EP0840086B1 - Launching device for self-propelled missile, in particular for rockets - Google Patents

Description

The invention relates to a launcher for self-propelled missiles, in particular artillery missiles.

Such launchers are known per se. A known launching device described in EP 0 731 331 A2 has a launch tube in which the Missiles to be fired in the ready-to-fire condition is arranged so that it is in the front area over several support bodies arranged on its circumference is supported on the inner surface of the launch tube.

However, such training encounters difficulties once the missile is at its aft end with freely radially projecting tail wings is. Since this is not the inner wall of the launch tube should be touched, the launch tube should one accordingly have a large inner diameter. this leads to but difficulties in the construction of the Support body, which then has a significant radial expansion should possess, which in turn creates difficulties in guiding and releasing the support body after leads to the launch.

US-A-3 769 876 discloses a launcher for Missile with foldable tail unit described with a square container that doubles as a transport container serves. In the container is at the top and one on the bottom in the longitudinal direction running support rail attached, and the Missile is in the area between the support rails arranged. The lower support rail acts as a guide element a cross-sectionally U-shaped guide rail, in which a support body runs. The upper Support rail carries a guide rail that comes with a longitudinal groove and lateral grooves is provided in the guide lugs located at the front and rear of the missile intervention. On both sides of the missile there are free spaces to accommodate the folded Tail surfaces on the outside of cylindrical rest on curved guide rails.

In WO-A 93/02333 a sub-caliber floor from Sabot type described. That with stabilizing wings provided floor is from a cage surrounded, which is composed of individual segments is. The stabilizing wings are within the Cage. The projectile is shot down from a pipe, whose inside diameter is the outside diameter of the cage corresponds, and after leaving the pipe the cage disintegrates into the individual segments.

The invention has for its object a launcher to create who is trained that missiles can be fired from it, at the rear end with freely radially protruding Tail wings are provided, with support body with usual radial expansion should be used.

According to the invention, the solution is achieved with the features from claim 1. Advantageous further developments of the invention are in the dependent claims described.

The basic idea of the invention is that Support body not on the inner wall of the launch tube itself to support and guide, but rather as the cylinder inner surface sections trained guide surfaces to be arranged on own guide elements in such a way that they are offset radially inwards, whereby between the guide elements in the circumferential direction in predetermined angular distances through slots for the tail wings of the missile are provided.

In principle, it would be possible to have such guide surfaces in such a way that to produce in a pipe with accordingly large pipe thickness running in the longitudinal direction Grooves for receiving the tail wings are incorporated become. The cost of materials would then be extraordinarily large and the pipes would be very heavy. Because of this, it is beneficial how described further below using an exemplary embodiment, the guide elements in strips, for example than cut out of a tube in the longitudinal direction Form strips and these on the To fix the inner wall of the launch tube.

This leads to much lighter designs for the launch tube and too much material savings.

The formation of the launcher according to the invention it also allows the support body in both the front as well as in the rear area of the missile to arrange its scope so that this at two in Cross sections arranged one behind the other in the longitudinal direction is guided and supported. The Support body also with anti-twist devices be combined.

The following is based on the accompanying drawings an embodiment of a launcher explained in more detail according to the invention.

Fig. 1 eine Artillerierakete in Seitenansicht in einer Stellung, in der die Leitwerkflügel in einer vertikalen und einer horizontalen Ebene liegen;

Fig. 1A eine Ansicht von hinten in der Ebene IA-IA in Fig. 1;

Fig. 1B eine Ansicht von vorne in der Ebene IB-IB;

Fig. 2 die Artillerierakete nach Fig. 1 in einer um die Längsachse um einen Winkel von 45° gedrehten Stellung;

Fig. 2A eine Ansicht von hinten aus der Ebene IIA-IIA;

Fig 2B eine Ansicht von vorne aus der Ebene IIB-IIB;

Fig. 3A einen schematischen Querschnitt durch ein Abschlußrohr ohne eingesetzte Artillerierakete;

Fig. 3B einen Schnitt analog Fig. 3A bei eingesetzter Artillerierakte in einer Ansicht aus der Ebene IIIB-IIIB in Fig. 1;

Fig. 3C einen Schnitt analog Fig. 3A bei eingesetzter Artillerierakete in einer Ansicht aus der Ebene IB-IB in Fig. 1;

Fig. 4 den Schnitt durch das Abschußrohr mit eingesetzter Artillerierakte gemäß Fig. 3B, wobei das Abschußrohr nach der Linie VI-VI in Fig. 7 dargestellt ist;

