system security of the entire missile may through this additional unit, even under extreme operating conditions, not be endangered.
- a heat-sensitive film that has proven itself has proven itself the hot exhaust gases from the engine melted and / or ignited and the penetration of the gases into the smoke unit allows.
- the band mentioned in claim 4 facilitates the assembly of the Cones and is also aerodynamic.
- a convex design is also flow-favorable the inlet, cf. Claim 5, she also directs the hot ones Gases from the engine towards foil sensitive to heat and accelerates their ignition.
- a smoke set according to claim 6 is favorable.
- the pyrotechnic mixture according to claim 7 has proven to be proven optimal.
- a smoke unit also transferred to a steam unit, whereby the pressure generation in the water pipes easily through the Back pressure of the rocket can be generated and the initiation of Vapor formation by melting and / or burning off the Closure pieces or fuses, claim 8, takes place.
- 1, 1 denotes the output of a hollow cylinder, inside there is 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.
- This rocket has a launch 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.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
- Guiding Agricultural Machines (AREA)
- General Factory Administration (AREA)
- Vehicle Waterproofing, Decoration, And Sanitation Devices (AREA)
- Toys (AREA)
Description
- 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 der Diffusor-Fläche,
- Fig. 4
- ein Band mit Verschlusspropfen 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.
Claims (8)
- Vorrichtung zur Erzeugung einer optischen Markierung der Flugbahn eines durch ein Triebwerk beschleunigten Flugkörpers, insbesondere einer Rakete, welche Vorrichtung dem Triebwerk zugeordnet ist und eine als Hohlzylinder ausgebildete Einheit aufweist, die dem austretenden Gasstrahl und/oder der abströmenden Luft sichtbare Rauch- und/oder Dampfpartikel beimengt, dadurch gekennzeichnet, dass an die Düse des Triebwerks bzw. an den Raketenmotor eine Rauch- und/oder Dampfeinheit angeschlossen ist, welche durch den Gasstrahl des Raketenmotors aktiviert bzw. gezündet wird, dass im Inneren des Hohlzylinders (1;2) ein Siebrohr (2) vorgesehen ist, welches heckseitig eine Diffusor-Fläche (7) aufweist, und dass der Hohlzylinder (1;2) im Inneren Bohrungen (5) aufweist, welche durch eine hitzempfindliche Folie (8) abgedeckt sind,
- Vorrichtung nach Anspruch 1, dadurch gekennzeichnet, dass in der Diffusor-Fläche (7) axiale Bohrungen (18) vorhanden sind.
- Vorrichtung nach Anspruch 2, dadurch gekennzeichnet, dass die Bohrungen (18) durch Verschlusszapfen (20) dicht verschlossen sind.
- Vorrichtung nach Anspruch 2, dadurch gekennzeichnet, dass die Bohrungen (18) durch Verschlusszapfen (20), welche an einem Band (19) angeordnet sind, dicht verschlossen sind.
- Vorrichtung nach Anspruch 1, dadurch gekennzeichnet, dass gegenüber der Düse (7') des Triebwerks ein bombierter Einlass (21) im Hohlzylinder (1;2) angeordnet ist.
- Vorrichtung nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, dass der Hohlzylinder (1;2) eine pyrotechnische Mischung enthält.
- Vorrichtung nach Anspruch 6, dadurch gekennzeichnet, dass die pyrotechnische Mischung aus 22% Zinkoxid, 18% Polyvinylchlorid, einer Reaktionsmischung aus 22% Zinkdiaminchlorid, 36% Ammoniumperchlorat und 2% Kollodiumwolle besteht.
- 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.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US3830997P | 1997-02-25 | 1997-02-25 | |
US38309P | 1997-02-25 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0860682A1 EP0860682A1 (de) | 1998-08-26 |
EP0860682B1 true EP0860682B1 (de) | 2002-05-02 |
Family
ID=21899201
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP97204141A Expired - Lifetime EP0860682B1 (de) | 1997-02-25 | 1997-12-30 | Vorrichtung für die optische Markierung der Flugbahn von durch Triebwerke beschleunigten Flugkörpern |
Country Status (5)
Country | Link |
---|---|
US (1) | US5929369A (de) |
EP (1) | EP0860682B1 (de) |
AT (1) | ATE217077T1 (de) |
DE (1) | DE59707152D1 (de) |
DK (1) | DK0860682T3 (de) |
Families Citing this family (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6581521B1 (en) * | 2002-08-26 | 2003-06-24 | Robert G. Dixon | Reusable gas grenade canister |
US6845715B2 (en) * | 2003-02-24 | 2005-01-25 | Arie Sansolo | Explosion simulator |
