EP0056789B1 - Recoilless missile system - Google Patents

Description

The present invention relates to a recoil-free missile system with at least one tube and at least one missile projectile for each tube, the tube having at least one chamber for receiving a propellant charge (see DE-A-2721 248). This system is especially intended for anti-tank and anti-aircraft defense, i.e. moving point targets. Other applications are included.

There are a variety of weapon systems for fighting tanks and aircraft that use missile projectiles, and recoil-free tubes can be used. A very high initial speed is desirable for all missile projectiles, especially those that are not readjusted; if the propellant charge also has to be accelerated, the total weight of the projectile increases and a limit will soon be set for it, in particular when such weapon systems are used on the move.

It is an object of the present invention to provide a missile system which can be transported by a few people and in which the missile projectile reaches a very high initial speed and a previously unknown target or target accuracy is achieved. This goal is achieved with a missile system described in the claims.

• Fig. 1 zeigt, teilweise im Längsschnitt, ein erstes Ausführungsbeispiel eines Rohres und eines Raketengeschosses gemäß der Erfindung.
• Fig. 2 zeigt, im Längsschnitt, ein zweites Ausführungsbeispiel.
• Fig. 3 zeigt, teilweise im Längsschnitt, ein drittes Ausführungsbeispiel.
• Fig. 4 zeigt einen Schnitt von Fig. 3.
• Fig. 5 zeigt ein Anwendungsbeispiel des Geschosses gemäß Fig. 1.
• Fig. 6 zeigt ein Anwendungsbeispiel der Raketengeschosse gemäß Fig. 3 und 4.
• Fig. 7 zeigt, teilweise im Längsschnitt, ein weiteres Ausführungsbeispiel.
• Fig. 8 zeigt, im Längsschnitt und im vergrößerten Maßstab ein Detail von Fig. 7, und
• Fig. 9 zeigt einen Schnitt von Fig. 8.

The invention will now be explained in more detail with reference to a drawing of exemplary embodiments.

• Fig. 1 shows, partly in longitudinal section, a first embodiment of a tube and a missile projectile according to the invention.
• Fig. 2 shows, in longitudinal section, a second embodiment.
• Fig. 3 shows, partly in longitudinal section, a third embodiment.
• FIG. 4 shows a section from FIG. 3.
• FIG. 5 shows an application example of the projectile according to FIG. 1.
• 6 shows an application example of the missile projectiles according to FIGS. 3 and 4.
• Fig. 7 shows, partly in longitudinal section, a further embodiment.
• Fig. 8 shows, in longitudinal section and on an enlarged scale, a detail of Fig. 7, and
• FIG. 9 shows a section of FIG. 8.

1 shows the rocket tube 1 with two rotating rings 2 and 3, in which propellant charges 4 and 5 are located. At the points where the rings 2 and 3 are, gas passage openings 2a and 3a are arranged in the tube. At the rear end of the tube there is the outlet nozzle 6. In the missile tube 1 there is the missile projectile 7, which is a multi-stage missile projectile. At the rear, on the left in FIG. 1, is the first stage 8, which preferably consists of thin, circular films made of nitroglycerin-nitrocellulose. The propellant charge of the first stage is arranged around the extension of the nozzle 9 of the second stage 10, which is shown in section in FIG. 2 and will be explained there. This extension has holes 11 through which the gases of the first stage pass for the purpose of pressure relief. The tail unit 12, which consists of three or more wings 13, can also be seen at the rear end of the missile projectile. The gases initially pass through the tail unit and give the projectile a rotation corresponding to the position of the wings, for example five revolutions per second, in order to compensate for the imbalance caused by the building and burning of the propellant charges. For example, such an inaccuracy can cause a lateral force due to a shift in the center of gravity, which would result in a drift of 100 m at a distance of 1000 m; This drift can be reduced to a few decimeters by rotating the projectile. In contrast, a swirl stabilization of the projectile is not possible due to the impairment of the shaped charge effect. According to the invention, the projectile should be set in rotation immediately at the start, if possible without trains in the tube, i.e. H. when using a smooth tube. At the level of the second stage, a sealing, multi-part sabot 57, which serves as a guide in the tube, is attached to the missile projectile and releases after the missile has left the tube.

