EP0056789B1 - Dispositif de missile sans recul - Google Patents

Dispositif de missile sans recul Download PDF

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Publication number
EP0056789B1
EP0056789B1 EP82810021A EP82810021A EP0056789B1 EP 0056789 B1 EP0056789 B1 EP 0056789B1 EP 82810021 A EP82810021 A EP 82810021A EP 82810021 A EP82810021 A EP 82810021A EP 0056789 B1 EP0056789 B1 EP 0056789B1
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EP
European Patent Office
Prior art keywords
tube
projectile
gun
rocket
stationary
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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
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EP82810021A
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German (de)
English (en)
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EP0056789A2 (fr
EP0056789A3 (en
Inventor
Treuhand Gmbh Fides
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Individual
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Individual
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Publication of EP0056789A3 publication Critical patent/EP0056789A3/de
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Expired legal-status Critical Current

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41A—FUNCTIONAL FEATURES OR DETAILS COMMON TO BOTH SMALLARMS AND ORDNANCE, e.g. CANNONS; MOUNTINGS FOR SMALLARMS OR ORDNANCE
    • F41A1/00—Missile propulsion characterised by the use of explosive or combustible propellant charges
    • F41A1/08—Recoilless guns, i.e. guns having propulsion means producing no recoil

Definitions

  • 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.
  • missile projectiles 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.
  • the rocket tube 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.
  • 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.
  • a swirl stabilization of the projectile is not possible due to the impairment of the shaped charge effect.
  • 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.
  • 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).
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • FIG. 2 is a 200 millimeter caliber.
  • the propellant charge 29 contained in the combustion chamber 27 and arranged in a ring around the end of the missile projectile 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.
  • 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.
  • 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.
  • this missile projectile 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.
  • 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.
  • a stationary or mobile mount 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.
  • the timer also causes the projectiles to be dismantled after 4 to 6 seconds.
  • 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.
  • a connected computer can calculate and continuously correct the point on the target level at which the target pierces the target level.
  • 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.
  • 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.
  • 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.
  • FIG. 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.
  • 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.
  • the computer for calculating the lead angle with the ballistics belonging to the loaded ammunition is put into operation.
  • 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 .

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  • 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)

Claims (26)