Fig. 5 einen Schnitt durch das Abschußrohr ohne eingesetzte Artillerierakete in einer gegenüber Fig. 3A vergrößerten Darstellung, wobei das Abschußrohr im Schnitt nach der Linie V-V in Fig. 7 dargestellt ist;

Fig. 6 einen Schnitt durch das Abschußrohr analog Fig. 4 ohne eingesetzte Artillerierakete nach der Linie VI-VI in Fig. 7;

Fig. 7 einen Schnitt durch das Abschußrohr gemäß der Linie VII-VII in Fig. 5;

Fig. 8 einen vergrößerten Ausschnitt aus dem Abschußrohr gemäß dem Feld VIII in Fig. 7;

Fig. 9 in einer explodierten perspektivischen Darstellung die Stege und die Tragschichtabschnitte eines Führungselements des Abschußrohres nach den Fig. 1 bis 8 vor und nach dem Zusammensetzen;

Fig. 10 in einer explodierten perspektivischen Darstellung mehrere Tragschichtabschnitte von Führungselementen mit daran befestigten Stegen und Verbindungsringen des Abschußrohres nach den Fig. 1 bis 8 während des Zusammensetzens vor dem Einbau in das Abschußrohr.

The drawings show:

Figure 1 is an artillery rocket in side view in a position in which the tail wings are in a vertical and a horizontal plane.

Fig. 1A is a rear view in the plane IA-IA in Fig. 1;

1B is a front view in the plane IB-IB;

FIG. 2 shows the artillery rocket according to FIG. 1 in a position rotated about the longitudinal axis by an angle of 45 °;

2A is a rear view from the plane IIA-IIA;

2B is a front view from the plane IIB-IIB;

3A shows a schematic cross section through an end pipe without the artillery missile used;

3B shows a section analogous to FIG. 3A with the artillery file inserted in a view from the plane IIIB-IIIB in FIG. 1;

3C shows a section analogous to FIG. 3A with the artillery missile inserted in a view from the plane IB-IB in FIG. 1;

4 shows the section through the launch tube with the artillery file according to FIG. 3B, the launch tube being shown along the line VI-VI in FIG. 7;

5 shows a section through the launch tube without the artillery missile used, in an enlarged view compared to FIG. 3A, the launch tube being shown in section along the line VV in FIG. 7;

6 shows a section through the launch tube analogous to FIG. 4 without the artillery missile used along the line VI-VI in FIG. 7;

Figure 7 is a section through the launch tube along the line VII-VII in Fig. 5.

8 shows an enlarged detail from the launch tube according to field VIII in FIG. 7;

9 shows an exploded perspective view of the webs and the base layer sections of a guide element of the launch tube according to FIGS. 1 to 8 before and after assembly;

Fig. 10 in an exploded perspective view of several base sections of guide elements with attached webs and connecting rings of the launch tube according to Figs. 1 to 8 during assembly before installation in the launch tube.

1, 1A and 1B and 2, 2A and 2B is one Artillery rocket 1 in two against each other around the longitudinal axis positions rotated by 45 ° are shown. The missile 1 is freely radial at its rear end protruding tail wings 2.1, 2.2, 2.3 and 2.4 provided. To shoot from a closer below explained launch tube 5 are in the front section the rocket 1 a total of 4 at equal angular intervals support bodies 3.1, 3.2 arranged on the circumference, 3.3 and 3.4 in place, while at the rear end of the Missile 1 behind the tail wings also in equal angular distances four support bodies 4.1, 4.2, 4.3 and 4.4 are arranged.

With the rocket not yet inserted into the launch tube 1 are the support body 3.1 to 3.4 and 4.1 to 4.4 in a known manner via mounting straps, not shown attached to the missile 1. After insertion the missile 1 will be in the launch tube as soon as the support body on the described below Support the guide surfaces of guide elements, the straps loosened and pulled out.

The launch tube is shown in FIGS. 3A to 7 with used rocket shown in more detail.

