ES1306016U - SHOULDER-FIRED WEAPON SYSTEM WITH REMOVABLE SHUTTER - Google Patents

Abstract

Rocket-projectile assembly, characterized in that it comprises: - a rocket-projectile (1); - a container-launcher (2), which serves to contain the rocket-projectile (1) before being launched, and also serves as a launching weapon for the rocket-projectile (1); - a propulsion system, inside the tube (7), and comprising a countermass (21), behind the rocket-projectile (1); - a shutter (14), located between the rocket-projectile (1) and the countermass (21), to shut off exhaust gases in the tube (7); - perimeter fins (22) on the back of the rocket-projectile (1), and which, inside the tube (7) are folded forward, in a longitudinal orientation, but which, once the rocket-projectile (1) leaves the tube (7) are configured to deploy, towards a radial orientation, to stabilize the rocket projectile (1) during flight; and - elongated connecting elements (20) arranged perimeter around the rocket-projectile (1) and the shutter (14), engaging one with the other, and partially overlapping on a rear part of the fins (22), so that, When the fins (22) deploy, they move the connecting elements (20), which detach from the rocket-projectile (1) and the shutter (14), allowing the shutter (14) to be released.

Description

DESCRIPTION

SHOULDER-FIRED WEAPON SYSTEM WITH SHUTTER

REMOVABLE

Technical field

The present invention can be included in the sector of combat weapons, in particular, rocket projectiles with a container container that serves to launch the rocket projectile. More specifically, the object of the invention refers to a shoulder-fireable weapon system, in which a rocket-projectile is launched using a container that contains it, and which has a removable shutter, as well as incorporating various new developments that facilitate its use and provide improved benefits.

Background

In the aforementioned technical sector, the weapons described in invention patents ES8307368, ES2019503 and utility model ES1092530 are known, in which a rocket-projectile is fired using so-called "rocket motor" propulsion systems. using as a launcher a container that contains it, and that also incorporates the shooting and aiming devices, so they are single-use.

Specifically, patent ES8307368 describes a simple aiming equipment without magnification, although it already includes the use of a shooting reticle, where patent ES2019503 incorporates as an improvement an optical equipment, also equipped with a shooting reticle, and providing image magnification, according to an arrangement in which the aiming equipment is mobile and is placed either on any one of two supports located on the sides of the launcher, to facilitate use by both right- and left-handed shooters. For its part, the utility model ES1092530 proposes optical aiming equipment placed on a single support, to which it is solidly fixed by mechanical means and/or by the use of adhesives. This last improvement has the drawback that the aiming equipment is excessively exposed to falls and impacts due to it protruding from the launcher.

On the other hand, the weapons described in patents ES8307368 and ES2019503 incorporate a mechano-pyrotechnic firing mechanism, in which the use of pyrotechnic chain transmission means is necessary. These transmission media are pyrotechnic in nature, such as wicks, so they are susceptible to degrading over time if they are not stored in ideal conditions, that is, within their containers and packaging, in storage tanks and under temperature conditions. and adequate humidity.

Likewise, the systems described above have mounted so-called "rocket engine" propulsion systems.

Summary description of the invention

The present invention presents a shoulder-fireable weapon system, which has a rocket-projectile to be fired directly using a container that contains it, and which has a removable shutter, as described in independent claim 1, which solves the problems. previously explained drawbacks of the state of the art. In particular, the inclusion of a shutter that detaches after firing improves the aerodynamics and external ballistics of the rocket projectile.

Other preferred embodiments of the object of the invention are explained in the dependent claims and in the detailed description, the advantages of which are summarized below:

- Have an ignition mechanism that does not maintain accumulated energy during storage, transportation and handling of the entire invention, but rather generates it at the moment of firing. Likewise, the ignition mechanism does not require the maintenance associated with the presence of batteries.

- Have foldable aiming equipment that improves protection against falls, impacts and mechanical stress during storage, transportation and handling and that optionally allows the use of thermal vision equipment that is mechanically and functionally compatible with all models of weapon systems. .

- Have front and rear protection with padded elements that improve the protection of the visor and other elements, both the launcher and the projectile, against falls, impacts and mechanical stress during storage, transportation and handling. The protections allow the shot to be taken without having to be removed.

- Propulsion through countermass to be able to fire from a closed area.