The head of the projectile, which is known per se and is not explained in more detail here, contains the projectile tip 14 and a shaped charge 15, as well as, for example, an impact detonator (not shown). In the outlet nozzle 6 there is a cover 43 which flies away during ignition with a black powder capsule 44 and an igniter 45.

The sequence of a shot is as follows: First, the igniter 45 ignites the black powder charge, which ignites the propellant charge of the first stage 8, which gives the projectile an initial acceleration, the tube also serving as a combustion chamber. The black powder charge simultaneously ignites the propellant charge of the second stage 10, which consists of considerably thick-walled powder rods. If the projectile in the tube has moved approximately one caliber length, the first propellant charge 4 of the tube is ignited, as a result of which the pressure in the tube is kept at a high level. These gases also initially pass through the tail unit 12 to the end nozzle 6. After the projectile has progressed further in the tube, the second propellant charge 5 is ignited, and further propellant charges can follow. It should be noted that the propellant charges 4 and 5 and possibly others need not be accelerated. An internal pressure of the order of 1000 bar builds up inside the tube, with none on the tube Recoil forces act and this therefore remains at rest when fired. The tube including the bullet can only be used once and for a next shot the entire tube with the bullet must be replaced. The tube can be reloaded in a suitable facility, the fastenings 16 and 17 of the rings 2, 3 being removed and the rings being exposed.

There are different ways to stabilize a projectile, for example the usual swirl stabilization and the so-called arrow stabilization. In the so-called arrow stabilization, the influence of the cross wind on the bullet trajectory is eliminated by giving the bullet a constant speed during the flight, which in this example means that the thrust of the second stage must be the same as the air resistance, so that the the initial speed given by the first stage and the propellant charges on the pipe is maintained.

When loading the missile projectile, the powder rods of the second stage are introduced through the nozzle 9 into the combustion chamber. After the last powder rod has been introduced, the opening in the sieve grate 18 which closes the second stage 10 is closed in a bayonet-like manner by a sieve grate closure 19.

An exemplary embodiment is given as an anti-tank projectile. Caliber 100 mm, tube length 3 m, weight of the loaded tube 100 kg, weight of the stationary propellant charge 2.5 kg, load weight of the first mobile charge 8 0.5 kg with a burning time of 5 ms, the second stage 0.5 kg with a burn time of 1 s; Internal pipe pressure over 1000 bar, initial speed about 1000 m / s, target distance about 1000 m.

With this caliber, the weight of the pipe and the projectile reaches a size at which the pipe can no longer be operated and straightened by one man alone. In order to achieve expedient operation, the tube, see FIG. 5, is placed on a tripod-shaped directional mount 20, the upper part 21 of which is designed to enable the tubes to be replaced quickly. Between the tripod and the upper part there is an electrical or hydraulic straightening aid 22, which can be operated with the hands or feet around the upper part, which also has a telescopic sight 23 and a range finder, relative to the tripod as a function of the distance, the elevation angle and adjust the two straightening angle speeds. As a further operating aid, it may be useful to attach an adjustment device that allows the riflescope to be adjusted electrically or hydraulically relative to the tube depending on the target distance, the elevation angle and the two directional angle speeds so that the correct lead angle of the moving target Tube remains set to the target if the rifle scope is constantly adjusted to the target. The total weight of the guide carriage including the hydraulics and the operating aids is approximately 100 kg. The position of the shooter on the one hand and due to the gases escaping to the front on the other hand prevent the shooter from being bothered by the fuel gases emerging from the tube at the front and rear. This also applies to the gases of the second stage 10 which was already ignited during the launch and which are deflected by the gases escaping to the front.

