EP0180722B1 - Missile - Google Patents

Description

The invention relates to a missile according to the preamble of patent claim 1.

Missiles are to be understood as rockets launched from launcher tubes as well as projectiles fired from tubular weapons which have a tail unit for stabilizing the trajectory. In order to improve the accuracy of such missiles, a second wing-surrounding tail unit is often provided, which is arranged in front of the tail unit in the direction of flight. A particularly great effect can be achieved with this second tail unit if the wings of this tail unit protrude far beyond the diameter of the missile.

From the document DE-C3-25 18 593 a missile is known which corresponds to the features of the preamble of claim 1. A pyrotechnically drivable motor is used to swing open the front stabilizing wings folded into the housing.However, it is arranged in the area of the wing bearing racks and therefore requires a considerable amount of energy to open, with none of the holding means securing the idle wing wings and releasing them for the opening process Disclosures are disclosed.

From the document US-A-3,047,257 an aircraft is known in which a fluid motor is used for the controlled adjustment of the geometry of an aircraft wing, whereby, however, comparatively small adjustment paths can only be carried out over a longer period of time.

From US-A-4,262,862 it is known to open the tail wings in a rocket via a cable drive driven by a piston / cylinder unit. Here, however, the fulcrum of the empennage wing lies outside the rocket body, which is why this rope construction is very space-consuming and - in particular due to the high launch loads - is not suitable for a projectile fired from a barrel weapon.

The invention has for its object to provide a missile corresponding to the features of the preamble of claim 1 with a particularly effective and reliable working second tail unit, which can be safely opened even after a very long storage time and with large acceleration loads.

This object is achieved on the basis of a missile of the type specified in the introduction by the invention specified in claim 1.

Advantageous refinements and developments of the invention emerge from the subclaims.

Fig. 1:

eine schematische Darstellung eines Flugkörpers mit einem Heckleitwerk und einem zweiten Leitwerk;

Fig. 2:

in Teilschnittdarstellung eine vergrößerte Detaildarstellung des Flugkörpers gemäß Fig. 1;

Fig. 3:

eine Schnittdarstellung des Flugkörpers entlang der Linie III - III nach Fig. 2 mit Blick entlang des Pfeils 3';

Fig. 4:

eine vergrößerte Detaildarstellung des Flugkörpers und zwar als Schnitt entlang des Kreissektors IV - IV nach Fig. 3;

Fig. 5:

eine Schnittdarstellung des Flugkörpers entlang der Linie V - V nach Fig. 2.

Fig. 6:

einen Querschnitt durch eine Weiterbildung der Erfindung.

The invention is explained in more detail below with reference to the drawings. It shows:

Fig. 1:

a schematic representation of a missile with a tail unit and a second tail unit;

Fig. 2:

a partial sectional view of an enlarged detail of the missile according to FIG. 1;

Fig. 3:

a sectional view of the missile along the line III - III of Figure 2 with a view along arrow 3 '.

Fig. 4:

an enlarged detail view of the missile as a section along the sector IV - IV of FIG. 3;

Fig. 5:

3 shows a sectional illustration of the missile along the line V-V according to FIG. 2.

Fig. 6:

a cross section through a development of the invention.

1 shows a schematic representation in side view of a missile 100 with a tail unit 101 provided for the trajectory stabilization and a tail unit 102 comprising a second wing 14, which seen in the direction of flight before the Tail unit 101 is arranged. This second tail 102 enables the flight path of the missile 100 to be influenced particularly precisely in the final phase of its flight path. Wings 14, which are designed to protrude far beyond the diameter of the missile 100, are particularly effective for this purpose.

In order to enable the missile 100 to be fired from launch tubes or weapon barrels with a predetermined caliber, which essentially corresponds to the outer diameter of the missile 100, the wings 14 of this second tail unit 102 are designed to be retractable, at least during the launch or launch process and only afterwards, but at the latest at the beginning of the final phase of the trajectory, by means explained in more detail below, in order to get into their working position.

