DE1027561B - Longitudinal swinging folding tail for rocket projectiles - Google Patents

Description

GERMAN

The invention relates to a longitudinally swingable folding tailgate for rocket projectiles, the individual wings are opened by at least one helical spring each parallel to the axis of the projectile.

It is known to use the aforementioned folding guards in grenades to stabilize the projectile trajectory. This stabilization of the projectile trajectory requires that the tail unit wings and their cushioning, which at least partially cause the wings to spread, essential parts of the space of the grenade claim, which od for the explosive device. The like. Are lost, whereby the effect of the grenade is unfavorable being affected.

Compared to the known it is in the invention to rocket projectiles, i. H. Bullets with own reaction drive, which are equipped with a nozzle for the reaction jet. The arrangement of the Nozzle leads to the fact that between it and the cylindrical rocket jacket a full or a hollow Space that normally has no function to perform. Based on this feature of the rocket projectiles The invention consists in the fact that the coil springs that are used to open the individual wings of the Serve folding tail, are arranged in the space around the propellant nozzle of the projectile. Through this it has been achieved that the space otherwise superfluous with these rocket projectiles for accommodation the tail wing and its expanding springs are used without thereby reducing the Rocket propellant charge or the explosive device or the like.

According to the invention, it is advantageous to proceed in such a way that the wings have such a shape that they are in In the retracted position, insert it into the radial slots in the support body of the tail unit, which is at the height of the nozzle of the nozzle neck and has a cross section which is substantially the caliber of the projectile body is equivalent to.

The invention is explained below by way of example with reference to the drawing.

1 and 2 show the rear part in a partially sectioned side view and rear view, respectively a designed according to a first embodiment of the invention missile projectile with retractable Tail unit, the upper wing of which is shown in the unfolded position, while the other Wings are shown in the retracted position;

3 and 4 show, under the same conditions, a according to a second embodiment of the invention trained rocket projectile with retractable tail unit.

The missile projectile as such is designed in any way with the exception of its retractable tail unit and has z. B., as in Fig. 1 and 2 dar-longitudinal swinging folding tailgate
for rocket projectiles

Applicant:

Brevets Aero-Mecaniques SA,
Geneva (Switzerland)

Representative: Dr. H. Wilcken, patent attorney,
Lübeck, Breite Str. 52/54

Claimed priority:
Luxembourg of July 21, 1955

placed on a missile body 1, which contains the propellant charge (z. B. powder sticks) and to the rear is extended by a discharge nozzle 2 from which the jet of propellant gas emerges.

The actual retractable tail unit consists in a known manner of a certain number of wings 3 (z. B. four) which are arranged at the rear end of the rocket and are each pivotable about an axis 4 which is perpendicular near the base of the unfolded wing is arranged to the axis XY of the rocket, the deployment of the wings by a tilting movement from front to back in a plane passing approximately through the axis XY. This tilting movement is indicated by the curved arrow F. In Fig. 1, the upper wing is shown in the deployed position and the lower wing in the retracted position.

According to a characteristic of the invention, the pivot axis 4 of each wing is not permanently installed, but in such a way that it can be adjusted within certain limits in a direction parallel to the axis XY of the rocket.

At the foot of each wing 3 a to the axis 4 concentric tooth sector 5 is provided, the with a rack 6 rigidly connected to the nozzle 2 and the body 1 of the projectile stands, the toothed sector 5 and the rack 6 are mutually so that when adjusting the Pivot axis 4 from its foremost position (retracted wing) to its: rearmost position (ent- *

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f al teter wing) the toothed sector 5 rolls on the rack 6 and thus forces the corresponding wing 1 out pass from the retracted position to the deployed position.

For the wing such a shape is expediently chosen that they are in the retracted position in place radial slots / in a tail unit holder 7, which surrounds the nozzle 2 in particular in the zone of its neck and has a cross section which corresponds approximately to the cross section of the body 1 of the missile.

When the missile is in the launcher, e.g. B. a launch tube, the wings 3 are drawn into the slots f and do not form a projection on the body 1 of the rocket, the axes 4 of the wings taking their foremost position shown in Fig. 1 for the lower wing.

As soon as the missile leaves the launcher, the acceleration acting on it favor the Centrifugal force generated by the rocket's rotation around its axis (if the rocket has such a Movement) and that acting on each wing from the beginning of its unfolding movement Air resistance is the unfolding movement of the wings 3. According to the invention, the axis 4 of each stands Wing 3 to achieve the deployment movement under the action of an elastic system, e.g. a coil spring 8, the axis 4 from its foremost To bring the position in which the corresponding wing is retracted into its rearmost position seeks in which the wing is unfolded.