GB2442382B (en) * | 2005-07-06 | 2008-05-21 | Tdw Verteidigungstech Wirksys | Adjustable charge for a warhead |
DE102005031588B3 (de) * | 2005-07-06 | 2007-01-11 | TDW Gesellschaft für verteidigungstechnische Wirksysteme mbH | Dosierbare Ladung eines Gefechtskopfes |
US7451680B1 (en) * | 2006-10-20 | 2008-11-18 | The United States Of America As Represented By The Secretary Of The Navy | Submarine steam generator missile ejection system |
US20080223246A1 (en) * | 2007-03-13 | 2008-09-18 | Dindl Frank J | Burping projectile |
DE102009020558A1 (de) * | 2009-05-08 | 2010-11-18 | Rheinmetall Waffe Munition Gmbh | Aktivierungseinheit für munitionsfreie Scheinziele |
DE102008028245A1 (de) * | 2008-06-16 | 2009-12-17 | Rheinmetall Waffe Munition Gmbh | Flareanzündung sowie Verwendung in einem Ausstoßsystem |
SG10201402195PA (en) | 2009-05-08 | 2014-10-30 | Rheinmetall Waffe Munition | Activation unit for explosive masses or explosive bodies |
DE102009030870A1 (de) | 2009-06-26 | 2010-12-30 | Rheinmetall Waffe Munition Gmbh | Wirkkörper |
DE102009030869A1 (de) | 2009-06-26 | 2011-02-10 | Rheinmetall Waffe Munition Gmbh | Wirkkörper |
DE102012020540A1 (de) * | 2012-10-19 | 2014-04-24 | Rheinmetall Waffe Munition Gmbh | Patrone und Verfahren zu seiner Herstellung |
DE102012020541A1 (de) * | 2012-10-19 | 2014-04-24 | Rheinmetall Waffe Munition Gmbh | Patrone und Verfahren zu seiner Herstellung |
DE102014001866B3 (de) * | 2014-02-06 | 2015-07-02 | Martin Rybol | Aus der Kartusche eines Infrarot-Täuschkörpers ausstoßbarer Wirkkörper |
US9062948B1 (en) * | 2014-10-03 | 2015-06-23 | ASGS Associates, Trustee for Aerial Smoke Generator System CRT Trust | Aerial smoke generator system |
Family Cites Families (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB1236416A (en) * | 1968-07-09 | 1971-06-23 | Aerospatiale | An infra-red tracer for a missile |
US3680484A (en) * | 1968-08-03 | 1972-08-01 | Messerschmitt Boelkow Blohm | Pyrotechnic emitter |
US3712228A (en) * | 1969-02-26 | 1973-01-23 | Us Navy | Target marker warhead |
US3625155A (en) * | 1970-01-08 | 1971-12-07 | Us Navy | Device for producing white smoke by imploding red phosphorus |
US3726226A (en) * | 1971-08-31 | 1973-04-10 | Us Army | Universal smoke marking grenade for dry and inundated areas |
DE2733700C2 (de) * | 1977-07-26 | 1979-05-03 | Buck Chemisch-Technische Werke Gmbh & Co, 8230 Bad Reichenhall | Übungsgefechtskopf für Artillerieraketen |
SE427694B (sv) * | 1979-04-02 | 1983-04-25 | Bofors Ab | Speciellt for utbilndningsendamal anvendbar fullkalibrig ovningsgranat |
US4436034A (en) * | 1981-05-05 | 1984-03-13 | A/S Raufoss Ammunisjonsfabrikker | Smoke grenade with successive slow and fast burning charges |
US4438700A (en) * | 1982-07-19 | 1984-03-27 | The United States Of America As Represented By The Secretary Of The Army | White smoke spotting composition for training ammunition |
NO153190C (no) * | 1983-10-20 | 1986-01-29 | Raufoss Ammunisjonsfabrikker | Anordning ved raketter. |
EP0229457B1 (de) * | 1985-10-31 | 1991-03-13 | British Aerospace Public Limited Company | Leuchtsatz für Rakete |
US4726295A (en) * | 1986-05-16 | 1988-02-23 | Aai Corporation | Grenade arrangement for screening cloud |
US4732086A (en) * | 1987-01-27 | 1988-03-22 | Honeywell Inc. | Fin stabilized armor-penetrating tracer projectile and method of manufacturing same |
DE4101392C2 (de) * | 1991-01-18 | 1994-05-19 | Buck Chem Tech Werke | Mörsergranate |
FR2694804B1 (fr) * | 1992-08-11 | 1994-09-16 | Poudres & Explosifs Ste Nale | Leurre stabilisée et propulsé, émettant dans l'infrarouge. |
US5661257A (en) * | 1996-01-16 | 1997-08-26 | Thiokol Corporation | Multispectral covert target marker |
-
1997
- 1997-12-30 AT AT97204141T patent/ATE217077T1/de not_active IP Right Cessation
- 1997-12-30 EP EP97204141A patent/EP0860682B1/de not_active Expired - Lifetime
- 1997-12-30 DE DE59707152T patent/DE59707152D1/de not_active Expired - Fee Related
- 1997-12-30 DK DK97204141T patent/DK0860682T3/da active
-
1998
- 1998-02-24 US US09/028,702 patent/US5929369A/en not_active Expired - Fee Related
Also Published As
Publication number | Publication date |
---|---|
DK0860682T3 (da) | 2002-07-29 |
DE59707152D1 (de) | 2002-06-06 |
EP0860682A1 (de) | 1998-08-26 |
US5929369A (en) | 1999-07-27 |
ATE217077T1 (de) | 2002-05-15 |
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