Brief description of the figures

The above and other advantages and characteristics will be more fully understood from the following detailed description of some embodiment examples with reference to the attached drawings, which should be considered by way of illustration and not limitation, in which:

Figure 1 shows a perspective view of the projectile-rocket assembly according to the present invention.

Figure 2 shows a schematic view of the ignition system of the entire invention.

Figures 3A and 3B show detailed views of the front cover (Figure 3A) and the rear cover (Figure 3B).

Figures 4 and 5 illustrate the vision equipment and a support on which to mount a thermal vision equipment.

Figures 6 and 7 illustrate the position of the countermass, the plug, the projectile and the joining elements in their location within the tube of the launcher container, both in the initial position, before firing (figure 6), and in the final position, after the shot (figure 7).

Reference list

1 rocket-projectile

2 Container-launcher

3 Propulsion charge

4 Electric igniters

5 Lead wires

6 Electric generator

7 Tube

8 Front cover

9 Back cover

10 Front protector

11 Rear protector

12 Vision Equipment

13 Housing

14 Shutter

15 First support

16 Carrier

17 Optical assembly

18 Axis

19 Second support

20 Union elements

21 Counterdough

22 Fins

23 Trigger mechanism

Detailed description of an embodiment example

Next, with the help of the attached figures 1-7 cited above, a detailed description of an example of a preferred embodiment of a projectile-rocket assembly according to the present invention is offered.

The invention refers, as shown in Figure 1, to a weapon system that can be fired from the shoulder, which incorporates a rocket-projectile (1), see Figure 6, such that the C90-CR and CS90 models, among others, of different calibers, manufactured with the same principles of concepts, as well as also incorporating a launcher-container (2), which serves to contain the rocket projectile (1) before being launched, and also serves as a launching weapon to launch said rocket-projectile ( 1).

To launch the rocket projectile (1), the assembly of the invention may include, as represented in Figure 2: a firing mechanism (23); and an ignition system, which has a propellant charge (3) of an easily activated pyrotechnic type (for example, double-based propellant, such as black powder or B-KNO3 mixture), inside which They find electrical igniters (4) electrically connected, by means of conductive cables (5), to the firing mechanism (23), through a dynamo-type electric generator (6) (either linear or rotary). At the moment of firing, a shooter (person in charge of firing the shot) presses an ignition button (not shown) and the generator releases electrical energy so that the igniters (4) ignite the propellant charge (3). .

The generator (6) in turn acts powered by a set of springs (not shown) that remain unloaded during storage and transportation of the assembly of the invention, until an activation button is activated, which is when said springs are loaded, such as as is known in the state of the art. Once the springs are loaded, pressing the firing button causes the springs to activate the operation of the dynamo generator (6) and the subsequent firing. The ignition system and the firing mechanism are inert during storage, transportation and handling of the entire invention. The choice of a dynamo generator (6), avoiding the use of batteries, provides a trip free of maintenance needs. The entire spring loading and preparation process for firing is reversible as long as the firing button is not pressed.

According to Figures 3A and 3B, the launching container (2) comprises: a tube (7), see Figure 6, preferably cylindrical in shape, open at both ends; and two covers (8, 9), front (8) (see figure 3A) and rear (9) (see figure 3B), mounted at the ends of the tube (7), to cover said tube (7), to maintain the rocket-projectile (1) in position, protected and immobilized, inside the tube (7). The tube (7) can be made of a resistant and light material, such as polyester resin or epoxy resin, reinforced, where appropriate, with fiberglass, as an example.

At the ends of the tube (7), there are protectors (10, 11) made of impact-absorbing materials, such as foams (polyethylene or polyurethane foam) with densities between 20 and 80 kg/m3, for example, that surround the tubes. ends of the tube (7) protruding longitudinally and transversely from said tube (7), to absorb both shocks, in different orientations, as well as vibrations. The protectors (10, 11) are hollow on the inside, in the longitudinal direction of the tube (7), to accommodate the covers (8, 9). The combination of protruding geometry and absorbent composition serves to protect the tube (7) and, in particular, a vision equipment (12), also referred to as "targeting equipment", mounted on the tube (7), both in transport and shooting configuration, thus avoiding exposure to shocks and vibrations, as will be described later, one of the two protectors (10, 11) is a front protector (10) that externally surrounds the corresponding end. of the tube (7), while the other of the protectors (10, 11) is a rear protector (11) also protruding from the tube (7), both longitudinally and transversely at the opposite end. In case of falls, the force of. Impact is transmitted in a longitudinal direction, the most unfavorable situation being a fall with the whole of the invention oriented vertically, while, in the case of vibrations, the effort is transmitted mainly in transverse directions.