1. Dispositif de missile sans recul avec au moins un tube de lancement et pour chaque tube au moins une fusée ballistique avec un empennage (12, 32, 51), le tube (1, 24) comprenant au moins une chambre (2, 3; 27, 67) pour recevoir une charge propulsive (4, 5; 29, 62), caractérisé en ce que la fusée ballistique (7, 28, 46) contient au moins une charge propulsive (10, 34, 68) dont la poussée correspond environ à la résistance de l'air de la fusée volant à sa vitesse initiale, afin de conserver cette vitesse initiale et éliminer l'influence du vent latéral.
2. Dispositif selon la revendication 1, caractérisé en ce que l'empennage (12, 32, 51) comprend au moins trois ailes (13, 33, 52) et en ce que les chambres de combustion (1, 2, 3; 8, 10; 27, 67) sont conçues de manière que les gaz sortant passent à travers l'empennage et mettent la fusée en rotation déjà dans le tube, pour contrebalancer l'erreur de sa trajectoire due au balourd.
3. Dispositif selon la revendication 1 ou 2, caractérisé en ce que le tube (1) comprend au moins deux anneaux (2, 3) fixés autour du tube et recevant chacun une charge propulsive (4, 5) et en ce qu'il comprend des ouvertures de passage de gaz (2a, 3a) à l'endroit des anneaux.
4. Dispositif selon l'une des revendications 1 à 3, caractérisé en ce que la fusée ballistique (7) est à deux étages, la poussée du second étage (10) correspondant à environ la résistance de l'air de la fusée en vol.
5. Dispositif selon la revendication 4, caractérisé en ce que le premier étage (8) contient une charge propulsive de nitroglycérine-nitrocelu- lose en forme de feuilles annulaires minces.
6. Dispositif selon l'une des revendications 1 à 5, caractérisé en ce que le tube (1) à changer après chaque tir repose sur un affut orientable (20) comprenant des moyens (22) de réglage vertical et horizontal, une lunette de pointage (23) et un télémètre.
7. Dispositif selon la revendication 1 ou 2, caractérisé en ce qu'une chambre sphérique (27) servant à recevoir une charge propulsive stationnaire (29) est montée par une fermeture à bain- nette (26) à l'extrémité arrière du tube (24).
8: Dispositif selon la revendication 7, caractérisé en ce que le paroi intérieure (40) de la chambre (27) comprend des ouvertures de passage de gaz (41).
9. Dispositif selon l'une des revendications 1 à 8, caractérisé en ce que la chambre de combustion stationaire (1,27,67) est fermée vers l'arrière par un couvercle amovible (43, 59) comprenant à l'intérieur un détonateur (44) avec une amorce (45).
10. Dispositif selon la revendication 1 ou 2, caractérisé en ce qu'à l'extrémité arrière du tube (24) est disposée une chambre de combustion stationnaire cylindrique ou cônique (67) avec une paroi interne cylindrique ou cônique (66) dans laquelle peut être insérée une cartouche (60) avec une douille cylindrique ou cônique (71) contenant la fusée ballistique (28) avec un détonateur (44) et une amorce (45) ainsi qu'un propulseur (63) et une tête de combat (65).
11. Dispositif selon la revendication 10, caractérisé en ce que la charge propulsive stationnaire (62) est disposée entre la douille (71) et une paroi interne de cartouche (70) et en ce que la paroi interne de cartouche comprend des ouvertures (73) disposées non radialement afin que l'influence des gaz de combustion sur l'empennage (32) de la fusée mette celle-ci en rotation additionnelle.
12. Dispositif selon la revendication 10 ou 11, caractérisé en ce qu'après détachement de la culasse (59), la partie de fond de tuyère (64) est orientable latéralement.
13. Dispositif selon l'une des revendications 10 à 12, caractérisé en ce qu'il comprend de la munition de réserve avec des têtes de combat différentes et en ce que les cartouches (60) sont supportées dans un carrousel disposé à l'extrémité arrière de la pièce et protégé des gaz sortant par une tôle de protection (74).
14. Dispositif selon la revendication 1, caractérisé en ce que la fusée ballistique (28, 46) ne comporte qu'un seul êtage (34, 48) dont la poussée correspond à environ la résistance de l'air de la fusée en vol.
15. Dispositif selon l'une des revendications 1 à 14, caractérisé en ce que le second (10) ou le seul étage (34) comprend un fond (37) servant de réflecteur de poussée conçu de manière à supporter la totalité de la pression intérieure dans le tube.
16. Dispositif selon l'une des revendications à 15, caractérisé en ce qu'un grillage (18, 36) avec une partie de fermeture (19) est disposé devant la tuyère (9, 35) du second ou de l'unique étage.
17. Dispositif selon l'une des revendications 1 à 16, caractérisé en ce que la fusée ballistique (7, 28) comprend un réflecteur de poussée en plusieurs parties (57, 38) servant de guide dans le tube (1, 24) et qui est monté de manière à se détacher après sa sortie du tube.
18. Dispositif selon la revendication 14 ou 15, caractérisé en ce que la fusée ballistique (28, 46) est rendue étanche par rapport au tube (24) par un joint (39).
19. Dispositif selon la revendication 7, caractérisée en ce que le tube (24) est relié de manière fixe avec une partie supérieure d'un affut orientable (20) comprenant des moyens d'orientation (22) réglables en vertical et en horizontal, une lunette de pointage (23) et un télémètre ainsi qu'une cavité de chargement (25).
20. Dispositif selon l'une des revendications 1 à 19, caractérisé en ce qu'il comprend des moyens pour régler le tube dans l'angle de jet en cas de cible mobile, si la lunette de pointage est toujours dirigée sur la cible.
21. Dispositif pour la défense anti-aérienne selon l'une des revendications 7 à 14, caractérisé en ce que le tube (24) contient un nombre de fusées ballistiques (46) disposées de manière amovible à un fond servant de réflecteur de poussée commun (54).
22. Dispositif selon la revendication 21, caractérisé en ce que plusieurs tubes (24) de même orientation sont fixés à un affut orientable (58) comprenant un seul axe (56) pivotant dans une direction.
23. Dispositif selon la revendication 21 ou 22, caractérisé en ce qu'il comprend un appareil de détection de la cible et un appareil de calcul pour calculer l'angle d'élévation de l'axe pivotant (56), du moment de lancement et du nombre de fusées.
24. Dispositif selon la revendication 23, caractérisé en ce que l'appareil de détection et l'appareil de calcul sont montés par cardan sur l'axe pivotant (56).
25. Dispositif selon l'une des revendications 1 à 20, caractérisé en ce que les ogives (14, 30) de la fusée (7, 28) contiennent une charge creuse (15,31).
26. Dispositif selon la revendication 21, caractérisé en ce que les fusées (46) comprennent un détonateur d'impact, ou de proximité et un détonateur à retard.
EP82810021A 1981-01-20 1982-01-19 Dispositif de missile sans recul Expired EP0056789B1 (fr)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
CH34581 1981-01-20
CH345/81 1981-01-20
EP81810236 1981-06-11
EP81810236 1981-06-11

Publications (3)

Publication Number Publication Date
EP0056789A2 EP0056789A2 (fr) 1982-07-28
EP0056789A3 EP0056789A3 (en) 1982-09-08
EP0056789B1 true EP0056789B1 (fr) 1984-08-29

Family

ID=25684282

Family Applications (1)

Application Number Title Priority Date Filing Date
EP82810021A Expired EP0056789B1 (fr) 1981-01-20 1982-01-19 Dispositif de missile sans recul

Country Status (3)

Country Link
EP (1) EP0056789B1 (fr)
DE (1) DE3260613D1 (fr)
IL (1) IL64778A0 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0228781B1 (fr) * 1985-10-31 1992-08-05 British Aerospace Public Limited Company Moteur d'expulsion pour missile
AUPS303702A0 (en) * 2002-06-20 2002-07-11 Metal Storm Limited A cartridge assembly for multiple projectiles
CN109579615B (zh) * 2018-12-20 2024-01-16 北京恒星箭翔科技有限公司 一种可在有限空间使用的单兵火箭发射系统

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE303807C (fr) *
CA868494A (en) * 1964-03-17 1971-04-13 C. C. Briercliffe Henry Recoilless gun
FR2125701A6 (fr) * 1965-11-26 1972-09-29 Thomson Csf
US3459101A (en) * 1967-11-09 1969-08-05 Us Army High velocity weapon
FR2311271A1 (fr) * 1975-05-16 1976-12-10 Serat Systeme d'arme leger, notamment antichar
SE416230B (sv) * 1976-05-17 1980-12-08 Bofors Ab Anordning for rekylfri utskjutning av en missil
US4213393A (en) * 1977-07-15 1980-07-22 Gunners Nils Erik Gun projectile arranged with a base drag reducing system

Also Published As

Publication number Publication date
EP0056789A2 (fr) 1982-07-28
DE3260613D1 (en) 1984-10-04
EP0056789A3 (en) 1982-09-08
IL64778A0 (en) 1982-03-31

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