In the case of an even larger caliber and the resulting larger dimensions and weights, it is advisable to firmly install the pipes on a stationary or mobile gun carriage and to arrange the projectile together with propellant charges from the pipe and to attach them to the pipe again for each shot. Such an exemplary embodiment is shown in FIG. 2, which is a 200 millimeter caliber. One recognizes the tube 24, which rests on an upper part (not shown) of the directional mount 20 and to which a spherical combustion chamber 27 is fastened by means of a bayonet lock 26, in which the single-stage missile projectile 28 is located. The propellant charge 29 contained in the combustion chamber 27 and arranged in a ring around the end of the missile projectile, like the stationary propellant charges 4 and 5 of the previous example, consists of small powder rods with a suitable cross section. The missile projectile 28 may have a missile head similar to that in the previous example, with a tip 30 and a shaped charge 31 of 160 mm in diameter. The missile projectile can have the same empennage 32 with wings 33, whereby depending on the position of the wings the projectile is given a greater or lesser rotation and the empennage serves to guide the missile in the tube. The tail unit is followed by the combustion chamber 34 of the rocket, which is closed off from its nozzle 35 by a grating 36 with an opening 36a. This combustion chamber 34, like the combustion chamber 10 in the previous example, contains a base 37 which serves as a sabot and which has to take up the total internal pressure of the tube of approximately 1000 bar and consequently must have a suitable strength, while in this arrangement the remaining part of this rocket stage from Internal pipe pressure is relieved and only has to be dimensioned for the approximately 10 times smaller combustion chamber pressure of this stage. This also applies to the previous example. The combustion chamber 34 is loaded, as in the previous example, with relatively thick powder bars, the total thrust of which is dimensioned to correspond to the air resistance of the projectile in order to prevent the drift by the side wind, as described above. At the level of the sabot, the missile projectile has a three-part sabot ring 38 which separates from the projectile after leaving the tube. The missile missile will sealed from the stationary combustion chamber 27 by means of a seal 39. The inner wall 40 of the stationary combustion chamber 27 has holes 41 in order to allow the fuel gas to pass through to the missile projectile. The stationary combustion chamber 27 is closed off by an outlet nozzle 42 with a cover 43, the cover flying away when ignited and can be made from a combustible material such as cellulose. A black powder capsule 44 with detonator 45 is attached to the cover 43.

The shot is fired via the igniter 45, which ignites the black powder charge 44, as a result of which both the stationary propellant charge 29 and the propellant charge are ignited in the combustion chamber 34 of the missile projectile. Essentially, the stationary propellant charge of the missile gives the initial speed, while the propellant charge of the missile projectile maintains the initial speed, i. H. serves to overcome air resistance, making the missile projectile insensitive to side winds.

• Kaliber 200mm, Hohlladung 160mm, Geschoßgewicht 25 kg, Gewicht der Geschoß-Treibladung 4 kg, Schubkraft = Luftwiderstand 1000kg, Anfangsgeschwindigkeit 1000m/sec, Zielentfernung 1000 m, Länge des Rohres 4 m, Gewicht des Rohres 500 kg, Gewicht der geladenen stationären Brennkammer 250 kg, Gewicht der stationären Treibladung 30 kg, Brennzeit 10 ms.

The example described has approximately the following data:

• Caliber 200mm, shaped charge 160mm, projectile weight 25 kg, weight of the projectile propellant charge 4 kg, thrust = air resistance 1000kg, initial speed 1000m / sec, target distance 1000 m, length of the tube 4 m, weight of the tube 500 kg, weight of the loaded stationary combustion chamber 250 kg, weight of stationary propellant charge 30 kg, burning time 10 ms.

When using this missile projectile as an anti-tank missile, it can be mounted on a similar mount as in the previous example, with the difference that the tube, as mentioned at the beginning, is firmly attached to the upper part of the mount. It is expedient to use a loading trough 25 for inserting the projectile and the loaded combustion chamber, which is only indicated in FIG. In addition, the same accessibility features as described above can be used.