To support and guide the support body 3.1 to 3.4 and 4.1 to 4.4 serve guide surfaces 6.1, 7.1, 8.1, 9.1 (see Fig. 3A and Fig. 5), the one Have a distance from the axis of the launch tube 5, which is smaller than the inside radius of the launch tube. These guide surfaces are in a predetermined Distance from the inner wall of the launch tube 5 attached guide elements 6, 7, 8 and 9 arranged. The guide elements 6 to 9 extend through the entire launch tube 5 in the longitudinal direction and in the circumferential direction in each case over predetermined angular ranges of, for example, 68 ° (see FIG. 6), and are between the guide elements 6 to 9, respectively longitudinal slits 11 for the passage of the empennage wings 2.1, 2.2, 2.3 and 2.4 (see Figures 3B, 3C and 4). The Guide surfaces 6.1, 7.1, 8.1 and 9.1 are as cylinder inner surface sections trained whose axes coincide with the axis of the launch tube 5. How The drawings show the guide elements 6 to 9 as running in the longitudinal direction and cylindrically curved in the transverse direction Stripes formed, for example, by dividing a corresponding pipe section in two on top of each other vertical planes, which are in the Cut longitudinal axis, can be obtained.

Each of the guide elements 6 to 9 is shown in the Embodiment five in the longitudinal direction extending and substantially radial to the axis of the Launch tube 5 standing connecting webs 10, the along its one longitudinal edge with the guide element and along the other longitudinal edge with the launch tube inner wall are connected in the launch tube 5 attached. Here, as can be seen in FIG. 7, in each case several webs (in Fig. 7 with 10.1 ... 10.n referred to) adjoin one another in the longitudinal direction arranged. The attachment of the webs 10 to the launch tube 5 and on the guide elements 6 to 9 via screw connections. 4 to 7 show the exact structure of these screw connections.

Each of the guide elements is made up of two layers built up, namely an outer base layer 16, which consist of several, adjoining one another in the longitudinal direction Base course sections 16.1 to 16.n (Fig. 7) and a continuous inner guide layer 6.2, 7.2, 8.2 and 9.2. The outer base layer 16 or the base layer sections 16.1 to 16.n are over screws pointing from the inside out 13 connected to the connecting webs 10 while the continuous inner management layer 6.2, 7.2, 8.2, 9.2 over from the outside inwards Screws 14 with the base layer 16 or the base layer sections 16.1 to 16.n is firmly connected. 4, these screw connections are located outside the areas where the support body 3.1 - 3.4 (or 4.1 - 4.4) on the guide surfaces 6.1 - 9.1 slide.

To achieve material savings on the one hand and on the other hand, enough material for the screw connections is the thickness of the connecting webs 10, as can be seen for example in FIGS. 4 to 6, larger in the area of their longitudinal edges than in Area of their middle.

So that a good connection of the longitudinal ones Crosspieces 10 and at the joints a reliable connection is guaranteed, are in the area of the joints between two groups adjoining one another in the longitudinal direction from connecting bars 10.i - 10.i + 1 (10.1 -10.2 in 7) connecting rings 18 inserted into the launch tube 5, with which the 15 screw connections Ends of the connecting webs 10.i and 10.i + 1 (10.1 and 10.2 in Fig. 7) are screwed. The screw connection the connecting webs at the ends with the base layer 16 of the guide elements are made using screw connections 13. Likewise, at the two ends of the launch tube 5 each connecting rings 17 in the launch tube 5 used with the ends of the connecting webs 10.1 or 10.n via screw connections 15 are screwed and at these points to the base layer are connected via screw connections 13. The connecting rings 17 have half the width of the Connection rings 18.

Possible angular distances between the bars and screw connections 6 can be seen on the circumference of the tube; possible radial distances of the individual elements from the The axis of the launch tube 5 can be seen in FIG. 5.

The base layers 16 on the one hand and the guide layers 6.2, 7.2, 8.2, 9.2 on the other hand can from different materials.

There are swirl prevention devices on the rear support bodies 4.1 to 4.4 arranged.

The support body 3.1 to 3.4 and 4.1 to 4.4 can so be built like this in the older unpublished DE-OS 19 508 008 is described.

9 and 10 show an exploded perspective Presentation of phases in a possible procedure for assembling a launch tube according to the Fig. 1 to 8.

As the upper part of Fig. 9 shows, the Base layer sections, one of which is shown in Fig. 9 and is designated by reference number 16, in each case five webs 10 attached and screwed (s. Fig. 7), so that that shown in Fig. 9 at the bottom Partial element is created. This sub-element is shown in Fig. 10 in the upper part. How recognizable there, several of these become one Base layer section 16 and five webs 10 existing Part elements attached to connecting rings, by those in Fig. 10 a later inside the launch tube lying connecting ring 18 and one at the end the launch tube lying connecting ring 17 shown is. The parts are attached to each other again by means of screw connections according to 7 and 8.

