DE1258765B - Projectile with a rocket propellant that can be fired from a barrel with the aid of an auxiliary launch charge - Google Patents

Description

FEDERAL REPUBLIC OF GERMANY

GERMAN

PATENT OFFICE

EDITORIAL

Int. CL:

F42b

German class: 72 d-19/10

Number: 1 258 765

File number: S 906311 c / 72 d

Filing date: April 18, 1964

Open date: January 11, 1968

The invention relates to a rocket propellant for launching from a rocket propellant Tube with the help of an auxiliary launcher charge suitable projectile with a device for delayed ignition the rocket propellant after launch and with an exhaust pipe for the propellant gases, into which a detachable tail tube is inserted, the ejection tube forming the projectile tail a tail unit carries.

The use of such projectiles also in infantry combat, especially as armor-piercing Weapon has the great advantage that the projectiles can be fired from any barrel. On the one hand then the projectiles, regardless of whether they are provided with a hollow or full charge, have good flight characteristics and with a Rocket propellant of sufficient power must be provided, on the other hand it must also be ensured that that the projectile receives sufficient accuracy.

While the first two requirements do not present any major difficulties, it is possible to achieve them Sufficient accuracy with the previously known projectiles of the type mentioned not guaranteed. Rather, it turns out that the stabilizing effect of the projectiles provided on these projectiles Tail unit is not sufficient to prevent the projectile after leaving the Launch tube deviates more or less far from its predetermined trajectory.

The technical object of the invention is to provide a projectile of the general type given at the beginning To train training with considerable explosive power and a high-performance rocket propellant in such a way that that it follows a given trajectory as precisely as possible and accordingly one high accuracy developed.

This technical task is carried out according to the basic idea the invention achieved in that the tail pipe is additionally provided with stabilizing surfaces is provided, which with the tail unit of the projectile an aerodynamic unit with accordingly Form increased effect or to compensate for the launch up to the ignition of the rocket propellant occurring vibrations interact.

In the case of the projectile according to the invention, the tail pipe acts very quickly and precisely dampening the vibrations of the projectile during launch due to the combined effect of its stabilizing surfaces with those of the tail unit on the projectile. As a result, the rocket propellant is only ignited when these vibrations are completely dampened from a pipe with the help of a
Auxiliary launcher charge of a launchable projectile
with a rocket propellant

Applicant:

Societe Technique de Recherches

Industrielles & Mecaniques, Paris

Representative:

Dipl.-Ing. R. H. Bahr

and Dipl.-Phys. E. Betzier, patent attorneys,

4690 Herne, Freiligrathstr. 19th

Named as inventor:
Michel Precoul, Paris

Claimed priority:

France of April 30, 1963 (933 236)

are, so that there is a very high accuracy.

Only after these vibrations have been balanced is the tail pipe blown off because it is then his Has served its purpose. As a result, this is necessary due to the stabilization surfaces attached to the tail pipe caused higher weight not to be dragged along the trajectory, and the stabilization surfaces also do not generate any unnecessary aerodynamic drag along the flight path. Appropriately and according to a further feature of the invention, the stabilizing surfaces of the blasted off tail pipe arranged so that it is in its cross-sectional projection between the stabilizing surfaces of the tail unit.

In a further embodiment of the invention is at the front end of the detached tail pipe a chamber open at the front is formed by a transverse wall. In an axial hole in the transverse wall a primer can then be used to transfer the ignition to the delay set for the propellant

... charge can be used.

The invention is explained in more detail using an exemplary embodiment that is shown in FIG Drawing is reproduced. It shows

Fi g. 1 shows a longitudinal section through a projectile according to -: the invention,

F i g. 2 shows a section along line 2-2 of FIG. 1 and
F i g. 3 shows a section along line 3-3 of FIG. 1.

709 718/113

Claims (1)