• 2. Granaten aller Art
• 3. sogenannte Bomblets, d. h. Flugkörper mit Hohlladungen, die so zu Boden fallen, daß die Hohlladung von ca. 80 mm Durchmesser nach oben gerichtet ist und auf Panzer oder andere Fahrzeuge anspricht. Bomblets eignen sich zum zeitweiligen Sperren eines Gebietes für Panzer und Fahrzeuge aller Art, wobei beispielsweise 10 Stück pro Schuß abgefeuert werden können. Die Zeitdauer, während welcher die Bomblets scharf sind, ist nur der eigenen Truppe bekannt und kann vorher eingestellt werden und
• 4. Flugzeugabwehrgeschosse. In den Fig. 3, 4 und 6 ist ein Flugzeugabwehrsystem dargestellt, welches auf der großkalibrigen Flugkörperanlage gemäß Fig. 2 basiert. Der stationäre Teil, d. h. das Rohr 24, die stationäre Brennkammer 27 mit den hinteren Verschlußteilen 42 und 43 sind die gleichen wie bei Fig. 2 und daher nur teilweise dargestellt. Statt eines einzelnen Geschosses sind eine Vielzahl, in vorliegendem Beispiel 19, Einzelgeschosse im Rohr angeordnet, mit je einem Gewicht von etwa 1 kg, einem Durchmesser von ungefähr 25 mm und einer Länge von 800 mm. Die Spitze 47 des Einzelgeschosses 46 enthält einen Aufschlag- oder Annäherungszünder und einen Zeitzünder. Jedes Einzelgeschoß enthält eine Brennkammer 48 mit einer Treibladung von ungefähr 0,25 kg Gewicht und einer Brennzeit von 3 bis 4 Sekunden, sowie einen Brennkammerboden 50 und weist ein Leitwerk 51 mit Flügel 52 auf. Die Einzelgeschosse sind in einer mehrteiligen Hülse 53 mit einem Gitter oben und einem Treibspiegelboden 54 mit Gasdurchlaßöffnungen 54a gehalten, der gegenüber der stationären Brennkammer 27 mit einer Dichtung 55 abgedichtet ist. Wie beim vorhergehenden Beispiel dient die stationäre Treibladung 29 dazu, den Raketen eine Anfangsgeschwindigkeit von etwa 1000 m/Sek. zu erteilen, während die einzelnen Treibladungen der Geschosse dazu dienen, diese Anfangsgeschwindigkeit während der Brennzeit von 3 bis 4 Sekunden zu bewahren, um so die vorher beschriebene Stabilisierung zu erreichen. Sehr bald nach dem Austreten der Geschosse aus dem Rohr fällt die Hülse mit dem Treibspiegelboden und dem Gitter ab. Die Treibladungen der Flugkörper werden beim Abschuß gezündet, beispielsweise direkt durch die Gase im Rohr, die durch die Gasdurchlaßöffnungen 54a hindurchtreten. Die Gase bewirken ebenfalls eine Drehung des Flugkörpers im Rohr durch das Leitwerk.

With the large-caliber rocket tube, a variety of other projectile bodies can be fired, e.g. B.

• 2. Grenades of all kinds
• 3. So-called bomblets, ie missiles with shaped charges that fall to the ground so that the shaped charge of approximately 80 mm in diameter is directed upwards and responds to tanks or other vehicles. Bomblets are suitable for temporarily blocking an area for tanks and vehicles of all kinds, whereby, for example, 10 pieces can be fired per shot. The length of time during which the bomblets are sharp is only known to your own troops and can be set beforehand and
• 4. Anti-aircraft missiles. 3, 4 and 6, an aircraft defense system is shown, which is based on the large-caliber missile system according to FIG. 2. The stationary part, ie the tube 24, the stationary combustion chamber 27 with the rear closure parts 42 and 43 are the same as in Fig. 2 and therefore only partially shown. Instead of a single storey, a large number, in the present example 19, individual storeys are arranged in the tube, each with a weight of approximately 1 kg, a diameter of approximately 25 mm and a length of 800 mm. The tip 47 of the single storey 46 contains an impact or proximity fuse and a time fuse. Each individual storey contains a combustion chamber 48 with a propellant charge of approximately 0.25 kg in weight and a burning time of 3 to 4 seconds, as well as a combustion chamber floor 50 and has an empennage 51 with a wing 52. The individual storeys are held in a multi-part sleeve 53 with a grille at the top and a sabot bottom 54 with gas passage openings 54a, which is sealed off from the stationary combustion chamber 27 by a seal 55. As in the previous example, the stationary propellant 29 serves to give the rockets an initial speed of approximately 1000 m / sec. to be given, while the individual propellant charges of the projectiles serve to maintain this initial speed during the burning time of 3 to 4 seconds in order to achieve the stabilization described above. Very soon after the bullets emerge from the tube, the sleeve with the sabot bottom and the grille falls off. The propellant charges of the missiles are detonated when fired, for example directly by the gases in the tube which pass through the gas passage openings 54a. The gases also cause the missile in the tube to rotate through the tail unit.