The covers (8, 9) are connected or fitted to the respective protectors (10, 11) by means of mechanical connections such as clips, form closures, flanges, as well as optionally also by adhesive, to promote joint resistance to mechanical stress. induced by shock or vibration.

The covers (8, 9) do not need to be removed to carry out the shot, so that the rocket-projectile (1) remains protected at all times, preventing access to the interior of the tube (7) from dust, water or other type of harmful agent, in addition to considerably reducing the time necessary to configure the system "ready to shoot". This is possible thanks to the fact that the thrust developed in the shot is sufficient to remove the caps (8, 9) without affecting the shooting parameters (accuracy, range, etc.)

The set of the invention further comprises the vision equipment (12) - also referred to as "aiming equipment" - mentioned above, and shown in Figures 4 and 5. The vision equipment (12) comprises a first support (15) fixed to the tube (7), and a carrier (16), articulated with the first support (15), and in which an optical assembly (17) is mounted as a sight glass. The joint between the first support (15) and. The carrier (16) allows the carrier (16) and, therefore, the optical assembly (17) to be folded onto the tube (7), reducing the exposure of the optical assembly (17) to knocks and falls during storage, transportation and handling. of the assembly of the invention. The optical assembly (17) includes a particular reticle adapted to the external ballistics of various models of ammunition appropriate for the assembly of the invention.

The articulation between the first support (15) and the carrier (16) is done through a single rotation on a robust axis (18) for firm locking in the position of use. Preferably, the carrier (16) is configured as a parallelepiped block that extends between both ends of the first support (15), along the direction of the axis (18). The vision equipment (12) may further include a housing (13) removably mounted on the tube (7) to protect the optical assembly (17).

Additionally, the vision equipment (12) described may also include a second support (19), see Figure 5, which allows attachment of a thermal vision equipment (not shown). The second support (19) is compatible with the use of other night vision glasses by intensification, so it allows the thermal vision equipment to be placed in front of the optical assembly (17) of the folding vision equipment (12), so that in the position of use does not alter magnification or homogenization with the tube (7), thus allowing shots to be taken in conditions of low light or visibility with the same precision that can be done with the foldable vision equipment (12) under normal conditions.

The set of the invention also includes, as represented in Figure 6, a propulsion system equipped with a countermass (21), which enables use in an urban environment and, in particular, within a closed enclosure of reduced dimensions, such that inside a building. It is a launch system that reduces the amount of gases released to the outside and, above all, the pressure at which they are at the moment of being released, so that the effects of the gases, generated inside the tube ( 7) at the time of firing, they do not cause damage to the shooter or to the structure (for example, walls) of the room in which the shot occurs. The countermass (21) is a robust and rigid element, so that, while it is housed inside the tube (7), it can resist mechanical attacks due to blows, vibrations, falls, etc., and so that, while it moves inside the tube (7) during firing, correctly seal the gases inside the tube (7). On the other hand, once expelled from the tube (7), the countermass (21) breaks up into small fragments to avoid being thrown a long distance towards the rear area, also called the slipstream area, and thus maintain a rear safety area. as small as possible. A possible composition for the counterdough (21) includes a polymer casing and a filler of granular and therefore easily dispersible material, for example, sand.

On the other hand, to allow the rocket projectile (1) to reach the speed necessary for a suitable trajectory and flight conditions, and for this speed to be uniform, it is preferred that, within the tube (7), an adequate thrust is produced on the rocket-projectile (1) and the countermass (21), that is, the rocket-projectile (1) and the countermass (21) form a closed combustion chamber, the rocket-projectile (1) moving forward and the countermass (21) backwards, so it is necessary that the countermass (21) and a shutter (14) located at the back of the rocket-projectile (1) block the passage of gases to the outside from the combustion chamber.

