EP0860682B1 - Device for the optical marking of the trajectory of missiles propelled by thrusters - Google Patents

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

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.

In connection with the training of operating personnel of surface-to-air missiles, surface-to-surface missiles and air-to-surface missiles however, it is helpful if the trajectory the missile, at least in its launch area, is visually visible is.

Avoidance maneuvers can also be practiced by pilots, if they launch practice rockets early and safely can recognize.

From 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.

It is therefore an object of the present invention to provide a device to create which are readily available as additional Unit can be assigned to an engine and which the Thrust performance of the engine is not affected or only slightly affected and have no influence on the control behavior of the missile.

In addition, the system security of the entire missile may through this additional unit, even under extreme operating conditions, not be endangered.

This object is achieved in the characterizing part of claim 1 specified measures solved.

It is advantageous to have one attached to the rear of a sieve tube Diffuser surface as it is aerodynamic and coaxial smoke distribution also favors.

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.

Advantageous further developments are in the dependent claims below described the subject of the invention.

By including holes in the diffuser surface, Claim 2, overpressures can be reduced in the smoke unit and malfunctions, especially at higher ones Temperatures can be prevented.

Convenient are locking pin according to claim 3, which in easiest way to relieve overprints by turning them off the holes are pushed.

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.

Alternatively, the construction of 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.

Based on practical examples, the following the subject of the invention shown in more detail.

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.

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 the diffuser surface,

Fig. 4

a tape with sealing plugs for closing bores in the diffuser surface of the screen 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 all figures, the same functional parts are the same Provide reference numbers.

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.

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.

The combustion chamber 6, in which smoke is generated, has a conical diffuser surface 7 on the rear.

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 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.

The rear part 15 is analogous to a conventional missile educated.

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.

The diffuser surface 7 has a larger opening angle on as the conical part of the nozzle bore 7 'in one Thruster 12.

Inside the smoke unit, 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.

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 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.

Have proven themselves in the sieve tube 2 on the entire cylinder surface distributed twenty four holes of 5.8 mm each Diameter.

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).

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 a preferred embodiment, therefore, the subject of the invention evolved by designing of the sieve tube 2 according to FIG. 3 was provided.

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.

These axial bores 18 are annular Bands 19 closed with locking pins 20, Fig. 4.

5 is the preferred one Embodiment shown as a whole.

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.

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 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.

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.

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 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.

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.

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.

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.

Practice rockets could also, instead of target electronics and the necessary water containers from explosive charges be integrated into the missile body.

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 (8)

1. Assembly for generating an optical marking of the flight path of a flying object, in particular a rocket, which is accelerated by a power unit, which assembly is associated with the power unit and has a component which is in the form of a hollow cylinder and which admixes visible smoke and/or steam particles to the exhaust gas jet and/or the discharged air, characterised in that a smoke and/or steam unit is connected to the nozzle of the power unit or to the rocket motor and is activated or ignited by the gas jet of the rocket motor, in that a sieved tube (2) is provided inside the hollow cylinder (1; 2) and has a diffusor face (7) at the rear end, and in that the hollow cylinder (1; 2) has bore holes (5) therein, which are covered by a heat-sensitive foil (8).
2. Assembly according to claim 1, characterised in that axial bore holes (18) are provided in the diffusor face (7).
3. Assembly according to claim 2, characterised in that the bore holes (18) are sealed tightly by locking spigots (20).
4. Assembly according to claim 2, characterised in that the bore holes (18) are sealed tightly by locking spigots (20) which are arranged on a band (19).
5. Assembly according to claim 1, characterised in that a tapered inlet (21) is arranged in the hollow cylinder (1; 2) opposite the nozzle (7') of the power unit.
6. Assembly according to any one of claims 1 to 5, characterised in that the hollow cylinder (1; 2) contains a pyrotechnic mixture.
7. Assembly according to claim 6, characterised in that the pyrotechnic mixture comprises 22% zinc oxide, 18% polyvinyl chloride, a reaction mixture of 22% zinc diaminochloride, 36% ammonium perchlorate and 2% collodion cotton.
8. Assembly according to claim 1, characterised in that the steam unit comprises a plurality of water-carrying tubes which open in a hollow cylinder and which are closed and/or secured by heat-sensitive end pieces or safety devices.

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