FIG. 2 shows a partial sectional view of an enlarged detail of the missile according to FIG. 1, namely the middle part at the height of the second tail unit 102. A wing 14 that is folded out in the working position and a wing 14 that is folded in the rest position can be seen. In the rest position, the wing 14 is in an axially extending slot 20 arranged in the outer wall of the missile 100. In order to move from the rest position into the working position, the wings 14 are rotatably mounted about axes 21 arranged perpendicularly with respect to the longitudinal axis 103 of the missile 100. The opening is expediently against the direction of flight of the missile 100, so that attacking air forces support the opening process. Special requirements are placed on the means which transfer the wings 14 of the second tail unit 102 from the rest position into their working position. On the one hand, these funds should take up as little space and weight as possible, since they are dead loads reduce the missile's payload; on the other hand, they should work reliably even after a long period of storage, even with the strongest acceleration forces, and unfold the wings 14 that were initially folded in. According to the invention, the means for unfolding the wings 14 comprise an inflatable body (airbag) 12, 12 'which, when the wings 14 are in the rest position, is folded up in a confined space essentially in the area of the longitudinal axis 103 of the missile 100 in such a way that their bearing point on the axes 21 facing end pieces of the sinks 14 sunk in the slots 20 rest on this folded body 12, 12 '. From this folded position, this inflatable body 12, 12 'can be inflated by supplying gas, it preferably expanding in the radial direction and being inflatable to an essentially disk-shaped structure. By this inflation process, which takes place in a very short time with gas supply, a force acting in the radial direction is exerted on the ends of the wings 14 so that they pivot about the axes of rotation 21 and get into their working position, in which they are essentially perpendicular to the Stand longitudinal axis 103 of the missile 100. Reference number 12 denotes the inflatable body in the folded state; Reference number 12 'the inflated state. A high-tension gaseous medium for acting on the body 12, 12 'is carried in a compressed gas container 3 which is connected to the inflatable body 12, 12' via gas channels 4, 6 with the interposition of an optionally electrically remote-controlled pressure reducing valve 5. Until the wings 14 of the tail unit 102 unfold, the compressed gas container 3 is closed by a gas-tight closure 2. This closure 2 is removed in order to initiate the opening process of the wings 14, for example by means of a pyrotechnic primer 1. Before that flowing out of the compressed gas container 3 high-tension gas for the purpose of unfolding the wing 14 acts on the inflatable body 12, 12 'and gives it the shape clearly recognizable in FIG. 4, a fuse must first be removed which locks the wing 14 in the rest position within the axial slot 20. This fuse consists of a slide 7, which is slidably mounted in the gas channel 6 in the direction of the longitudinal axis 103 and which carries a cup-shaped retaining disk 8, which engages with its side wall 8 'in a recess 23 arranged in the outer edge 22 of the wing 14. For this purpose, gas flowing out of the compressed gas container 3 after removal of the closure 2 reaches the gas channel 6 via the gas channel 4 and the pressure reducing valve 5 and moves the slide 7 so far in the flight direction along the axis 103 that the side wall 8 'of the cup-shaped holding disk 8 disengages from the recess 23 of the wing 14 and thereby releases it. The movement of the slide 7 then opens a bore 11 in the gas channel 6, which connects it to the inflatable body 12, 12 'and enables it to be inflated by the gas pressure present in the gas channel 6. Due to the radial expansion of the inflatable body 12, 12 ', the wings 14 are swung around suddenly and thus get into their working position in which they are locked by spring-loaded bolts 24 which engage in recesses 25 arranged in the vicinity of the axis of rotation 21 in the wing 14.

The means provided according to the invention for unfolding the wings 14 can be accommodated in a comparatively narrow space and work even after a very long storage time even under high acceleration loads According to a further embodiment of the invention, which is only shown in a schematic cross-sectional drawing in FIG. 6, the wings 14 of the tail unit are arranged in the radial direction and are arranged inside the shell of the missile 100. Its end pieces facing the missile axis rest on an inflatable body 12 which is folded up in the idle state. When this inflatable body 12 is subjected to a gas pressure, it expands and pushes the wings 14 outward in the radial direction, so that they get into their working position.

In all exemplary embodiments of the invention, the inflatable body 12, 12 ′ consists of a gas-tight material that can withstand high pressure loads. For example, a fabric-reinforced rubber cover or a cover made of a plastic is particularly suitable.

Claims (4)

1. Missile with a tail unit system (101) and a second control surface system (102) which is positioned in front of the tail unit as viewed in the direction of flight and of which the blades (14) are constructed so that they can be extended by certain means in opposition to the direction of flight, the blades (14) being situated, when in their position of rest, in slits (20) taking an axial course in the outer casing of the missile (100) and being mounted so as to be rotatable about shafts (21) positioned perpendicular to the longitudinal axis (103) of the missile (100), characterised by the fact that for the purpose of locking the blades (14) in the position of rest a slide (7) is provided which is mounted in a gas channel (6) so as to be slidable in the direction of the longitudinal axis (103) and which is provided with a cup-shaped retaining plate (8) which by a side wall (8') engages a recess 23 situated in the outer edge (22) of the blade (14), and that a body (air bag) (12) which can be subject to pressure gas via a gas channel (6) is provided as a means for extending the blades (14).
2. Missile in accordance with Claim 1, characterised by the fact that the air bag, when the blades (14) occupy their position of rest, is folded, mainly in the zone of the longitudinal axis (103) of the missile (100), in such a way that those end pieces of the blades (14) embedded in slits (20) which face away from the position in which the blades (14) bear on the shafts (21) rest on the airbag which extends mainly in the radial direction and which can be inflated to a substantially disc-shaped structure.
3. Missile in accordance with one of Claims 1 or 2, characterised by the fact that the means for extending the blades (14) comprise a pressure gas container (3), and that the body (12,12') is connectable to the pressure gas container (3) via the gas transmission channels (4,6).
4. Missile in accordance with one of Claims 1 to 3, characterised by the fact that for the purpose of locking the blade a spring loaded bolt (24) is provided which, after the extension of the blade (14) engages a recess (25) situated in the vicinity of the shaft (21).

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