According to a further characteristic of the invention, these helical springs 8 lie parallel to the axis XY of the rocket in recesses 9 in the tail unit holder 7.

Each axis lies in a slideway 10 mounted in the tail unit holder 7 parallel to the axis XY and protrudes with its ends into two recesses 9 which are mounted in the holder 7 on both sides of the slideway 10 parallel to the latter.

A helical spring 8 is located in each recess 9 arranged, which with its front end against the bottom of the corresponding recess 9 and with its rear end against the protruding into the relevant recess 9 end of the axle 4, where appropriate a pressure piece 11 is arranged between the spring 8 and the corresponding end of the axle 4 can be.

The above retractable tail rocket has the following advantages, among others:

It has a simple structure.

When the wings are in their retracted position, no part protrudes outside, as the return system the wing lies completely within the cross section of the missile body 1.

The wings unfold very quickly as a result of a large number of those that favor this unfolding Factors, especially the effect of the springs 8.

In the unfolded position, the wings 3 assume a stable position, since each wing then moves with it the foot section of its rear edge against the rear wall 12 of the missile body and with a nose 13 against the rear flank of the rack 6 puts.

The wings 3 can be returned to their retracted position from the deployed position when this should become necessary during the handling preceding the launch.

In the embodiment shown in FIGS. 3 and 4, each wing 3 is pivotable about an axis 4a, which is mounted in the tail unit holder 7 without the possibility of axial adjustment. Each wing 3 is under the action of two return springs 14 which are approximately parallel to the axis X-Y in the tail unit holder. These springs work in tension and are anchored with their front end on the tail unit holder 7 and with their rear end on the ends of a sliding finger 15, the middle part of which acts on a nose 16 provided on the foot part of the wing. The springs 14 thus contribute to the deployment of the wings when the missile has left the launcher.

It should be noted that you can do it in particular by an appropriate dimensioning of the inclination of the Can set up nose 16 so that the finger 15 between its guide slide and the front end this nose is clamped when the corresponding wing 3 has come into its open position is (position shown for the upper wing in Fig. 3). The finger 15 prevents it from being jammed Vibrations of the wing 3 and also relieves the corresponding spring 14, which after opening of the wing, the blocking of the same takes place exclusively by the finger 15.

Finally, it should be noted that the use of coil springs to open the wings 3 both in the embodiment according to FIGS. 1 and 2 as well as in the embodiment of FIGS. 3 and 4, an abbreviation the opening time of the wings and also allows each wing to be designed so that its center of gravity in the retracted position is closer to the longitudinal axis of the projectile than the pivot axis 4 of the wing in question, so that the helical spring then adjusts the wing from its retracted position causes a position in which the inertial forces in the opening direction of the wing work.

Claims (6)

PATENT CLAIMS: 1. Longitudinal swinging folding tail unit for rocket projectiles, whose individual wings are at least a helical spring lying parallel to the projectile axis can be opened, characterized in that, that the coil springs (8, 14) in the space around the propellant nozzle (2) of the projectile are arranged. 2. Tail unit according to claim 1, characterized in that each wing axis (4) parallel to the projectile axis ( XY) can be displaced to a limited extent, a toothed sector (5) centered on the axis (4) being provided at the foot of each wing (3) in a known manner , which is in engagement with a rack (6) fixed to the nozzle casing (2), the toothed sector and rack being arranged in such a way that when the turning axis (4) is displaced from the front folded position to the rear unfolded position, the toothed sector * rolls on the rack and thereby takes the wings with it. 3. Tail unit according to claim 1, characterized in that the wings have such a shape that they insert in the retracted position into radial slots (f) in the support body of the tail unit which surrounds the nozzle (2) at the level of the nozzle neck and has a cross section which corresponds essentially to the caliber of the projectile body. 4. tail unit according to claim 1, characterized in that the expanding springs (8) of the wings (5) are arranged in individual recesses of the tail boom. '5. Tail unit according to claim 1, characterized in that the wing axes (4 a) are fixed and each expansion spring (14) moves a sliding finger (15) with a stop (16) on the foot of the wing cooperates, this stop (16) occupies such a position that the Spring (14) favors the development of the wing. 6. tail unit according to claim 5, characterized in that that the stop (16) of each wing and the driver finger (15) work together so that the finger is clamped on its slide by the stop (16) as soon as the wing reached its fully open position. Considered publications: French Patent Nos. 502 394, 715 385, 502; British Patent No. 634,090;
U.S. Patent No. 2,365,577. 1 sheet of drawings © 709 958/86 3.58