Once the rocket projectile (1) has left the tube (7), it is desired that the rocket projectile (1) reach a configuration that is as aerodynamic as possible to reduce braking against the air. This makes it possible to maintain the speed of the rocket projectile (1) as high as possible throughout the entire trajectory. For this, it is proposed that the shutter (14) be detached from the rocket-projectile (1) once the appropriate muzzle velocity has been reached. If it does not come off, the shutter (14) offers a high surface area for the advancement of the rocket-projectile (1) due to its geometry that reaches the maximum caliber of the rocket-projectile (1) with surfaces completely frontal to the movement of the rocket-projectile (1). 1). This geometry is conditioned by its initial function of blocking the passage of gases between said plug (14) and the tube (7) and by the need to reduce the mass and length of the elements to be accelerated. This generates, on the one hand, an increase in the braking coefficient and, consequently, a highly curved trajectory that reduces the probability of hitting the target accurately. In order to implement this solution in the propulsion system, as shown in Figures 6 and 7, the rocket-projectile (1) and the shutter (14) are held together by elongated connecting elements (20). The rocket-projectile (1) has, on its rear part, perimeter fins (22) that, inside the tube (7) are folded forward, in a longitudinal orientation, but which, once the rocket-projectile (1) leaves The tube (7) is deployed, towards a radial orientation, by means of devices known in the state of the art, such as springs, to stabilize the rocket projectile (1) during flight. The connecting elements (20), as illustrated in Figure 6, are arranged, perimeter to the rocket-projectile (1) and the shutter (14), engaging one with another, and partially overlapping with a rear portion of the fins (22). . When the rocket-projectile (1) leaves the tube (7) and, as shown in figure 7, the fins (22) deploy, displacing the connecting elements (20), which detach from the rocket-projectile (1) and of the plug (14), allowing the plug (14) to detach. This same mechanism of union and separation between the shutter (14) and the rocket-projectile (1) can be applied to the union between said rocket-projectile (1) and an alternative launch system, by rocket motor, so that the launching system detaches after firing.

Claims (5)

1. - Projectile-rocket assembly, characterized in that it comprises: - a rocket projectile (1); - a container-launcher (2), which serves to contain the rocket-projectile (1) before being launched, and also serves as a launching weapon for the rocket-projectile (1); - a propulsion system, inside the tube (7), and comprising a countermass (21), behind the rocket-projectile (1); - a shutter (14), located between the rocket-projectile (1) and the countermass (21), to shut off exhaust gases in the tube (7); - perimeter fins (22) on the rear part of the rocket-projectile (1), and which, inside the tube (7) are folded forward, in a longitudinal orientation, but which, once the rocket-projectile (1) leaves the tube (7) are configured to deploy, towards a radial orientation, to stabilize the rocket projectile (1) during flight; and - elongated connecting elements (20) arranged perimeter around the rocket-projectile (1) and the shutter (14), engaging one with the other, and partially overlapping a rear part of the fins (22), so that, when The fins (22) deploy, moving the connecting elements (20), which detach from the rocket-projectile (1) and the shutter (14), allowing the shutter (14) to be released. 2. - Projectile-rocket assembly, according to claim 1, which additionally comprises: - a firing mechanism (23), with a firing button; and - an ignition system, with a pyrotechnic type propulsion charge (3), inside which are pyrotechnic igniters (4) electrically connected, by means of conductive cables (5), to the firing mechanism (23), through a dynamo-type electric generator (6), to be activated by a person in charge of firing, pressing a firing button, so that the generator (6) provides the energy necessary for the pyrotechnic igniters (4) to produce ignition of the propulsion charge (3). 3. - Projectile-rocket assembly according to any of claims 1-3, where the container-launcher (2) comprises: - a tube (7), open at both ends; - two front (10) and rear (11) protectors, located at both ends of the tube (7), and made of impact-absorbing materials, externally surrounding the ends of the tube (7) and protruding longitudinally and transversely from said tube (7 ), to absorb both shocks, in different orientations, as well as vibrations; the protectors (10, 11) being in the longitudinal direction of the tube (7); and - two covers (8, 9), front (8) and rear (9), connected or fitted into the protectors to cover the ends of the tube (7), to keep the rocket-projectile (1) in position, protected and immobilized , inside the tube (7), the covers (8, 9) being automatically removable by the rocket-projectile itself (1) and by exhaust gases, as a result of a shot of the rocket-projectile (1). 4. - Projectile-rocket assembly according to any of claims 1-3, further comprising a vision equipment (12) comprising a first support (15) fixed to the tube (7), and an articulated carrier (16). with the first support (15), and in which an optical assembly (17) is mounted as a peephole. 5. - Projectile-rocket assembly according to claim 4, where the vision equipment (12) also includes a second support (19) to attach thermal vision equipment.