With a propellant charge of 0.25 kg per single storey, the thrust is about 15 kg, which is sufficient, the initial speed of 1000 m / sec. to maintain for 3 to 4 seconds. A flight destination 4 km away is therefore reached in 4 seconds. During this time, an aircraft can perform a different evasive maneuver of approximately 50 m. In order to achieve a good chance of being hit, it is advisable to arrange several, for example 8 to 12 tubes on a common carriage, as shown in FIG. 6 is shown schematically. The upper part 58 of a stationary or mobile mount can be seen there, which carries on both sides a horizontally arranged, pivotable axis 56, on which a fastening block 57 is arranged, which for example carries 4 rocket tubes 24, which are loaded as in the present example. If the 8 pipes fire at the same time, about 150 floors will be started at the same time. With an average spread of 2.5% of the distance, there are about 150 storeys in a target circle of 100 m (8000 m2), that is about one storey per 50 m ² . A target of 50 m ² could therefore be hit with some probability. When using fewer floors, but with an approximation are fired, the probability of a hit is increased by the splinter density. The timer also causes the projectiles to be dismantled after 4 to 6 seconds. When using the carriage described here, it is only possible to achieve a hit in a plane that is exactly perpendicular to the directional axis. The aiming is done in such a way that an approaching target is detected with a radar device. The target distance and the movement, as well as the temporal change in the movement (acceleration) of the target is determined spatially. From this data, a connected computer can calculate and continuously correct the point on the target level at which the target pierces the target level. With known bullet ballistics, the computer also determines the elevation angle of the swivel axis and the exact time of firing, as well as the number of pipes to be fired. The aiming and firing of the entire volley is done automatically. In this way it is possible to bring a large number of projectiles to the target with a high probability of being hit. The disadvantage of using a single mount is that a target that flies parallel to the target plane cannot be hit. Therefore, in order to capture such targets, it is necessary to use several mountings, the direction or swivel axes of which form an angle to each other.

When calculating the elevation angles, it is possible to prevent projectile fragments from falling onto certain areas by blocking certain angular areas.

If the radar device and the computer together with the operator are gimbal-mounted on the pivot axis, this axis need not be arranged horizontally and can therefore be adapted to the course of the terrain.

The setting up of the directional mount or the swivel axis within wide limits can also be achieved in that the computing device is mechanically or electrically coupled to the swivel axis and the deviation of the swivel axis from the horizontal in the computing device is taken into account by a pendulum system. This allows the guide gun to be placed on the ground and the aiming process can then be carried out immediately without further preparation.

Both the missile tubes and the missile projectiles can be designed and used differently than described. For example, in the exemplary embodiment according to FIG. 1 it is possible to use only one or more than two stationary propellant charges and to build the two parts in dimensions other than those proposed. In addition, it is possible to use a different alignment gun with other alignment aids and in particular to use alignment frames that are connected to a central computer.

In the exemplary embodiment according to FIG. 2, it is also possible to use a multi-stage rocket instead of a single-stage one, while the specified data can be varied accordingly. When designing the missiles as anti-aircraft bullets, a large variation in the dimensions and in the number and type of the individual bullets used per tube is possible. A different selection from materials known per se is also possible with regard to the stationary propellant charges used in the missiles.

