Missile for intercepting alien drones
AssigneesRheinmetall Air Defence AG, Skysec GmbH
InventorsManuel METZ, Franco METZ
Life of this patent
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Abstract
The invention relates to a missile (1) for intercepting alien drones (21), comprising a capturing net (9) and a parachute (18), wherein a plurality of weights (15) are connected to the capturing net (9), wherein the capturing net (9) can be ejected from the missile (1) and the weights (15) can be ejected from the missile (1). The capturing of the alien drone is improved by the fact that the capturing net (9) can be ejected by a first means and the weights (15) can be ejected by a second means, wherein the weights (15) and the capturing net (9) can be ejected at different times from the missile (1).
Claims16
Missile (1) for intercepting alien drones (21) comprising a capturing net (9) and a parachute (18), wherein a plurality of weights (15) are connected to the capturing net (9), wherein the capturing net (9) can be ejected from the missile (1), wherein the weights (15) can be ejected from the missile, characterised in that the capturing net (9) can be ejected by means of a first means and the weights (15) can be ejected by means of a second means, wherein the weights (15) and the capturing net can be ejected from the missile (1) at different points of time.
Missile according to any one of the preceding claims, characterised in that the capturing net (9) is arranged in a container (11), wherein the container (11) forms a rear area of the missile (1), wherein the container with the capturing net (9) can be ejected by the first means.
Missile according to any one of the preceding claims, characterised in that the weights (15) are arranged in ejector receptacles (14), wherein the ejector receptacles (14) are arranged in the longitudinal direction of the missile (1) seen in front of the container (11).
Missile according to any one of the preceding claims, characterised in that the missile (1) comprises a replaceable unit (12), wherein the replaceable unit (12) comprises the capturing net (9), the weights (15) and the ejector receptacles (14).
Missile according to the preceding claim, characterised in that the replaceable unit (12) comprises a fuselage part (13), wherein the fuselage part (13) comprises a hollow space (17), wherein a parachute (18) is arranged in the hollow space (17), wherein the parachute (18) is connected to the fuselage part (13) and/or the capturing net (9) via a flexible connection means (19, 20).
Missile according the preceding claim, characterised in that the hollow space (13) adjoins the container (11), wherein the container (11) comprises an opening (26), wherein the capturing net (9) is connected to the weights (15) and/or a parachute (18) via a flexible connection means (16, 19) and this connection means (16, 19) or the capturing net (9) are guided through the opening (26).
Missile according to any one of the preceding claims, characterised in that the internal diameter of the container (11) is larger than the opening (26).
Missile according to any one of the preceding claims, characterised in that the capturing net (9) in the form of a coiled rope is arranged in the container (11) and thus forms a winding, wherein an end of the rope connected to the weights (15) is found inside the winding and a free coil end is found on the outside of the winding.
Missile according to any one of the preceding claims, characterised in that the missile (1) has the form of a rocket.
Missile according to any one of the preceding claims, characterised in that the missile (1) comprises a plurality, in particular more than three circumferentially spaced wings (2).
Missile according to any one of the preceding claims, characterised in that the missile (1) has a drive (5), in particular a propeller drive (6) in front of the centre of gravity of the missile (1) in the direction of flight.
Missile according to any one the preceding claims, characterised in that the weights (15) are arranged in the area of the centre of gravity of the missile (1).
Missile according to any one of the preceding claims, characterised in that the maximum airspeed of the missile (1) is over 100 km/h, in particular over 200 km/h.
Missile according to any one of the preceding claims, characterised in that the first means and/or the second means are formed by at least one pyrotechnic propellant and/or a means operating with pressurised air.
Missile according to any one of the preceding claims, characterised in that a means for ejecting the parachute (18) from the hollow space (13) is provided.
Dependencies are inferred from the claim text.