3 4 The projectile 1 has a tail unit 7 at a pierce and ignites the delay set 41. Ejection tube 35 for the gases of a rocket propellant This burns in the chamber C. At the end of it sentence. It also has a detachable tail pipe combustion it ignites the propellant charge block 44. 37 with a tail unit made up of stabilizing surfaces 39. The gases produced thereby flow first The tail unit 7 consists of wings 36 and is forward 5 through the chamber C and effect, preferably made of plastic after construction. Also, from a certain pressure level, the shearing of the throwable tail pipe with its guide surfaces, the pins 42 and thus the throwing off of the tail forms a throwable stabilization device S , pipe 37. can be made of plastic. The concentric arrangement 48 of the connection The wings with the stabilizing surfaces 39 sit io of the tail pipe with the projectile causes at the front end of the tail tube 37 close to the stabilization device S very quickly and First floor after having covered a very short distance As a result, the two tail units 39 and 7 form triggers. The projectile is therefore on the one hand not enough during the first phase of the shot and which is as disruptive as possible, on the other hand, the retains Damping of the bullet's movements by the stabilization device during the phase of the sen center of gravity an aerodynamic unit of expulsion of the gases into the chamber C a movement planned strongly increased effect. forward. If N is the number of wings 36 of the tail unit 7 The delay in the ignition of the delay of the projectile, the number N 'is the rate 41 is based on the degree of the launch Wing with the stabilizing surfaces 39 according to the 20 effective damping of the vibrations of the Invention N '= -% - K where K = I or preferential imposed projectile matched this environment, even ^ö 2 ° whose aerodynamic and dynamic example 2 is understandable. The wings of the stabilization device S characteristics are to be taken into account in the cross-sectional projection between the wings 36 of the stabilization device 7 of 25 can be summarized as follows: the actual projectile arranged in order to achieve better aerodynamic effects . Plant 7 of the projectile and the rocket propellant 5 The shape of the tail tube 37 of the stabilizer - a reinforced stabilization system, which is very The device S depends on the type of the launch of the projectile. In the case of which it compensates for vibrations that occur. There- The exemplary embodiment provided is the case of these vibrations as soon as the ignition is triggered Rifle grenade accepted. That is why the rocket propulsion took place, largely attenuated. Tail pipe 37 the task of the barrel of the rifle Then the tail pipe 37 has served its purpose, to enclose. It is thrown off and forms along the rest of the At its front end, the tail tube 35 does not carry any unnecessary aerodynamic trajectory 37 a primer 40, which from the resistance. shoot the projectile through gases through the rocket propellant can be beaten up will. This primer 40 ignites the loan acceleration of the projectile achieve because Delay rate 41 of the rocket propellant 5. That no longer the risk of inaccuracies in the Ge tail pipe 37 is de-sheared on the projectile with the help of 40 lap track at the transition to self-propulsion 42 of a predetermined strength. Therefore, the shot can be carried out with a reduced charge solidifies. the firing weapon and accordingly reduced The propellant charge 5 sits in an ejection tube 35, delivered at the initial velocity of the projectile which the tail unit 7 is attached. This pipe is to be. This reduction can e.g. B. Va up to ^2/3 the connection to the 45 also has one on the front. The decrease in charge means, however The plug 43 producing the head T of the projectile results in a considerably reduced recoil of the weapon closed. and therefore also considerably lower vibrations A propellant charge block 44 is in the firing phase on its periphery. This results in invention » 45 and its forward face is inhibited. He burns according to a significantly improved accuracy, from its rear edge and through its 50 Some of the features described above middle channel, which causes the bullet to advance slowly, also when ejecting Gradual combustion in its chamber 35 "results in the maintenance of a after that of the tail pipe On the rear side of the propellant charge 5 is a movement component pointing forward and a pipe socket 46 which widens backwards and which is thrown off in the rearward direction. The body 35 of the propellant charge 5 is elongated 55. This prevents any dangerous hurling movement in a projection 35 ', which prevents the connection of the pipe of the tail pipe in the direction of the shooter ver ~ 37 of the stabilization device S together with. There is also one, even if the pins 42 are used. rings, additional speed of the projectile. A delay set 41 is attached in the widening part of the pipe socket 46 with the aid of a tight bell body 41 '. During combustion 1. With a rocket propellant for the delay set 41, the chamber C is sealed off from the outside by being fired from a tube with a HiMe toric seal 47. Since the primer device for the delayed ignition of the smoke is sealed on the opposite side, the chamber C is completely closed with a ketene propellant after the launch. ■ an exhaust pipe for the propellant gases, When the projectile is fired, the detonator is inserted into a detachable tail pipe to protect 40 from the gases of the launch charge, whereby the outgrowth forming the projectile hack shock tube carries a tail unit, characterized in that that the tail pipe (37) is additionally provided with stabilizing surfaces (39) which are connected to the tail unit (7) of the projectile form an aerodynamic unit with a correspondingly increased effect or to compensate for it the vibrations occurring when firing up to the ignition of the rocket propellant. 2. Projectile according to claim 1, characterized in that the stabilizing surfaces (39) of the blastable tail pipe (37) in its cross-sectional projection between the stabilizing surfaces (35) of the tail unit (7) are arranged. 3. Projectile according to claim 1, characterized in that the front end of the detachable Tail tube (37) is formed by a transverse wall, a chamber (C) open at the front. 4. Projectile according to claim 3, characterized in that in an axial bore of the transverse wall a primer (40) for transmitting the ignition to the delay set (41) for the Propellant charge is used. Considered publications:
French Patent No. 1147 642;
U.S. Patent Nos. 3,008,414, 2,944,486. 1 sheet of drawings 709 718/113 12.67 © Bundesdruckerei Berlin