7 to 9 show an embodiment variant of the example according to FIG. 2 with the aim of making the part to be replaced as light as possible. With each shot, the entire rear combustion chamber is no longer replaced, but only a missile projectile with a cartridge, which weighs about 60 kg compared to about 250 kg with the same caliber.

The cartridge 60, which can be inserted from behind via a nozzle base which can be folded away or folded down, indicated at 59, contains a cartridge sleeve 61, expediently made of a combustible material, with the stationary propellant charge 62 (see FIG. 8), the marching engine 63, which corresponds to that of FIG. 2 corresponds. The sleeve wall 71 of the cartridge can be cylindrical or conical in order to be able to insert and withdraw the cartridge better. The known outlet nozzle 64 connects to the sleeve at the rear, while the warhead 65 is arranged at the front, which can have a shaped charge, shrapnel, bomblets or the like. The interior 66 of the stationary combustion chamber 67 is cylindrical or conical. In Fig. 9 you can see the propellant charge 68 consisting of rods with a profile suitable for burning, the combustion chamber wall 69 and the stationary propellant charge 62, which is arranged concentrically therewith and consists of powder rods or platelets, between the sleeve wall 71 and an inner cartridge wall 70, in the inner Cartridge wall 70 openings 73 are attached, which run non-radial in order to give the projectile an additional rotation by the action of the fuel gases on the tail unit 32. The other elements indicated are as in the previous examples, in particular as in FIG. 2.

The primer 45 with black powder charge 44 is arranged on the base of the cartridge. The supply ammunition can be arranged at the rear end of the gun, for example in a carousel with an automatic loading system known per se. It is expedient to protect the ammunition from the exhaust gases and to provide a protective plate 74. The stock ammunition can comprise different types of projectiles, that is, for anti-tank or anti-aircraft defense, or for other targets.

The shooter then only needs to set the appropriate control element, which means that the relevant ammunition is fed and this automatically into the station re combustion chamber inserted and the nozzle bottom piece is closed. At the same time, the computer for calculating the lead angle with the ballistics belonging to the loaded ammunition is put into operation. In the anti-aircraft projectiles, the time fuse for disassembling the warhead is set if no proximity fuse is used.

The above shows that the gun can be used very versatile and with a high firing order.

The carriage can be arranged stationary or, depending on the caliber, on lighter wheeled or tracked vehicles. The gun carriage must be as immobile as possible when shooting or aiming. The vehicle must therefore stop, whereupon the carriage, possibly together with the vehicle, is raised by several suitable hydraulic or mechanical supports and can be shot as quickly as possible. It is obvious that the vehicle or the carriage must be set up in a suitable manner in order to ensure that the pipe is largely free to move both in the vertical and in the horizontal direction and that the operating team must be effectively protected against the exhaust gases emerging from the pipe .

Claims (26)

1. Recoilless missile system with at least one launcher tube and for each tube at least one rocket projectile with a tail unit (12, 32, 51), the tube (1, 24) comprising at least one chamber (2, 3; 27, 67) for receiving a propelling charge (4, 5; 29, 62), characterized in that the rocket projectile (7, 28, 46) contains at least one propelling charge (10, 34, 68) the pressure of which being about equal to the air resistance of the projectile flying at its initial speed, in order to preserve this initial speed and to eliminate the influence of the lateral wind.

2. System according to blaim 1, characterized in that the tail unit (12, 32, 51) comprises at least three fins (13, 33, 52) and in that the combustion chambers (1, 2, 3; 8, 10; 27, 67) are so designed that the emerging gases flow through the tail unit and set the projectile into rotation already in the tube for compensating the error of its trajectory due to unbalance.

3. System according to claim 1 or 2, characterized in that the tube (1) comprises at least two rings (2, 3) secured about the tube and receiving each a propelling charge (4, 5) and in that it comprises gas-passages openings (2a, 3a) located at the place of the rings.

4. System according to one of the claims 1 to 3, characterized in that the rocket projectile (7) has two stages, the pressure from the second stage (10) corresponding to about the air resistance of the flying projectile.

5. System according to claim 4, characterized in that the first stage (8) contains a propelling charge of thin annular foils of nitroglycerine-nitrocellulose.