It is then in a manner not shown continuous guide layers on the base layers 16 screwed on, as can be seen again from FIG. 7 and then the whole of the guide elements, the webs and the connecting rings Forms inserted into a launch tube and there again attached by means of screws 12 according to FIG. 7.

The composition of the whole launch tube with its Guide elements made up of a large number of identical designs Sharing favors automatic production.

Claims (12)

1. Launching device for self-propelled missiles, in particular artillery rockets, having at least one launcher tube (5), in which the missile (1) to be launched is arranged in the state of readiness for launch such that it is supported in the front region via a plurality of support elements (3.1, 3.2, 3.3, 3.4) disposed on its periphery against guide surfaces (6.1, 7.1, 8.1, 9.1) in the interior of the launcher tube (5), wherein the support elements (3.1, 3.2, 3.3, 3.4) rest against the missile (1) in such a way that during the launch they are conveyed together with the missile out of the launcher tube and then released, and wherein the guide surfaces (6.1, 7.1, 8.1, 9.1) are portions of the inner surface of a cylinder, the axes of which coincide with the axis of the launcher tube (5) and which are at a distance from the tube axis which is smaller than the inner radius of the launcher tube (5) and which are disposed on four guide elements (6, 7, 8, 9), which are fastened at a preset distance from the inner wall of the launcher tube (5) and extend in longitudinal direction of the launcher tube (5) at least from a point in the vicinity of the back end of the launcher tube (5) up to the tube mouth and in peripheral direction in each case over preset angular regions, wherein longitudinally extending through-slots (11) for tail fins (2.1, 2.2, 2.3, 2.4) are disposed between the guide elements (6, 7, 8, 9).
2. Launching device according to claim 1, characterized in that the guide surfaces (6.1, 7.1, 8.1, 9.1) are disposed at the inside of longitudinally extending strip-like guide elements (6, 7, 8, 9), which are curved cylindrically in transverse direction and fastened to the inner wall of the launcher tube (5).
3. Launching device according to claim 2, characterized in that the fastening of the guide elements (6, 7, 8, 9) is effected in each case by means of connecting webs (10), which extend in longitudinal direction and substantially radially relative to the launcher tube axis and are connected along their one longitudinal edge to a guide element (6, 7, 8, 9) and along the other longitudinal edge to the inner wall of the launcher tube (5).
4. Launching device according to claim 3, characterized in that each guide element (6, 7, 8, 9) is connected to the inner wall of the launcher tube by a plurality of connecting webs (10.1 ... 10.n) arranged consecutively in longitudinal direction.
5. Launching device according to claim 3 or 4, characterized in that the connecting webs (10 or 10.1 - 10.n) are connected to the launcher tube (5) and the guide elements (6, 7, 8, 9) in each case by means of screw connections (12, 13).
6. Launching device according to one of claims 2 to 5, characterized in that each of the strip-like guide elements (6, 7, 8, 9) is composed of two layers, namely an outer supporting layer (16), which is screw-connected to the connecting web (10), and an inner guide layer (6.2, 7.2, 8.2, 9.2) firmly connected to the supporting layer (16).
7. Launching device according to claim 6, characterized in that the guide layer (6.2, 7.2, 8.2, 9.2) is screw-connected to the supporting layer (16).
8. Launching device according to one of claims 3 to 7, characterized in that the thickness of the connecting webs (10) is greater in the region of their longitudinal edges than in their middle region.
9. Launching device according to one of claims 3 to 8, characterized in that in the region of each of the junction points between two groups of connecting webs (10.1 to 10.n) arranged consecutively in longitudinal direction a connecting ring (18) and at either end of the launcher tube (5) a connecting ring (17) is inserted into the launcher tube (5), to which connecting ring the ends of the connecting webs (10.1, 10.n) are screw-connected.
10. Launching device according to one of claims 1 to 9, characterized in that an anti-spin device is disposed in the region of the tail (2.1, 2.2, 2.3, 2.4) of the missile (1).
11. Launching device according to one of claims 1 to 10, characterized in that support elements (4.1, 4.2, 4.3, 4.4) disposed in the back region of the missile (1) are situated behind the tail (2.1, 2.4).
12. Launching device according to claim 10 and 11, characterized in that the anti-spin device is disposed on the back support elements (4.1, 4.2, 4.3, 4.4).

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