6. System according to one of the claims 1 to 5, characterized in that the tube (1) to be changed after each fire lies on a laying gun carriage (20) comprising means for pointing in the vertical and horizontal direction, a sighting telescope (23) and a telemeter.

7. System according to claim 1 or 2, characterized in that a spherical chamber (27) for receiving a stationary propelling charge (29) is mounted by a bayonet catch (26) at the rear end of the tube (24).

8. System according to claim 7, characterized in that the internal wall (40) of the chamber (27) comprises gas-passage openings (41).

9. System according to one of the claims 1 to 8, characterized in that the stationary combustion chamber (1, 27, 67) is closed at the rear by a removable cover (43, 59) comprising a detonator (44) with a primer (45).

10. System according to claim 1 or 2, characterized in that at the rear of the tube (24) is arranged a cylindrical or conical stationary combustion chamber (67) with a cylindrical or conical internal wall (66) in which may be inserted a gun cartridge (60) with a cylindrical or conical gun cartridge shell (71) enclosing the rocket projectile (28) with a detonator (44) and a primer (45) as well as a propeller (63) and warhead (65).

11. System according to claim 10, characterized in that the stationary propelling charge (62) is arranged between the gun cartridge shell (71) and an internal gun cartridge wall (70) and in that the internal gun cartridge wall comprises openings (73) arranged non-radially so that the influence of the combustion gases on the tail unit (32) of the rocket projectile imparts an additional rotation to the latter.

12. System according to claim 10 or 11, characterized in that after loosening of the breech (59) the bottom part of the nozzle (64) is slewable laterally.

13. System according to one of the claims 10 to 12, characterized in that it comprises stock ammunition with different warheads and in that the gun cartridges (60) are supported in a tournament arranged at the rear end of the gun and protected against the outgoing gases by a protecting sheet (74).

14. System according to claim 1, characterized in that the rocket projectile (28, 46) comprises a single stage (34,48) the pressure of which corresponding to about the air resistance of the flying projectile.

15. System according to one of the claims 1 to 14, characterized in that the second (10) or single stage (34) comprises a bottom (37) serving as a pressure reflector which is designed for supporting the whole internal pressure of the tube.

16, System according to one of the claims 1 to 15, characterized in that a grade (18, 36) with a closing part (19) is arranged in front of the nozzle (9, 35) of the second or single stage.

17. System according to one of the claims 1 to 16, characterized in that the rocket projectile (7, 28) comprises a pressure reflector of several parts (57, 38) serving as a guide in the tube (1, 24) and which is so mounted that it comes apart after leaving the tube.

18. System according to claim 14 or 15, characterized in that the rocket projectile (28, 46) is made tight with respect to the tube (24) by means of a seal (39).

19. System according to claim 7, characterized in that the tube (24) is firmly bound with an upper part of a laying gun carriage (20) comprising directing means (22) adjustable vertically and horizontally, a sighting telescope (23) and a telemeter as well as a loading cavity (25).

20. System according to one of the claims 1 to 19, characterized in that it comprises means for adjusting the deflection of the tube in case of a mobile target if the sighting telescope is always directed on the target.

21. System for the anti-aircraft defense according to one of the claims 7 to 14, characterized in that the tube (24) contains a number of rocket projectiles (46) removably arranged at a bottom serving as a common pressure reflector (54).

22. System according to claim 21, characterized in that many tubes (24) having same orientation are fastened to a laying gun carriage (58) comprising a single shaft (56) slewable in one direction.

23. System according to claim 21 or 22, characterized in that it comprises an apparatus for detecting the target and a computing apparatus for calculating the angle of elevation of the slewing shaft (56), of the launching time and of the number of projectiles.

24. System according to claim 23, characterized in that the detection apparatus and the computing apparatus are mounted by cardan suspension on the slewable shaft (56).

25. System according to one of the claims 1 to 20, characterized in that the point (14, 30) of the projectile (7, 28) comprises a hollow charge.

26. System according to claim 21, characterized in that the rocket projectiles comprise an impact or proximity detonator and a time detonator.

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